| Army Aviation RDT and E Plan. Executive Summary. |
OCT 1976 |
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| Authors:
ARMY AVIATION SYSTEMS COMMAND ST LOUIS MO
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 | The Plan presents a time-phase analysis and presentation of the scientific and technological programs required to support the development of advanced airmobile systems responsive to the future needs of the Army. This document sets forth plans and objectives for Army aviation research and development activities for the FY77-96 period, with particular emphasis on the period from the present to 1981. Current R and D efforts in Army air mobility are ... |
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| A Laboratory Investigation Into Flight Path Perturbations During Steep Descents of V/STOL Aircraft. |
AUG 1976 |
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| Authors:
L. D. Reid; B. Etkin; H. W. Teunissen; P. C. Hughes; TORONTO UNIV (ONTARIO) INST FOR AEROSPACE STUDIES
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| Model Study of a Proposed Engineering Acoustic Research Facility (Etude sur Modele d'un Projet d'Installation de Recherches en Genie Acoustique), |
JUL 1976 |
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| Authors:
G. W. Johnston; F. Rueter; M. S. Chappell; NATIONAL RESEARCH COUNCIL OF CANADA OTTAWA (ONTARIO) DIV OF MECHANICAL ENGINEERING
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| A one-twelfth scale aeroacoustic model of a proposed engineering acoustic research facility has been tested to assess the background noise levels in the anechoic measurement area, and to develop a suitable exhaust collector for deflected jet conditions. The facility comprises an open circuit, open jet wind tunnel with an anechoic space surrounding the test section. Collector configurations with acceptably low background noise and low sensitivity to jet deflection have been ... |
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| Noise Certification Considerations for Helicopters Based on Laboratory Investigations |
JUL 1976 |
127 pages |
| Authors:
MAN-ACOUSTICS AND NOISE INC SEATTLE WA
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 | This is the second part of a program concerning noise certification for V/STOL and helicopter aircraft. Aspects considered were: an engineering calculation procedure which validly and reliably reflects annoyance to helicopter operations; estimates of noise exposure levels which could be compatible with human activities in areas surrounding heliports; noise exposure modeling for helicopter noise; certification measurement approaches for helicopter noise certification. The basics of the program involved human response evaluations ... |
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| A Study to Determine the Feasibility of Simulating the AV-8A Harrier with the X-22A Variable Stability Aircraft. |
JUL 1976 |
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| Authors:
J. Victor Lebacqz; Edwin W. Aiken; CALSPAN CORP BUFFALO N Y
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| A study program was undertaken to investigate the feasibility of conducting ground- and in-flight simulations of a jet-lift VTOL aircraft performing terminal area operations using the U. S. Navy X-22A V/STOL Research Facility. The objectives of the program were: To develop a generic mathematical model of the AV-8A aircraft during a decelerating approach to hover; To develop the methodology for computing the variable stability gains required to simulate the AV-8A ... |
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| V-STOL Ejector Short Diffuser Study. |
16 JUN 1976 |
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| Authors:
R. M. O'Donnell; R. A. Squyers; VOUGHT CORP ADVANCED TECHNOLOGY CENTER INC DALLAS TEX
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| Development of thrust augmenting ejectors has produced ejector/diffuser configurations capable of achieving the high levels of thrust augmentation necessary for VTOL aircraft propulsion requirements. Experimental testing has shown that thrust augmenting ejectors can be made more compact by reducing diffuser length with active diffusion boundary layer control employing the Antiseparation Tailored Contour (ATC). Thrust augmentation and internal flow measurements were determined in compact high performance thrust augmentors with various length ... |
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| A Study of the Failure of Joints in Composite Material Fuel Cells Due to Hydraulic Ram Loading. |
JUN 1976 |
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| Authors:
Henry Speer Ezzard Jr; NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
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| The objectives of this research were to show the relative importance of the transverse shearing forces, the bending meoments, and the tensile forces produced by hydraulic ram loading on military aircraft fuel tank joint designs for composite materials, and to present fuel tank test section designs. With the use of a finite element analysis, it was shown that the transverse shearing force may be major cause of attachment failure of ... |
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| Identification of Minimum Acceptable Characteristics for Manual STOL Flight Path Control. Volume I. Summary Report. |
JUN 1976 |
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| Authors:
Roger H. Hoh; Samuel J. Craig; Irving L. Ashkenas; SYSTEMS TECHNOLOGY INC HAWTHORNE CALIF
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| Characteristics of powered lift STOL airplanes that lead to unacceptable flight path control for approach and landing are identified. Most of the findings are based on the results of a piloted ground based simulator program. However, a short variable stability flight test program was conducted to allow interpretation of the simulation landing results in light of a flight environment. This report (Volume I) contains a comprehensive summary of the overall ... |
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| Identification of Minimum Acceptable Characteristics for Manual STOL Flight Path Control. Volume III. Detailed Analyses and Tested Vehicle Characteristics. |
JUN 1976 |
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| Authors:
Roger H. Hoh; Samuel J. Craig; Irving L. Ashkenas; SYSTEMS TECHNOLOGY INC HAWTHORNE CALIF
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| This report presents the detailed results and analysis procedures utilized to identify minimally acceptable flight path control characteristics of powered lift STOL airplanes. Deficiencies in flight path control are identified via closed loop analysis of describing function results obtained during the simulation. Unacceptable characteristics for flare and landing are identified from correlations of pilot rating and commentary with key parameters obtained from closed loop pilot-vehicle analysis. A more concise summary ... |
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| Simulating Maintenance Manning for New Weapon Systems: Maintenance Data Analysis Programs. |
MAY 1976 |
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| Authors:
Donald C. Tetmeyer; Sharon R. Nichols; Robert N. Deem; AIR FORCE HUMAN RESOURCES LAB BROOKS AFB TEX
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| A method was needed to obtain data on Air Force maintenance experience with subsystems which were similar to those being considered for application on new weapon systems. The data had to be be structured so that it would be conveniently used in developing input for a Logistics Composite Model (LCOM) simulation. This required quantifying the crew size, crew composition, task duration, and the probabilities of various task sequences; outputs that ... |
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| V/STOL Rotary Propulsion Systems - Noise Prediction and Reduction. Volume III. Computer Program User's Manual. |
MAY 1976 |
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| Authors:
B. Magliozzi; UNITED TECHNOLOGIES CORP WINDSOR LOCKS CONN HAMILTON STANDARD DIV
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| A computer program is presented which allows a user to make performance and far-field acoustic noise predictions for free-air propellers, variable pitch fans with inlet guide vanes, variable pitch fans with outlet guide vanes, fixed pitch fans, helicopter rotors, tilt rotors, fixed pitch lift vanes with remote, integral, and tip-turbine drives, and variables pitch lift fans with remote and integral drives. Noise prediction methodology for drive engines, single stream and ... |
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| V/STOL Rotary Propulsion Systems Noise Prediction and Reduction. Volume I. Identification of Sources, Noise Generating Mechanisms, Noise Reduction Mechanisms, and Prediction Methodology. |
MAY 1976 |
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| Authors:
B. Magliozzi; UNITED TECHNOLOGIES CORP WINDSOR LOCKS CONN HAMILTON STANDARD DIV
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| The propulsion systems of current and future V/STOL vehicles can be defined as combinations of free-air propellers, shrouded propellers, variable pitch fans, fixed pitch fans, tilt rotors, helicopter rotors, lift fans, gearboxes, and drive engines. In this report, noise sources for each of these propulsors, gearboxes, and drive engines are identified and rank ordered. The noise generating mechanisms for each of the propulsor noise sources identified are defined and systematically ... |
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| V/STOL Rotary Propulsion Systems Noise Prediction and Reduction. Volume II. Graphical Prediction Methods. |
MAY 1976 |
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| Authors:
B. Magliozzi; UNITED TECHNOLOGIES CORP WINDSOR LOCKS CONN HAMILTON STANDARD DIV
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| Graphical procedures for estimating noise and performance of free-air propellers, variable pitch fans with inlet guide vanes, variable pitch fans with outlet guide vanes, fixed pitch fans, helicopter rotors, tilt rotors, and lift fans are presented. Noise prediction methods for drive engines, gearboxes, jets with and without bypass flow, as well as noise reduction and performance losses for partly sonic inlets and duct linings are also presented. These graphical methods ... |
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| ARPV System/Design Trade Study. Volume IV. Launch and Recovery. |
26 APR 1976 |
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| Authors:
ROCKWELL INTERNATIONAL COLUMBUS OHIO MISSILE SYSTEMS DIV
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| On the basis of trade-off analysis of Launch and Recovery Systems for ARPV, the conventional take-off and landing method using high lift wing (STOL) technique, own thrust and arresting gear system emerged as the undisputable leader among the candidate systems. The next system in succession is the STOL configuration using modified SATS catapult conventional gear and arrester gear. The third best system comes out to be a STOL CONFIGURATION + ... |
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| Variable Jet Nozzle with Balanced Two-Dimensional Blocker Flap. |
14 APR 1976 |
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| Authors:
Sankaran Gowrinathan; DEPARTMENT OF THE NAVY WASHINGTON D C
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| A variable area jet nozzle construction capable of blocking flow in favor of another nozzle in a vertical or short take-off aircraft utilizes a balanced two-dimensional flap that is pivotable about rollers and movable, along curved tracks cooperable with the rollers, to assume a plurality of nozzle area varying or blocking positions under the influence of linear hydraulic actuators. (Author) |
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| Advanced V/STOL Propeller Critical Components Investigation. |
APR 1976 |
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| Authors:
E. H. Walz; UNITED TECHNOLOGIES CORP WINDSOR LOCKS CONN HAMILTON STANDARD DIV
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| This report presents the results of an experimental program to evaluate a full-scale Borsic aluminum composite structure spar/titanium propeller barrel retention system and a high-contact-angle duplex tapered roller bearing for an advanced technology 2000-SHP propeller system. (Author) |
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| Lift Fan Propulsion Concepts Study. |
25 MAR 1976 |
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| Authors:
Donald P. Gleiter; NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA AIR VEHICLE TECHNOLOGY DEPT
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| Contractor's conceptual designs of multimission lift fan VSTOL aircraft based on two different fan designs, one with a tip-turbine drive and one with a mechanical drive, were compared to determine the more suitable propulsion system for a Navy ASW aircraft with an initial operational capability in 1985. The comparison was based on consideration of propulsion system performance, propulsion-induced effects, propulsion system effects on flying qualities and control system design, aircraft ... |
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| Automatic Boundary Layer Control in an Ejector Wing Aircraft. |
02 MAR 1976 |
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| Authors:
Hermann Viets; DEPARTMENT OF THE AIR FORCE WASHINGTON D C
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| The patent concerns an ejector wing, for an aircraft, having inlet and diffuser doors which move from an open take-off configuration to a closed forward flight configuration and having hypermixing nozzles and root nozzles for supplying primary air into a plurality of channels in the wing structure. Apparatus is provided for controlling the air flow from the root nozzles in the boundary layer in the channels. Plurality of sensing ports ... |
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| A Flight Investigation using Variable Glide Path Trajectories to Compensate for Winds and Moderate Wind Shears (Etudes en Vol sous Differentes Trajectoires de Descente pour Compenser les Vents et les Cisaillements Moderes du Vent). |
FEB 1976 |
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| Authors:
W. S. Hindson; R. E. Smith; NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO)
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| The influence of wind, wind shears and turbulence on the approach and landing tasks of STOL and V/STOL aircraft has become of significant concern for this evolving class of flight vehicles, particularly during instrument flight operations. Flight experiments have been carried out to assess the considerations in alleviating the effects of along-track, a priori wind, including moderate shears, by adjusting the approach glide path for the conditions of the day. ... |
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| Design Comparison Between Helicopter and Tilt Rotor Aircraft. |
FEB 1976 |
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| Authors:
R. R. Oehrli; ARMY MATERIEL SYSTEMS ANALYSIS ACTIVITY ABERDEEN PROVING GROUND MD
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| A version of the AMSAA helicopter design program has been modified to include a tilt rotor analysis. This modification includes addition of a rotor strip theory performance analysis in the rigid mode. A series of studies have recently been completed with this analysis and this note has been prepared as a record of the procedures used. A discussion of the analysis and some example problems are shown. These indicate the ... |
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| An Experimental Investigation of Favorable Interference Effects from a Wing and Proprotor. |
1976 |
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| Authors:
Steven Lyttle Griffith; NORTH CAROLINA STATE UNIV RALEIGH DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
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| Although research on V/STOL aircraft has been extensive, there are other covertiplane configurations yet to be studied. Previous investigations of tilting proprotor concepts have considered the overall aerodynamic characteristics of specific designs. It is the purpose of this research to experimentally investigate the lift and drag characteristics of a constant-pitch proprotor and wing interaction system in the North Carolina State University subsonic wind tunnel. The testing system consisted of five ... |
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| Head-Up Display Symbology |
31 DEC 1975 |
80 pages |
| Authors:
William P. Orrick Jr.; Phyllis E. York; NAVAL AIR DEVELOPMENT CENTER WARMINSTERPA CREW SYSTEMS DEPT
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| This report consists of a table and accompanying illustrations which describe aircraft and weapons system functions displayed on the head-up displays in the A-7E, F-5, F-14, F-15, F-111A, CL-84, and AV-8A aircraft. Corresponding display formats as given in MIL-D-81641(AS) and MIL-STD-884B are included for comparison. |
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| Reduction of V/STOL Downwash Effects by Jet Exhuast Flow Control. |
DEC 1975 |
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| Authors:
D. E. Williams; CIVIL ENGINEERING LAB (NAVY) PORT HUENEME CALIF
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| The performance of V/STOL aircraft is influenced significantly by ground effects during landing and takeoff when the propulsive flow of the aircraft is directly dowward. To mitigate downwash effects, a new landing mat concept was developed at Civil Engineering Laboratory whereby exhaust flow is controlled by either a very thin array of diamond patterns or parallel ribs. The impinging jet flow aligns itself with the long axis of the grid ... |
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| Investigation of a Double Slotted Rudder for Application on Advanced Tactical Transport Aircraft. |
DEC 1975 |
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| Authors:
Russell F. Osborn Jr; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO
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| The aerodynamic and mechanical design of a double slotted rudder (DSR) system for possible use on the next generation STOL transport aircraft has been synthesized and the aerodynamic configuration tested in the Wichita State University low speed wind tunnel. Data collected during the Phase I wind tunnel program shows the double slotted rudder in combination with a typical transport aircraft vertical tail produces sixty per cent greater side force than ... |
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| Application of Circulation Control Rotor Technology to a Stopped Rotor Aircraft Design. |
DEC 1975 |
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| Authors:
Robert M. Williams; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
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| This paper presents the application of circulation control rotor (CCR) technology to a revolutionary new aircraft concept--the X-Wing stopped rotor V/Stol. This design affords the potential for major advances in rotary wing aircraft speed, range-payload, productivity, and cost through the application of highly innovative aerodynamic and structural design. The technology base for the concept has been derived from almost 6 years of related CCR aerodynamic and structural design studies at ... |
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| Trial Results of Ship Motions and Their Influence on Aircraft Operations for ISCS GUAM |
DEC 1975 |
112 pages |
| Authors:
A. E. Baitis; Dennis A. Woolaver; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD SHIP PERFORMANCE DEPT
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| The Naval Ship Research and Development Center made ship motion/ aircraft event correlation measurements on board the Interim Sea Control Ship (USS GUAM, LPH-9) during various deployments in 1971, 1972, and 1973. The primary objectives of these measurements were to collect and define ship motions which limit aircraft takeoffs and recoveries and to evaluate the effectiveness of GUAM's anti-roll tank. While emphasis is placed on the takeoff and recovery states ... |
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| Experimental Investigation of Multiple Jet Impingement Flows Applicable to VTOL Aircraft in Ground Effect. |
NOV 1975 |
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| Authors:
William G. Hill Jr.; Richard C. Jenkins; GRUMMAN AEROSPACE CORP BETHPAGE N Y RESEARCH DEPT
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| One of the critical areas for the design of VTOL aircraft is the special aerodynamic interactions that occur during operation near the ground (in ground effect) during takeoff and landing. Operation in ground effect can create either positive ('fountain') or negative ('suckdown') incremental forces; hot gas reingestion by the engines; and heating on the vehicle underside. One of the best ways to improve the state of the art in design ... |
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| A Simulator Evaluation of Tentative STOL Airworthiness Criteria. Volume I. Simulation Results and Analysis. |
NOV 1975 |
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| Authors:
Robert K. Heffley; John M. Lehman; Robert C. Rumold; Robert L. Stapleford; Barry C. Scott; SYSTEMS TECHNOLOGY INC MOUNTAIN VIEW CALIF
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| The general objectives of this simulation were to, evaluate the tentative airworthiness criteria and demonstrations proposed by the SSDWG. The following subject priorities were agreed upon by the Working Group: (1) Flare and landing; (2) Flight path response; (3) Cross coupling; (4) Safety margins; (5) Continued approach with an engine failure; (6) Flight path control power; and (7) Limiting flight conditions. The objectives were addressed using a single basic powered-lift ... |
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| A Simulator Evaluation of Tentative STOL Airworthiness Criteria. Volume II. Background Information. |
NOV 1975 |
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| Authors:
Robert K. Heffley; John M. Lehman; Robert L. Stapleford; Barry C. Scott; Charles S. Hynes; SYSTEMS TECHNOLOGY INC MOUNTAIN VIEW CALIF
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| A simulation program was conducted to examine specific airworthiness criteria proposed by the STOL Standards Development Working Group. The simulation included an airplane model which was deliberately designed to just meet as many of the proposed criteria as possible. The specific areas of investigation were longitudinal flight path/flight reference control, limiting flight conditions and safety margins, and propulsion system failure. Simulation results largely confirmed the approaches taken by the Working ... |
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| USAF Bioenvironmental Noise Data Handbook. Volume 58. U-10B In-Flight Crew Noise, |
NOV 1975 |
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| Authors:
Justus F. Rose Jr.; Nick A. Farinacci; AEROSPACE MEDICAL RESEARCH LAB WRIGHT-PATTERSON AFB OHIO
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| The U-10B is a USAF short-range, light cargo STOL aircraft used in counter-insurgency operations. The report provides measured data defining the bioacoustic environments at flight crew locations inside this aircraft during normal flight operations. Data are reported for one location in a wide variety of physical and psychoacoustic measures: overall and band sound pressure levels, C-weighted and A-weighted sound levels, preferred speech interference level, perceived noise level, and limiting times ... |
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| Plan for Conversion of DTNSRDC 7- X 10-Foot Transonic Wind Tunnel to Provide V/STOL Capability. |
SEP 1975 |
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| Authors:
Thomas M. Clancy; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
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| A plan is presented for adding a 12- x 15-foot V/STOL test section in the return leg of the 7- x 10-foot transonic wind tunnel at the David W. Taylor Naval Ship Research and Development Center (DTNSRDC). Features include (1) an inflatable bellmouth which is collapsible/removable to permit conversion from V/STOL to transonic operation on a quick turnaround basis and (2) provision for opening roof doors in the V/STOL section ... |
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| A Flight Investigation of Control, Display, and Guidance Requirements for Decelerating Descending VTOL Instrument Transitions Using the X-22A Variable Stability Aircraft. Volume II. Background Information and Supporting Data. |
SEP 1975 |
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| Authors:
J. Victor Lebacqz; Edwin W. Aiken; CALSPAN CORP BUFFALO N Y
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| The third flight research program using the variable stability X-22A was undertaken to investigate control, display, and guidance requirements for VTOL instrument transitions. The primary purpose of the experiment was to provide meaningful data related to the interaction of aircraft control system and displayed information characteristics on pilot rating and performance during a steep decelerating descending transition from a representative forward velocity (100 Kt) to the hover completely under instrument ... |
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| A Flight Investigation of Control, Display, and Guidance Requirements for Decelerating Descending VTOL Instrument Transitions using the X-22A Variable Stability Aircraft. Volume I. Technical Discussion and Results. |
SEP 1975 |
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| Authors:
J. Victor Lebacqz; Edwin W. Aiken; CALSPAN CORP BUFFALO N Y
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| The third flight research program using the variable stability X-22A aircraft was undertaken to investigate control, display, and guidance requirements for VTOL instrument transitions. The primary purpose of the experiment was to provide meaningful data related to the interaction of aircraft control system and displayed information characteristics on pilot rating and performance during a steep decelerating descending transition from a representative forward velocity (100 Kt) to the hover completely under ... |
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| A User's Guide to the MX Crew Ratio Simulation Model. |
AUG 1975 |
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| Authors:
Raul Garcia; Paul A. Lozano; Joseph E. Braswell; SCHOOL OF AEROSPACE MEDICINE BROOKS AFB TEX
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| The structure and products of the MX Crew Ratio Simulation Model are explained in general terms. This report is intended for persons who need to be familiar with the capabilities of the model but who have no need to know the detailed program logic. An example is also presented of some initial results using the model. (Author) |
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| Asymmetric Entrainment of 2-D Curved Jets. |
AUG 1975 |
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| Authors:
Subrato Chandra; John L. Loth; WEST VIRGINIA UNIV MORGANTOWN DEPT OF AEROSPACE ENGINEERING
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| The control of VTOL aircraft during transition from hover to forward flight is complicated by the lifting jet-airframe interaction. This analysis is concerned with the entrainment aspect of two dimensional thick curved jets. A realistic mathematical model of such jets should account for different entrainment rates and the total pressure decay in the jet. The present theoretical analysis predicts curved jet characteristics needed for an accurate mathematical modelling of two ... |
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| Lifting Jet Flow Fields. |
AUG 1975 |
|
| Authors:
John L. Loth; Richard E. Walters; Subrato Chandra; WEST VIRGINIA UNIV MORGANTOWN DEPT OF AEROSPACE ENGINEERING
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| The control of VTOL aircraft during transition from hover to forward flight is complicated due to the complex airframe-jet interaction. This investigation is concerned with mathematical modelling of asymmetric entrainment of lifting jets. The analysis is for two dimensional augmenters used on VTOL aircraft. The theoretical analysis of the lifting jets was limited to two dimensional curved jets in forward flight and out of ground effects. The aim was to ... |
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| Identification of Minimum Acceptable Characteristics for Manual STOL Flight Path Control. Volume II. STOL Aircraft Characteristics and Generic Model. |
JUL 1975 |
|
| Authors:
Samuel J. Craig; Wayne F. Jewell; Robert L. Stapleford; SYSTEMS TECHNOLOGY INC HAWTHORNE CALIF
|
| This report contains an overview of the fundamental aspects of manual flight path control as they relate to existing STOL aircraft concepts. The interrelationship between performance capability, represented for example by the glide slope polar, and path dynamic stability and control are identified. Several examples of path control problems are illustrated to substantiate the analytical discussion. A review of contemporary STOL propulsive lift concepts is given and the design features ... |
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| Army Aviation RDT and E Plan. Executive Summary. |
JUL 1975 |
|
| Authors:
ARMY AVIATION SYSTEMS COMMAND ST LOUIS MO
|
| The Army Aviation Research, Development, Test and Engineering (RDT and E) Plan is the U.S. Army Aviation Systems Command (USAAVSCOM) response to the requirement for a Consolidated R and D Plan (CRDP), which constitutes Block 13a in the Life-Cycle Management Model (LCMM) as described in the Joint CDC/AMC Materiel Need Procedures Handbook, March 1972. This Plan is prepared and maintained by AVSCOM on a continuing basis to address the short- ... |
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| Prediction Methods for Jet V/STOL Propulsion Aerodynamics. Volume I. Proceedings of a Workshop Held at the Institute for Defense Analyses, Arlington, Virginia on July 28-31, 1975, |
JUL 1975 |
|
| Authors:
Max F. Platzer; NAVAL AIR SYSTEMS COMMAND WASHINGTON D C
|
| High speed V/STOL aircraft operating from widely dispersed platforms have become of increasing interest to the U.S. Navy. The dispersed force concept requires a well developed technology base, involving phenomena and problems which do not occur on conventional aircraft or low speed V/STOL craft. Proper design must account for the interdependence of aerodynamic and propulsion phenomena, and flows so complex that purely theoretical prediction is precluded at present. A two-volume ... |
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| Prediction Methods for Jet V/STOL Propulsion Aerodynamics. Volume II. Proceedings of a Workshop Held at the Institute for Defense Analyses, Arlington, Virginia on July 28-31, 1975, |
JUL 1975 |
|
| Authors:
Max F. Platzer; NAVAL AIR SYSTEMS COMMAND WASHINGTON D C
|
| This volume continues the proceedings of the 1975 workshop on prediction methods for Jet V/STOL Propulsion Aerodynamics held at the Institute for Defense Analyses, Arlington, VA. This workshop was sponsored by the Naval Air Systems Command. The workshop participants included representatives from industry, government, universities and abroad. |
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| Investigation of Feasible Nozzle Configurations for Noise Reduction in Turbofan and Turbojet Aircraft. Volume 1. Summary and Multinozzle Configurations. |
JUL 1975 |
|
| Authors:
B. H. Goethert; J. R. Maus; William A. Dunhill; Ingo U. Borchers; TENNESSEE UNIV SPACE INST TULLAHOMA
|
| This report describes the major research activities carried out and the principal results obtained during a three year research effort by The University of Tennessee Space Institute for the Federal Aviation Administration. The major objective of this research was to develop techniques for reducing the noise generated by high velocity jet streams exhausting from a wide variety of nozzle configuration. In addition to exploring techniques for noise suppression and/or redirection, ... |
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| Investigation of Feasible Nozzle Configurations for Noise Reduction in Turbofan and Turbojet Aircraft. Volume II. Slot Nozzle Configuration. |
JUL 1975 |
|
| Authors:
B. H. Goethert; J. R. Maus; William A. Dunhill; Grant T. Patterson; Mahendra C. Joshi; TENNESSEE UNIV SPACE INST TULLAHOMA
|
| This volume contains a description of results obtained for two dimensional rectangular slot nozzles without and with straight attached flaps. Three appendices are included in this volume containing results of other research activities. |
|
| Analysis of Response Requirements for V/STOL Lift/Cruise Engines Used to Provide Height and Moment Control. |
30 JUN 1975 |
|
| Authors:
J. W. Clark Jr; NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA AIR VEHICLE TECHNOLOGY DEPT
|
| Parametric investigations were performed to determine constrainst imposed by handling qualities requirements on a V/STOL lift/cruise propulsion system when used to provide at least a portion of the vehicle moment control. Primary emphasis was placed on defining the magnitude of engine response time and incremental thrust necessary to satisfy the applicable requirements of the V/STOL Flying Qualities Specification, MIL-F-83300. Where possible the results were normalized by baseline aircraft parameters to ... |
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| The Effects of Stability Augmentation on the Gust Response of a STOL Aircraft during a Curved Manual Approach. |
JUN 1975 |
|
| Authors:
Milton B. Porter; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO
|
| The multiple precision approach paths which are possible with microwave landing systems pose new lateral separation problems for the simultaneous optimum curved approach trajectories. Separation criteria for these new multiple paths will be influenced by aircraft path tracking performance. Manually piloted STOL aircraft will be particularly sensitive to atmospheric turbulence during precision tracking. In this study a parametric variation of the open loop poles of a STOL aircraft was made ... |
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| Thrust Augmenting Ejectors |
JUN 1975 |
|
| Authors:
Hermann Viets; AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OH
|
| An overview of ejectors as thrust augmentors is presented including the motivation for and operation of thrust augmenting ejectors. Background studies involving jet mixing and diffusion studies are included as well as the state of the art in unsteady jet interactions. Examples of V/STOL aircraft designs incorporating thrust augmenting ejectors are shown and their advantages discussed. |
|
| Wind and Turbulence Information for Vertical and Short Take-Off and Landing (V/STOL) Operations in Built-Up Urban Areas - Results of Meteorological Survey |
JUN 1975 |
423 pages |
| Authors:
J. V. Ramsdell; BATTELLE PACIFIC NORTHWEST LABS RICHLAND WA ATMOSPHERIC SCIENCES DEPT
|
| Winds and turbulence have been measured at typical urban STOL and VTOL port sites and at a conventional rural airport during a 9-month period. These measurements have been used to develop a set of turbulence models for use in: design of V/STOL aircraft stability and control features, development of airworthiness criteria for certification of V/STOL aircraft, and simulation of the turbulence in the urban terminal environment of V/STOL aircraft. The ... |
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| Mixing Duct Pressure Distributions and Exhaust Flow Characteristics of a High Temperature and Pressure Cylindrical Ejector. |
JUN 1975 |
|
| Authors:
Brian Quinn; Howard L. Toms; AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO
|
| The thermodynamic and mixing characteristics of a family of inlet area ratio 26 ejectors have been measured across a range of primary reservoir pressures (0 to 80 psig) and temperatures (65 to 1000 degrees F). The length-to-duct diameter ratio of the ejectors was the family parameter and varied from 12.36 to 3.46. The distribution of pressure along the wall of the mixing duct clearly identified up to three distinct modes ... |
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| V/STOL Aircraft Noise Prediction (Jet Propulsors). |
JUN 1975 |
327 pages |
| Authors:
N. N. Reddy; D. F. Blakney; J. G. Tibbets; J. S. Gibson; LOCKHEED-GEORGIA CO MARIETTA
|
| A computer program is presented for predicting the noise levels of V/STOL aircraft with jet-propulsive-lift systems. Using the equations developed in Part I of this report the noise levels may also be estimated with hand calculations. Vectored thrust, externally blown flap, upper surface blown flap, internally blown flap, and augmentor wing are the propulsive-lift concepts considered. Semi-empirical equations are derived using the test results and theories for the following aircraft ... |
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| Methods for Aircraft State and Parameter Identification |
MAY 1975 |
|
| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)
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| Twenty-nine papers and comments are contained in these Proceedings. Several discuss and compare results obtained with different parameter identification techniques applied to specific fighter aircraft at high angles of attack, subsonic and supersonic transports, VTOL and STOL aircraft, and helicopters. Special problem areas such as systems modelling with high internally-generated fluctuations, aircraft state estimation in non-steady flight and parameter identification for non-linear aerodynamic regimes are covered. The sessions at the ... |
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| A STOL Airworthiness Investigation Using Simulations of Representative STOL Aircraft. |
MAY 1975 |
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| Authors:
Robert Rumold; John M. Lehman; Robert L. Stapleford; Charles S. Hynes; Barry C. Scott; SYSTEMS TECHNOLOGY INC MOUNTAIN VIEW CALIF
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| A simulator study of STOL airworthiness criteria for approach and landing was conducted using a series of different aircraft models. These models were selected to isolate a single parameter or characteristic for evaluation. Specific areas included in the study were: an evaluation of speed margins, a flight path margin evaluation, a study of flare and landing technique, the effects of touchdown zone constraints, an evaluation of two different turbulence models, ... |
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V/STOL
