SIDESLIP - Storming Media

Computational Fluid Dynamics Study for a Deep Stall Air Vehicle

31 MAY 2011

21 pages

Authors: Ravi Ramamurti; NAVAL RESEARCH LAB WASHINGTON DC CENTER FOR REACTIVE FLOW AND DYNAMICAL SYSTEMS

The full text of this report is available for sale.

The aerodynamic characteristics of a vehicle in deep-stall conditions are investigated and the motion of the vehicle is predicted in a self-consistent manner. Three-dimensional unsteady computations of the complete aircraft with prescribed control surface deflections are carried out. Both steady and unsteady flow simulations are performed to map out the lift, drag, and moment as a function of various flight and control surface parameters. The unsteady forces and moments were ...

Verification of Simulation Results Using Scale Model Flight Test Trajectories

MAY 2004

66 pages

Authors: Jeff Obermark; ARMY AVIATION AND MISSILE COMMAND REDSTONE ARSENAL AL MISSILE RESEARCH DEVELOPMENT AND ENGINEERING CENTER

The objective of this effort was to compare limited amounts of scale model trajectory data with appropriate full-scale data. The scale model data was scaled up to equivalent full-scale conditions. Two Degree-of-Freedom (2-DOF) trajectories and calculated miss-distances were compared to full-scale data. Likely error sources in the scale test process were identified. Simulation was used to estimate the effects of these errors on the trajectory. Simulation trends were used to ...

Model of Unsteady Aerodynamic Coefficients of a Delta Wing Aircraft at High Angles of Attack

MAR 2003

13 pages

Authors: L. Planckaert; OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AERONOSPATIALES CEDEX FRANCE SYSTEMS CONTROL/FLIGHT DYNAMICS

Studies on the subject of near-stall or post-stall flight have a direct impact on the evaluation of flight safety, on performance in terms of landing distance, and on increases in maneuverability. For several years, new flow control concepts have been studied, and some of them have proven effective in overcoming the difficulties (e.g., loss of control in yaw, asymmetry of forebody, roll instability) involving flight at high angles of attack. ...

In-Flight Flow Visualization Results of the F-106B with a Vortex Flap

MAR 2003

35 pages

Authors: Jay M. Brandon; James B. Hallissy; Philip W. Brown; John E. Lamar; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER

Surface and off-surface flow visualization techniques were used to visualize the three-dimensional vortex flows on the F-106 aircraft with vortex flaps installed. Results at angles of attack between 9 degrees and 18 degrees and Mach numbers from 0.3 to 0.9 are presented. A smoke flow vapor screen technique was used to document leading-edge vortex paths and sizes, while an oil flow technique was employed to provide detailed information on reattachment ...

Precision Air Data Support for Chem/Bio Attack Response

MAR 2003

122 pages

Authors: Kwang L. Tan; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

The defense response against chemical and biological (Chem/bio) weapons has gained a renewed focus in light of the September 11, 2001 terrorist attack. A successful response to a Chem/bio attack would involve measuring and predicting the dispersion of a toxic cloud in the atmosphere. The Naval Postgraduate School Aeronautics and Astronautics Department is working together with the Meteorology Department on a technique to make toxic cloud measurements using an Unmanned ...

Motion Effects on Leading-Edge Vortex Behavior over Delta Wings and Generalized Modeling

MAR 2003

23 pages

Authors: X. Z. Huang; E. S. Hanff; NATIONAL RESEARCH COUNCIL OF CANADA OTTAWA (ONTARIO) INST FOR AEROSPACE RESEARCH

Effects of static attitude and three different motions on vortex behavior and its breakdown over delta wings were investigated. These motions include the following: (1) harmonic oscillation or ramp-and-hold motion in roll at constant resultant angle of attack, (2) harmonic oscillation or ramp-and-hold in pitch, and (3) coning at constant resultant angle of attack. A basic 65 degree delta wing configuration was tested in two wind tunnels as well as ...

A Wind Tunnel Investigation of a Small-Scale Tiltrotor Model in Descending Flight

JAN 2002

7 pages

Authors: Anita I. Abrego; Kurtis R. Long; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER

A small-scale tiltrotor model was tested in the 7- by 10-foot Wind Tunnel at NASA Ames Research Center, with the goal of better understanding Vortex Ring State (VRS) effects on tiltrotor aircraft. Test objectives were to obtain performance data of a tiltrotor model over a wide range of descent conditions, to explore the effects of sideslip at these descent conditions, and to investigate the validity of using a single-rotor with ...

A Methodology to Predict the Empennage In-Flight Loads of a General Aviation Aircraft Using Backpropagation Neural Networks

FEB 2001

44 pages

Authors: David Kim; Maciej Marciniak; EMBRY-RIDDLE AERONAUTICAL UNIV DAYTONA BEACH FL

Back propagation neural networks were used to predict strains resulting from maneuver loads in the empennage structure of a Cessna l72P. The purpose of this research was to develop a methodology for the prediction of strains in the tail section of a general aviation aircraft that would not require installation of strain gages and to determine the minimum set of sensors necessary for a prediction suitable for small aircraft. This ...

Application of Negative Scarf to Inlet Design for Acoustic Reduction, Aerodynamic Assessment at Subsonic and Transonic Speeds

SEP 2000

14 pages

Authors: R. K. Nangia; M. E. Palmer; NANGIA AERO RESEARCH ASSOCIATES BRISTOL (UNITED KINGDOM)

Aircraft engines must meet current and future FAR regulations and noise "footprint" criteria. A way of reducing noise is to use negatively scarfed inlets. The extended lower lip acts as an acoustic "barrier." We need to understand the aerodynamic implications of inlet scarfing at low and transonic speeds. The subsonic aerodynamic performance (incidence, side-slip, and ground effects) of a conventional (+6 degree scarf) inlet has been assessed. A range of ...

Simulation and Analysis of Wing Rock Physics for a Generic Fighter Model with Three Degrees-of-Freedom

JUL 2000

115 pages

Authors: Ahmed A. Saad; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT

Modern fighter designs have been associated with lateral self-excited oscillations own as "Wing Rock". Simulations of wing rock by flow visualization utilities have been encouraged to develop a complete understanding of the fluid mechanism that drives fl%e motion as well as for prediction purposes. Previous windiwater tunnel simulations have been limited to a single degree-ofifreedom (DoF) in roll. In this study, for the first time, wing rock is computationally simulated ...

Pressure Measurements on a Proposed Optical Window Fairing for the AltusII Unmanned Air Vehicle

SEP 1999

84 pages

Authors: Scott C. Ferris; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Low-speed wind tunnel tests were conducted to determine surface pressure measurements on a proposed aerodynamic fairing for the Altus II UAV. These tests were conducted at various angle-of-attack and sideslip positions to determine the effect on the surface pressures for the optical window portion of the fairing. Of particular interests were the pressure contour field located over the optical window region and the total force ...

Prediction of Antisymmetric Buffet Loads on Horizontal Stabilizers in Massively Separated Flows, Phase II

MAY 1999

146 pages

Authors: Saeed Farokhi; Saeid Mirsafian; Tom Sherwood; Mark Ewing; AEROTECH ENGINEERING AND RESEARCH LAWRENCE KS

The Federal Aviation Administration (FAA) has a continuing program to collect data and develop predictive methods for aircraft flight loads. Some of the most severe and potentially catastrophic flight loads are produced by separated flows. Structural response to the aerodynamic excitation produced by separated flows is defined as buffeting. A low-cost technique for the prediction of full-scale buffet loads on horizontal stabilizers of aircraft is described. A 1/13-scale rigid generic ...

Effect of Sideslip on the Flow over a 65-deg Delta Wing

JAN 1999

61 pages

Authors: Nicolaas G. Verhaagen; DELFT UNIV OF TECHNOLOGY (NETHERLANDS)DEPT OF AEROSPACE ENGINEERING

Flow-visualization tests, surface-pressure measurements and balance tests were conducted on a model of a flat-plate 65-deg swept delta wing in a low-speed wind tunnel. The model was tested at a fixed angle of attack of 30 deg and at angles of sideslip up to 20 deg. The tests generated data that were used to study the effect of sideslip on the flow over the delta wing. ...

Development of Non-Linear, Low-Speed Aerodynamic Modelforthe F-16/Vista

AUG 1997

14 pages

Authors: Jacob Kay; John N. Ralston; Stanley F. Lash; WRIGHT LAB WRIGHT-PATTERSON AFB OH FLIGHT DYNAMICS DIRECTORATE

A NEW LOW-SPEED AERODYNAMIC DATABASE FOR THE F-16/VISTA WAS DEVELOPED FROM LOW-SPEED DATA SETS OBTAINED FROM NASA LANGLEY'S FACILITIES. THIS NEW MODEL WAS DESIGNED TO BE CONTINUOUS FROM -80 DEGREES TO +90 DEGREES ANGLE OF ATTACK, - 30 DEGREES TO +30 DEGREES OF SIDESLIP, AND TO INCORPORATE ALL SIDESLIP AND CONTROL EFFECTIVENESS INTERACTIONS IN A FULLY NON-LINEAR STRUCTURE. THIS PAPER FIRST REVIEWS THE MODEL STRUCTURE AND DOCUMENTS THE AERODYNAMIC DATA ...

Innovative Control Effectors (ICE) Phase III

AUG 1997

420 pages

Authors: Kenneth M. Dorsett; Scott P. Fears; Heather P. Houlden; LOCKHEED MARTIN TACTICAL AIRCRAFT SYSTEMS FORT WORTH TX

This report describes the Phase 2 portion of a joint U.S. Air Force U.S. Navy sponsored investigation of innovative aerodynamic control concepts for fighter aircraft without vertical tails. The Phase 1 work consisted of effector performance prediction, vehicle integration assessment, and transition studies for numerous control effector concepts. The Phase 2 effort is an extension of the Phase 1 work and consists mainly of three wind tunnel tests to acquire ...

Gyrodynamic Effects of an Energy Storage Flywheel on the Handling of a Hybrid-Electric Vehicle

09 JAN 97

145 pages

Authors: James L. Greer; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

This research presents the results of numerical simulation of the handling characteristics of a hybrid-electric vehicle which uses a flywheel for temporary energy storage. The work is presented in an effort to understand the potential interaction of the flywheel and the vehicle, and to predict what positive and negative outcomes may result. The vehicle is modeled with four wheels, and the roll, yaw, and sideslip-angle degrees of freedom. The simulation ...

Roll Angle and Ball Width Data Method Based on Dynamic Pressure for Helicopter Applications

27 SEP 96

35 pages

Authors: Herman Kolwey; NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD

A search of MH-53E and CH-53E roll angle, ball width, and sideslip data was conducted in order to establish Fleet steady heading sideslip (SHSS) NATOPS limits for aircraft lacking nose booms. No ball width data were found for the CH-53H. Plots of the available information were sent to NAVTESTPILOTSCH (Bob Miller). He suggested that the data (three different slopes) might be normalized to one slope, using a velocity squared ratio ...

Simulation Support of a 17.5% Scale F/A-18E/F Remotely Piloted Vehicle

30 MAY 96

10 pages

Authors: Timothy R. Fitzgerald; David R. Gingras; NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD

As defense budgets continue to shrink, cost-effective methods for the accurate and timely acquisition of aerodynamic data must be developed. Traditionally, wind tunnels have fulfilled this role at both the conceptual and developmental stages, as well as throughout the service life of an aircraft. However, although wind tunnels are a trusted and valuable data source that provide consistent repeatable data upon which to construct aerodynamic models, they also have inherent ...

Simulation Support of a 17.5 percent Scale F/A-18E/F Remotely Piloted Vehicle

27 FEB 96

2 pages

Authors: Timothy R. Fitzgerald; NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD

As defense budgets continue to shrink, cost-effective methods for the accurate and timely acquisition of aerodynamic data must be developed. Traditionally, wind tunnels have fulfilled this role at both the conceptual and developmental stages, as well as, throughout the service life of an aircraft. However, although wind tunnels are a trusted and valuable data source that provide consistent, repeatable data upon which to construct aerodynamic models, they also have inherent ...

Development of Lateral-Directional Transfer Functions for Class IV aircraft with Level 1 Flying Qualities

DEC 95

64 pages

Authors: Julieta E. Booz; NAVAL AIR WARFARE CENTER AIRCRAFT DIV WARMINSTER PA

This report describes the computer program that was developed to support the effort currently being conducted at C. S. Draper Laboratory, Inc. to develop a hybrid, learning augmented, lateral-directional flight control system. The output from the computer program is a set of transfer functions for trimmed flight conditions which can be used to describe representative F-18 time histories. The transfer functions meet the Level 1 Flying Qualities Requirements of MlL-F8785C ...

Estimation of Aerodynamic Load Distributions on the F/A-18 Aircraft Using a CFD Panel Code

MAR 95

Authors: H. A. Quick; DEFENCE SCIENCE AND TECHNOLOGY ORGANIZATION CANBERRA (AUSTRALIA)

The full text of this report is not available and therefore is not for sale. This information is provided for reference purposes only.

The computational fluid dynamics panel method code VSAERO has been used to estimate the aerodynamic load distributions on the stabilators, fins and aft fuselage of the F/A-18 aircraft for steady sideslip and steady roll conditions. Three separate VSAERO models have been developed to obtain results for these conditions. These are a symmetric F/A-18 model, a starboard fin model and a starboard stabilator and fin model. Difficulties in modelling the vortices ...

The Investigation of the Influence of Parameter (M Infinity)/(Square Root of Re) on the Aerodynamic Characteristics of a Body of Revolution with the Generatrix Break at Hypersonic Velocities

05 DEC 94

168 pages

Authors: V. I. Plyashechnik; CENTRAL AERODYNAMIC INST MOSCOW (RUSSIA)

This report contains the results of testing a body of revolution featuring the contour generatrix break in the wind tunnel T-121 of TsAGI. The test model is a body of revolution having an ogive nose, a central cylindrical body and an aft conical 'skirt' with a generatrix angle of theta=6.5 deg. The tests of the aerodynamic characteristics of the model (balance tests) were performed using an external three-component strain-gage balance ...

Effect of Juncture Fillets on Double-Delta Wings Undergoing Sideslip at High Angles of Attack

SEP 94

216 pages

Authors: Wen-Huan Chang; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

A flow visualization study of the vortical flow over a baseline double-delta wing model and a diamond-fillet double-delta wing model both with sharp leading edges was conducted in the Naval Postgraduate School water tunnel using the dye-injection technique. The main focus of this study was to observe the effect of juncture fillet on the vortex core trajectory, and vortex burst location on the wing surface at high angles of attack ...

Pressure Measurements on an F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 1. Wind Tunnel Test Summary

31 AUG 94

105 pages

Authors: Chris Pettit; Michael Banford; Dansen Brown; Ed Pendleton; WRIGHT LAB WRIGHT-PATTERSON AFB OH

Buffeting pressure measurements were made on the vertical tail surface of a full scale F/A-18 aircraft model in the National Full Scale Aerodynamics Complex at NASA Ames Research Center. Test variables included aircraft angle-of-attack, aircraft sideslip angle, and dynamic pressure. Accelerometers were used to obtain vertical tail accelerations. Pressure transducers were mounted on the starboard vertical tail. Steady and unsteady pressures were obtained. Unsteady pressure data were reduced to PSD ...

Pressure Measurements on an F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 2: Steady and Unsteady RMS Pressure Data

01 AUG 94

383 pages

Authors: Chris Pettit; Dansen Brown; Michael Banford; Ed Pendleton; WRIGHT LAB WRIGHT-PATTERSON AFB OH

Buffeting pressure measurements were made on the vertical tail surface of a full scale F/A- 18 aircraft model in the National Full Scale Aerodynamics Complex at NASA Ames Research Center. Test variables included aircraft angle-of-attack, aircraft sideslip angle, and dynamic pressure. Accelerometers were used to obtain vertical tail accelerations. Pressure transducers were mounted on the starboard vertical tail. Steady and unsteady pressures were obtained. Unsteady pressure data were reduced to ...

Pressure Measurements on an F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 3. Buffet Power Spectral Densities

AUG 94

705 pages

Authors: Chris Pettit; Dansen Brown; Michael Banford; Ed Pendleton; WRIGHT LAB WRIGHT-PATTERSON AFB OH

Pressure Measurements on An F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 4. Buffet Cross Spectral Densities. Part 1

AUG 94

695 pages

Authors: Chris Pettit; Dansen Brown; Michael Banford; Ed Pendleton; WRIGHT LAB WRIGHT-PATTERSON AFB OH

Interaction, Bursting and Control of Vortices of A Cropped Double-Delta Wing at High Angle of Attack

MAR 94

224 pages

Authors: Abdullah M. Alkhozam; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

A flow visualization study of the vortical flow over a cropped double-delta wing model with sharp leading edges and its three derivatives with small geometric modifications (fillets) at the strake wing junction was conducted in the Naval Postgraduate School water tunnel using the dye-injection technique. The fillets increased the wing area of the baseline model by 1%. The main focus of this study was to evaluate the effect of fillets ...

Hydrodynamic Flowfield Visualization Studies of a Mach 6 Waverider

MAR 94

172 pages

Authors: Lowell M. Johnson; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Flowfield visualization studies of a conical flow derived waverider were conducted in the Naval Postgraduate School water tunnel facility, as part of an ongoing study by the Naval Postgraduate School and the NASA Ames Research Center. The model, with an 8 inch root chord, 7.5 inch span and an aspect ratio of 1.41, was designed and constructed with an integrated forebody engine inlet ramp system and cowling for a hydrocarbon ...

Lateral-Directional, Full Envelope Control Law Design for F-16 with Thrust Vectoring

12 pages

Authors: William C. Reigelsperger; Kelly D. Hammett; Siva S. Banda; WRIGHT LAB WRIGHT-PATTERSON AFB OH

A manual flight control system for the lateral directional dynamics of a modern fighter aircraft incorporating thrust vectoring is presented. Design goals are posed in terms of maintaining acceptable flying qualities during high alpha maneuvering while also achieving robustness to model parameter variations and unmodeled dynamics over the entire flight envelope. The need for gain scheduling is eliminated by using an inner loop dynamic inversion/outer loop structured singular value (u) ...

Design of a Flight Controller for an Unmanned Research Vehicle with Control Surface Failures Using Quantitative Feedback Theory

DEC 93

163 pages

Authors: Mark S. Keating; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

This thesis describes the application of the multiple-input multiple- output (MIMO) Quantitative Feedback Theory (QFT) design technique to the design of a digital flight control system for the Lambda Unmanned Research Vehicle (URV). The QFT technique allows the synthesis of a control system which is robust in the presence of structured plant uncertainties. Uncertainties considered in this design are the aircraft's plant variation within the flight envelope and the effects ...

Low-Speed Pressure Distribution Measurements Over the Aft-Fuselage, Fins and Stabilators of a 1/9th Scale F/A-18 Wind-Tunnel Model

OCT 93

93 pages

Authors: L. D. MacLaren; H. A. Quick; AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)

The steady-state aerodynamic pressure distribution over the aft fuselage, fin and stabilator of a 119th scale FIA-18 model has been measured for varying conditions at low speeds. Pressure distributions are presented in the form of a parametric study and the integration of the pressures to obtain total loads is included to indicate the overall effects of angle of attack, sideslip, stabilator deflection and the LEX fence. The results from these ...

The Crossflow Separation of a Submarine Configuration in a Turning Maneuver

01 SEP 93

46 pages

Authors: Todd G. Wetzel; Roger L. Simpson; VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG DEPT OF AEROSPACE AND OCE AN ENGINEERING

The crossflow separation on a submarine configuration was studied. Forces and moments were taken for the submarine body alone, the body plus the sail, the body plus tail appendages, and the body with both a sail and tail appendages. Forces and moments were taken at sideslip angles from 0 deg to 15 deg. Oil flows were done for the body alone for sideslip angles of up to 20 deg. Boundary ...

Experimental Study of Vortex and Aerodynamic Characteristics of Stack Wings with Sideslip

20 JUL 93

15 pages

Authors: Bao Guohua; FOREIGN AEROSPACE SCIENCE AND TECHNOLOGY CENTER WRIGHT- PATTERSON AFB OH

This paper reports on an experimental study of stack wings with small aspect ratio, and describes the variation of detached vortex system at the aircraft wing leading edge with different aspect ratios. The influence on aerodynamic characteristics due to vortex twisting and bursting is analyzed. As revealed in the study, sideslip delays the vortex twisting at the upstream side of the aircraft wing. The vortex bursts early. At the downward ...

Computation of a Delta-Wing Roll-and-Hold Maneuver

12 FEB 93

46 pages

Authors: Raymond E. Gordnier; Miguel Visbal; WRIGHT LAB WRIGHT-PATTERSON AFB OH

This report presents computations of the flowfield around an 80 degree sweep delta wing undergoing a constant roll-rate maneuver from 0 to 45 degrees. The governing equations for the problem are the unsteady, three- dimensional Navier-Stokes equations. The equations are solved using the implicit, approximately-factored algorithm of Beam-Warming. Fixed roll angle results are also presented and compared with experimental measurements to demonstrate the ability of the numerical technique to accurately ...

Volume II. Flying Qualities Flight Test. Chapter 11: Engine-Out Theory

AUG 92

54 pages

Authors: AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA

This chapter examines the problems associated with an engine failure and how engine out flight testing is accomplished. The discussion will begin with performance issues, how engine loss affects the takeoff and initial climb segments. Next, the equations of motion are introduced, modified for an engine failure. They are used to show how minimum control speeds are determined by design. Finally, flight test techniques are introduced for the evaluation of ...

Vortex Flow Visualization Using Colored and Fluorescent Dyes on Flat Plate Delta Wing with Leading Edge Extension

MAY 92

22 pages

Authors: Scott P. LeMay; WRIGHT LAB WRIGHT-PATTERSON AFB OH

A water tunnel study was conducted in the Wright Laboratory 2ft x 2ft water tunnel to examine the vortex flowfield about a 60 deg flat plate diamond delta wing with an 80 deg leading edge extension (LEX). Flood light illuminated colored dye and laser light sheet illuminated fluorescent dye were used to visualize light sheet illuminated fluorescent dye were used to visualize the wing and LEX vortex core trajectories and ...

Effect of Canard Oscillations on the Vortical Flowfield of a X-31A-Like Fighter Aircraft Model

MAR 92

128 pages

Authors: D-Ming Liu; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

A flow visualization investigation was carried out in the Naval Postgraduate School water tunnel using dye injection technique to study the effects of oscillating a close-coupled canard on a 2.3% scale modal of a X-3 1A- Us fighter This investigation focussed primarily on the effects of canard oscillations on the breakdown characteristics of the wing root vortex for both static and dynamic conditions of the model at zero sideslip angle. ...

Flight Testing of a Half-Scale Remotely Piloted Vehicle

MAR 92

62 pages

Authors: Paul A. Koch; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Flight testing of a half-scale Pioneer remotely piloted vehicle was conducted to determine the longitudinal static stability flying qualities. A pulsewidth modulated telemetry system was used to provide data on control surface deflections, angle of attack, sideslip angle and airspeed. From the testing, the neutral point was determined to be 41.2% of mean aerodynamic chord, which was within l3% of theoretical predictions. On a subsequent flight, the Pioneer experienced electromagnetic ...

Development of Telemetry for the Agility Flight Test of a Radio Controlled Fighter Model

MAR 92

90 pages

Authors: Michael J. Gallagher; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Advanced design tools, control devices, and supermaneuverability concepts provide innovative solutions to traditional aircraft design trade-offs. Emerging technologies enable improved agility throughout the performance envelope. Unmanned Air Vehicles provide an excellent platform for dynamic measurements and agility research. A 1/8-scaled F-16A ducted-fan radio- controlled aircraft was instrumented with a telemetry system to acquire angle of attack, sideslip angle, control surface deflection, throttle position, and airspeed data. A portable ground station ...

Flow Visualization Studies of a Sideslipping, Canard-Configured X-31A- Like Fighter Aircraft Model

DEC 91

125 pages

Authors: Chang H. Kim; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

A water tunnel flow visualization investigation was performed to study the vortex development and bursting phenomena on a 2.3% scale model of a X-31A-Like fighter aircraft. The main focus of this study was two-fold: First, to study the effects of angle of attack and static sideslip on the model vortical flow field. Secondly, to study the effects of dynamic sideslip motion at two reduced yaw rates. Results indicate that the ...

Investigation of the Influence of Rotary Aerodynamics on the Study of High Angle of Attack Dynamics of the F-15B Using Bifurcation Analysis

DEC 91

167 pages

Authors: Ralph D. Fero; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

The purpose of this research was to use bifurcation analysis to investigate the effectiveness of rotary balance data in the prediction of aircraft spin behavior as both a stand alone representation of a model's aerodynamic data and in a conventional hybrid model. using the foundation of a previously developed model of the F-15B, the rotary balance aerodynamic force and moment data were implemented as a function of angle of attack, ...

Flight Test to Determine Feasibility of a Proposed Airborne Wake Vortex Detection Concept

APR 91

41 pages

Authors: James R. Branstetter; E. C. Hastings Jr.; James C. Patterson Jr; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

An investigation was conducted jointly by the FAA and NASA to determine the radial extent of the circulatory flow field around the lift- induced vortex system of an aircraft in flight. This flow field, if found to be of sufficient strength and span to activate instrumentation onboard a following aircraft, may provide the basis for designing a feasible airborne wake detection and avoidance system. A small probe aircraft was flown ...

Computation of Inlet Reference Plane Flow-Field for a Subscale Free-Jet Forebody/Inlet Model and Comparison to Experimental Data

FEB 91

77 pages

Authors: M. D. McClure; J. R. Sirbaugh; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

The computational fluid dynamics (CFD) computer code PARC3D was used to predict the inlet reference plane (IRP) flow field for a side-mounted inlet and forebody simulator in a free jet for five different flow conditions. The calculations were performed for free-jet conditions, mass flow rates, and inlet configurations that matched the free-jet test conditions. In addition, viscous terms were included in the main flow so that the viscous free-jet shear ...

Dynamic Analysis of a Combat Aircraft with Control Surface Failure

NOV 90

133 pages

Authors: Marc Roy; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

An investigation was performed to analyze the dynamic stability characteristic of an aircraft which has sustained damage to a primary control surface. The analysis was performed using the existing functional form of actual wind tunnel data taken on an F-16 model. Two control schemes are used for trimming an F-16 that has sustained damage to its rudder. The first control scheme represent the basic aircraft, while the second allowed the ...

Volume II. Flying Qualities Phase. Chapter 7: Lateral-Directional Static Stability

OCT 90

108 pages

Authors: AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA

Your study of flying qualities to date has been concerned with the stability of the airplane flying in equilibrium on symmetrical flight paths. More specifically, you have been concerned with the problem of providing control over the airplane's angle of attack and thereby its lift coefficient, and with ensuring static stability of this angle of attack. This course considers the characteristics of the airplane when its flight path no longer ...

Developmental Flight Testing of a Half Scale Unmanned Air Vehicle

SEP 90

61 pages

Authors: James D. Salmons; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

This thesis sought to perform developmental flight testing of a half- scale unmanned air vehicle. To do this the half scale version of the Pioneer (used by the US Marine Corps for training) was chosen as the airframe to instrument because of problems that the Unmanned Air Vehicle Office at the Pacific Missile Test Center had identified in the full scale version of the Pioneer. Problems included: (1) discrepancies in ...

Development of an Unmanned Air Research Vehicle for Supermaneuverability Studies

29 MAR 90

53 pages

Authors: Christopher M. Cleaver; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

With the advent of all-aspect missiles and highly maneuverable threat aircraft, maintaining air superiority in the future will require innovative solutions to current aerodynamic and propulsive limitations. Unmanned Air Vehicles (UAV's) provide an excellent experimental alternative for supermaneuverability investigations, providing dynamic flight measurements not available in wind tunnels. A 1/8 geometrically scaled F-16A was constructed and test flown in order to provide a proven, highly maneuverable of airspeed, angle of ...

The Measurement, Modeling and Prediction of Traction for Rocket Propellant 1

OCT 89

72 pages

Authors: Joseph L. Tevaarwerk; METALS AND CERAMICS INFORMATION CENTER COLUMBUS OH

The bearings used in rocket motor turbopumps are lubricated with the process liquid, no matter whether this is a mineral-based low-viscosity fuel such as RP1, or a cryogenic substance. Thus it is critically important that the rheological properties of the working fluid be known and modeled. Traction tests were performed on RP1, a common kerosene based rocket propellant. Traction data on this fluid are required for purposes of turbopump bearing ...

Aerodynamic Analysis of a U.S. Navy and Marine Corps Unmanned Air Vehicle

JUN 89

204 pages

Authors: Daniel F. Lyons; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

An aerodynamic analysis was performed on a U.S. Navy and Marine Corps Unmanned Air Vehicle (UAV) called PIONEER. A low-order panel method called PMARC (Panel Method Ames Research Center) was used to obtain various aerodynamic parameters and to evaluate the longitudinal and directional stability and control of the vehicle. In addition, a drag analysis of the vehicle was performed using techniques described in Fluid Dynamic Drag by Hoerner. Drag reduction ...