| EXPLOSIVES FOR SUPERSONIC MUNITIONS. |
OCT 1966 |
|
| Authors:
Donald A. Pitt; MINNESOTA MINING AND MFG CO ST PAUL
|
 | Two candidate explosives and their formulations with fuel ingredients have been compared to TNT for performance in the temperature range from -65 F. to the stagnation temperature expected on supersonic aircraft. Physical property data on preferred formulations are presented, with recommendations on their utility in the proposed application. (Author) |
|
| COMPILATION OF DATA ON CREW EMERGENCY ESCAPE SYSTEMS |
SEP 1966 |
|
| Authors:
John O. Bull; Edward L. Serocki; Howard L. McDowell; BOEING CO RENTON WA
|
| A comprehensive group of appropriate open ejection seats, encapsulated ejection seats, cockpit pod capsules, separable nose capsules, and subsystems are described. The descriptions provide information on items such as initiation, crew positioning and restraint, emergency pressurization and oxygen, seat-man separation, capsule separation, rocket motors, rocket catapults, stabilization, deceleration, recovery parachute, landing impact attenuation, flotation, location aids, and survival equipment or provisions. Information is also provided on escape system performance, tests, ... |
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| INVESTIGATION OF SUPERSONIC AIRCRAFT FUEL TANK FIRE AND EXPLOSION HAZARDS. |
SEP 1966 |
|
| Authors:
H. Dwight Fisher; Harold G. Weiss; DYNAMIC SCIENCE MONROVIA CA
|
| The problems associated with flight fires in supersonic transport aircraft include most of the factors present in conventional aircraft as well as some additional problems caused in part by the high temperatures produced by supersonic flight and new design concepts. The possibility that the major fuel storage areas may be in the fuselage poses probelms different from those associated with conventional wing tanks. This study constists of a laboratory investigation ... |
|
| STABILITY AND CONTROL. PART 2. |
Sep-1966 |
|
| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT PARIS (FRANCE)
|
| The subjects covered include the following: dynamic motions of aircraft; general handling, including handling criteria; auto-stability and control; derivative determination in flight and in wind tunnels; simulated handling assessments including the range of validity; pilot behaviour; special problems of stalling, super-stalling and T-tail configurations; handling during approach and landing, and auto-land systems; special problems of rough air, instrument flying and supersonic operation. (Author) |
|
| SRI PARTICIPATION IN VOLTAGE BREAKDOWN AND ROCKET CHARGING EXPERIMENTS ON NIKE-CAJUN ROCKET AFCRL AD 6.841. |
AUG 1966 |
|
| Authors:
Joseph E. Nanevicz; John B. Chown; Edward F. Vance; James A. Martin; STANFORD RESEARCH INST MENLO PARK CALIF
|
| Results of antenna voltage breakdown and rocket charging experiments on the supersonic flight of Nike-Cajun Rocket AD 6-841 are presented. Rocket altitudes up to 340,000 feet and rocket velocities up to 5000 feet per second were obtained. Flight-test measurements of the voltage breakdown of a VHF quadra-loop antenna and an X-band slot antenna are compared to static laboratory measurements. Modification of antenna breakdown characteristics by local aerodynamic effects and other ... |
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| CIRCULAR-ARC JET FLAPS AT SUPERSONIC SPEEDS - TWO DIMENSIONAL THEORY, |
JUL 1966 |
|
| Authors:
James L. Amick; MICHIGAN UNIV ANN ARBOR OFFICE OF RESEARCH ADMINISTRATION
|
| An inviscid theory of jet-flap interaction is developed for a two-dimensional jet which issues from a curved nozzle and follows a circular-arc path such that the centrifugal force is in equilibrium with the pressure difference between a high pressure separated flow region along the upstream edge of the jet and a low pressure (base pressure) region along the downstream edge. The theory is based on empirical relations for the pressure ... |
|
| FLUID FLOW AND HEAT TRANSFER IN HIGH-TEMPERATURE POROUS MATRICES FOR TRANSPIRATION COOLING. |
MAY 1966 |
|
| Authors:
J. C. Y. Koh; E. P. del Casal; R. W. Evans; V. Deriugin; BOEING AEROSPACE CO SEATTLE WA
|
| A detailed study of fluid flow and heat transfer characteristics in porous matrices has been performed. Refined prediction methods for pressure and temperature distribution in porous matrices have been developed to include the effects of gas conduction, internal heat sources, chemical reaction, non-steady state flows and slip flow. The show system feasibility, a high-temperature multilayer matrix system has been developed. Six specimens, one inch in diameter, were fabricated and tested ... |
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| AN AERODYNAMIC MODEL FOR A LOW-ALTITUDE ROCKET EXHAUST PLUME. |
25 APR 1966 |
|
| Authors:
Richard Shao-lin Lee; W. W. Balwanz; NAVAL RESEARCH LAB WASHINGTON DC
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| An aerodynamic model is proposed for the exhaust plume issuing from a rocket nozzle exit into quiescent ambient air in which chemical reaction or two-phase flow does not predominate. The model is based on the presently available knowledge and established aerodynamic principles for the various flow regimes involved. The major assumptions made are individually substantiated and justified by experimental evidence in existing literature. A theoretical analysis is carried over the ... |
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| TURBOFAN ENGINES-THEIR PRESENT AND FUTURE. |
18 APR 1966 |
|
| Authors:
V. Starostin; AEROSPACE TECHNOLOGY DIV LIBRARY OF CONGRESS WASHINGTON D C
|
| The article describes a way of making turbofan engines by the use of well-designed turbojet engines and discusses the efficiency of such a conversion. The use of an afterburner in a turbofan engine, permitting the use of these engines at high supersonic flight speeds, is also discussed. The author cites specific English and American aircraft now using turbofan engines. A diagram of the X353-5 turbofan engine with a high by-pass ... |
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| AIRCRAFT-INDUCED IONOSPHERIC DISTURBANCES. |
APR 1966 |
|
| Authors:
Frank A. Marcos; AIR FORCE CAMBRIDGE RESEARCH LABS L G HANSCOM FIELD MASS
|
| Experiments were conducted to determine whether acoustic waves could propagate from the lower atmosphere into the ionosphere and be detected by hf radio waves. A supersonic aircraft was flown on a trajectory designed to focus the shock wave energy, generated over a long flight path, into a relatively small region of the daytime E-layer which was being probed by a phase path vertical sounder. Three series of tests, consisting of ... |
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| SONIC BOOM |
FEB 1966 |
46 pages |
| Authors:
WEATHER WING (6TH) WASHINGTON DC
|
 | Because there are important meteorological effects on shock wave propagation, weather officers should become acquainted with some of the terminology and the physical principles of weather effects on sonic boom propagation. Calculation of shock wave patterns covering many square miles is an exceedingly complex operation which involves several parameters other than weather data. Sonic booms caused by either aircraft or missiles are influenced by size, shape, speed, trajectory, etc. The ... |
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| INVESTIGATION OF FIRE EXTINGUISHING SYSTEM REQUIREMENTS FOR ADVANCED FLIGHT VEHICLES. |
JAN 1966 |
|
| Authors:
Herbert Landesman; Eugene B. Klusmann; John Minich; Gorm Christiansen; NATIONAL ENGINEERING SCIENCE CO PASADENA CA
|
| Data are presented defining thermal stability limits for model structures of fluorinated chloro- and bromo-carbons suitable for use as fire extinguishing agents. Heating analyses have been made for an idealized extinguishant tank subjected to various flight regimes. Insulation thicknesses as well as example calculations of weight penalties due to insulation necessary to maintain temperatures below decomposition have been computed for various extinguishants in the idealized tank under Mach 4 and ... |
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| COMMERCIAL SUPERSONIC TRANSPORT PROGRAM. PHASE 2-C. PROPULSION SYSTEM PERFORMANCE SPECIFICATION. PRATT AND WHITNEY AIRCRAFT JTF 17A-20B ENGINE INSTALLATION |
15 NOV 1965 |
44 pages |
| Authors:
BOEING CO RENTON WA
|
| This specification defines the installed performance of the 650- pound-per-second Pratt and Whitney JTF17A-20B engine in the Boeing Model 733-394 airplane. Performance data are presented for the initial service (1900 F) engine and the basic (2200 F) engine. The estimated inlet drag values used for the determination of airplane performance characteristics are also specified. System performance requirements established herein are design objectives to be applied to the prototype airplanes. Application ... |
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| COMMERCIAL SUPERSONIC TRANSPORT PROGRAM. PHASE II-C. INTERIM AIRCRAFT PERFORMANCE ASSESSMENT REPORT. SYSTEMS. |
15 NOV 1965 |
|
| Authors:
BOEING CO RENTON WA
|
| Substantial progress has been made in all systems development essentially as outlined in the Phase II-B and II-C plans. Because of their relative importance and sensitivity to variations in airplane configuration and their effect on performance, only the development of flight control systems and flight deck vision is reported. (Author) |
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| COMMERCIAL SUPERSONIC TRANSPORT PROGRAM. PHASE II-C. PROPULSION SYSTEM PERFORMANCE SPECIFICATION. GENERAL ELECTRIC GE4/J5G ENGINE INSTALLATION. |
15 NOV 1965 |
|
| Authors:
BOEING CO RENTON WASH
|
| This specification defines the installed performance for the 475-pound-per-second size General Electric Company GE4/J5G engine in the Boeing Model 733-390 airplane and specifies the estimated inlet and nozzle drag values used for the determination of the airplane performance characteristics. System performance requirements established herein are design objectives to be applied in the prototype airplanes. Application of these requirements to production airplane design will be established after prototype flight testing. (Author). ... |
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| EFFECTS OF SONIC BOOM ON PEOPLE: ST. LOUIS, MISSOURI, 1961-1962 |
03 NOV 1965 |
|
| Authors:
Charles W. Nixon; Paul N. Borsky; AIR FORCE AEROSPACE MEDICAL RESEARCH LAB WRIGHT-PATTERSON AFB OH
|
| The vicinity of St. Louis, Missouri, was exposed to approximately 150 sonic booms during a 10-month period from July 1961 to April 1962. Ground overpressures, ranging up to about 3 lb/sq ft, were carefully measured for a series of 17 of the supersonic flights. Data obtained from over 2300 direct interviews, analyses of complaints, and engineering evaluations of alleged damage were related to information on aircraft operations and sonic-boom overpressure ... |
|
| AERODYNAMICS OF POWER PLANT INSTALLATION, PART I. |
OCT 1965 |
|
| Authors:
ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE)
|
| Contents: Engine designer's point of view; A discussion of selected aerodynamic problems on integration of propulsion systems with airframe on transport aircraft; The feasibility of supersonic combustion ramjets for low hypersonic speeds; The blunt trailing edge axial-flow supersonic compressor; Measurements of relaxation effects in nozzle flow of hot combustion gases by means of a shock tube technique; Aircraft performance problems associated with engine and intake installation; Low-drag installation of twin ... |
|
| ORIGINATION OF CONDENSATIONS IN SUPERSONIC FLOWS OF RAREFIED GASES, |
12 AUG 1965 |
|
| Authors:
A. A. Pomerantsev; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| An explanation is given of the disappearance of molecular condensations in a sharply rarefied gas, which allows one to calculate the heights of appearance of condensations in front of bodies entering a rarefied layer, in which freemolecular flows cease. (Author) |
|
| THE EFFECT OF VARIOUS BOATTAIL SHAPES ON BASE PRESSURE AND OTHER AERODYNAMIC CHARACTERISTICS OF A 7-CALIBER LONG BODY OF REVOLUTION AT M EQUALS 1.70. |
AUG 1965 |
|
| Authors:
Boris G. Karpov; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Models, 7 calibers long, with a variety of conical, ogival (convex) and concave boattails were free-flight tested at M = 1.70, for drag and other aerodynamic characteristics. The total drag decreases monotonically for boattails longer than 0.5 calibers. For shorter boattails, the drag is higher than that of the square based body. For boattail lengths between 0.5 and 1.5 calibers, conical boattails have lower drag than either the ogival or ... |
|
| V/STOL Plenum Chamber Combustion Research Study. |
28 APR 1965 |
|
| Authors:
Lawrence Maggitti; NAVAL AIR ENGINEERING CENTER PHILADELPHIA PA AERONAUTICAL ENGINE LAB
|
| A research program was initiated on combustion in the fan duct of a turbofan engine configured for V/Stol and supersonic flight at altitude. An analysis of the operating conditions for a typical application was made. Several methods of supporting combustion under these conditions and in the space available were considered. Experimental research was carried out on eighteen combustion chamber liners of the can type, sixteen of which were of experimental ... |
|
| PROBLEMS OF RESCUING CREWS AT EMERGENCIES AT GREATER SPEEDS AND HIGH FLIGHT ALTITUDES, |
01 APR 1965 |
|
| Authors:
A. V. Chesalov; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| Two trends of investigation are discussed: (1) To reduce overloads affecting the human immediately after catapulting by simultaneous gaining of protective methods for the face, internal organs and skin against the action of high speed airflow; and (2) to assure the possibility of sharply decelerating an aircraft suffering an emergency to indicated speeds of the order of 850-900 km/hr. |
|
| ENGINEERING INVESTIGATION AND TESTS WHICH FURTHER SUBSTANTIATE SYSTEM FEASIBILITY AND PROVIDE DATA RELATIVE TO THE DEVELOPMENT OF A NUCLEAR LOW ALTITUDE SUPERSONIC VEHICLE. PART II. TECHNICAL INFORMATION. VOLUME 9. NUCLEAR RADIATION EFFECTS TEST NO. 10 -- |
DEC 1964 |
|
| Authors:
LING-TEMCO-VOUGHT INC DALLAS TX LTV VOUGHT AERONAUTICS DIV
|
| Presented in this document are the results of Nuclear Radiation Effects Test No. 10 which was conducted under the LASV-N2 Air Force Contract AF33(657)-12517. The irradiation was performed in the Air Force Ground Reactor during the period 25 February through 1 March 1964. A series of radar components, a secondary power unit, several flight test instrumentation sensors, several advanced computer components, and portions of a command control subsystem were exposed ... |
|
| ENGINEERING INVESTIGATION AND TESTS WHICH FURTHER SUBSTANTIATE SYSTEM FEASIBILITY AND PROVIDE DATA RELATIVE TO THE DEVELOPMENT OF A NUCLEAR LOW ALTITUDE SUPERSONIC VEHICLE. PART II. TECHNICAL INFORMATION. VOLUME 10. NUCLEAR RADIATION EFFECTS. TEST NO. 18. |
DEC 1964 |
|
| Authors:
LING-TEMCO-VOUGHT INC DALLAS TX LTV VOUGHT AERONAUTICS DIV
|
| Presented in this document are the test results of Nuclear Radiation Effects Tests No. 18 which was a dynamic credibility demonstration conducted in the Air Force Ground Test Reactor during the time period of 29 July through 5 August 1964. This work was performed in support of Air Force Contract AF33(657)-12517. Planning and execution of the irradiation provided specific test data on subsystems, components, and materials representative of those which ... |
|
| CHANNELED BODIES STREAMLINED WITH FLAT AND CONIC SHOCK WAVES, |
18 NOV 1964 |
|
| Authors:
V. V. Keldysh; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| Consideration is given to examples of precise solutions for external flow around channeled bodies with supersonic velocities at the inlet to the internal channel, and the corresponding coefficients are calculated. Two classes of bodies are investigated: (1) bodies consisting of flat faces and streamlined over the design regime with the formation of flat, attached shock waves, (2) axisymmetric bodies for which external flow is conic. |
|
| COMMERCIAL SUPERSONIC TRANSPORT PROGRAM. PHASE II-A. COMPREHENSIVE REPORT. VOLUME V-A BOOK 2. AERODYNAMICS. |
01 NOV 1964 |
|
| Authors:
BOEING CO RENTON WA AIRPLANE DIV
|
| Performance data are presented for the Boeing Model 733-290 (Intercontinental), and Model 733-291 (Domestic) variable-sweep, commercial supersonic transport. Complete data are given to show the effects of weight, speed, altitude, power setting, and temperature so that airline operational and route analysis studies may be made. These data augment the basic performance given in Book One of this volume. Payload-range examples are shown at the maximum sonic boom overpressures of 2.5 ... |
|
| COMMERCIAL SUPERSONIC TRANSPORT PROGRAM. PHASE II-A. COMPREHENSIVE REPORT. VOLUME XVIII-A. TRAINING PLANS. |
01 NOV 1964 |
|
| Authors:
BOEING CO RENTON WA AIRPLANE DIV
|
| These studies show that there is a need for further and more extensive aircrew flight training than was proposed in Phase I. Specifically, the flight time has been increased from 14 hours to 24 hours. The flight engineer's course flight schedule is increased from 14 hours to 18 hours. The airlines are currently making encouraging progress in their efforts to demonstrate that significant reductions in flight training hours can be ... |
|
| COMMERCIAL SUPERSONIC TRANSPORT ENGINE. VOLUME IX-E. ENGINE. PART 3. OPERATIONS AND ECONOMICS. PHASE II-A DATA SUBMISSION. |
01 NOV 1964 |
|
| Authors:
PRATT AND WHITNEY AIRCRAFT GROUP EAST HARTFORD CT
|
| Contents: Sales Price, Operating Costs, Flight Operation and Safety; Safety, Over-all Performance, Utilization, Flexibility, Ground Operation; Support System Concept, Maintenance, Servicing, Training, Growth Potential; Performance, Life, and Specific Weight. |
|
| WIND TUNNEL CALIBRATION TESTS AND PRESSURE MEASUREMENTS ON A BLUNTED SLENDER CONE FROM MACH 1.5 TO 10.0, |
SEP 1964 |
|
| Authors:
George K. GARDINER; LITTON SYSTEMS INC WOODLAND HILLS CALIF
|
|
| METEOROLOGICAL ASPECTS OF THE SONIC BOOM. |
SEP 1964 |
|
| Authors:
Edward J. Kane; Thomas Y. Palmer; BOEING CO RENTON WASH AIRPLANE DIV
|
| This report is a study of the effect of changing meteoro logical conditions on the sonic boom produced during steady level flight. The influence of variations in atmospheric temperature, pressure, and wind on this noise are investigated. Simplified methods are established for estimating the effect of these variations. Combinations of meteorological conditions which can produce anomalous propagation such as complete cut-off, focusing, and extreme lateral spread are discussed. The effect ... |
|
| SONIC BOOM BIBLIOGRAPHY, |
SEP 1964 |
|
| Authors:
Robert K. Friedman; FEDERAL AVIATION AGENCY WASHINGTON D C
|
| This bibliography on sonic boom has been compiled in response to a specific request. No claim is made that these 193 citations comprise an exhaustive or critical compilation. The inclusion of any reference to material is not to be construed as an endorsement of the information contained in that material. The reference search was completed August 28, 1964. (Author) |
|
| TRANSIENT AIRLOADS ON A BODY OF REVOLUTION DUE TO INDICIAL SINKING AT A LARGE ANGLE OF ATTACK, |
AUG 1964 |
|
| Authors:
J. Ray Ruetenik; W. Bryan Brooks; MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND STRUCTURES RESEARCH LAB
|
| A nonlinear method is proposed for predicting the airloads on a slender, pointed body of revolution due to indicial sinking at a large angle of attack at supersonic or low hypersonic speeds. The method is an extension of Miles (NAVORD 2052) linearized theory for a slender, pointed body achieved by incorporating the Bryson theory of the indicial drag of a circular cylinder for the transient cross-flow drag on the body. ... |
|
| IN 1973 YOU WILL TRAVEL AT 2330 KM/HOUR, |
14 JUL 1964 |
|
| Authors:
Constantin Sabin Ioan; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| The specialists assert with confidence that in ten years intercontinental passenger planes will fly in the stratosphere at altitudes of 18-20 km at the impressive cruising speed of 2330 km/hour (Mach 2.2). |
|
| DYNAMIC ROLL AND MOTOR SEPARATION TEST OF AN XADR-9A MODEL, IN THE BLOWDOWN FACILITY, FOR TRACOR, INC., |
08 JUL 1964 |
|
| Authors:
W. S. Talk; GENERAL DYNAMICS DAINGERFIELD TEX ORDNANCE AEROPHYSICS LAB
|
| The TRACOR XADR-9A missile was set up in cell 6 and testing began on 26 May 1964. During the test period, ten (10) configurations were tested at Mach numbers of .8, .9, 1.0, and 1.1. The determination of the model roll rate was the primary objective of the test, at each Mach number and aat 0, 5, and 10 degrees angle of attack. Two booster rocket separation tests were covered ... |
|
| AN INDUCED VOLTAGE TECHNIQUE FOR EXPLODING A PLASTIC PROJECTILE, |
01 JUL 1964 |
|
| Authors:
Rayner A. Montgomery; E. Eugene Kilmer; NAVAL ORDNANCE LAB WHITE OAK MD
|
| An induced voltage technique for exploding a plastic projectile in supersonic flight was investigated. A 40-mm projectile was launched at speeds varying from 2,000 fps to 4,000 fps. Proper initiation of the explosive train was obtained. This technique was considered for application in laboratory facilities for conducting ballistic research. (Author) |
|
| RESEARCH ON THERMAL EFFECTS ON FUELS ATTRIBUTABLE TO STORAGE. |
JUL 1964 |
|
| Authors:
J. J. Bialy; T. A. Norris; F. P. Frascati; TEXACO INC BEACON N Y TEXACO RESEARCH CENTER
|
| Texaco Research Coker was modified to a more dynamic system, to both approach the test conditions used in various fuel test rigs, such as the CRC rig, and to simulate actual mission profiles for different supersonic aircraft. The modifications included vacuum system for the fuel reservoir, cold finger device and sampling port for fuel sampling. A series of shakedown runs have been completed using the modified test aggregate. Analytical phase ... |
|
| PROCEEDINGS OF THE OSU-RTD SYMPOSIUM ON ELECTROMAGNETIC WINDOWS (7TH), 2-4 JUNE 1964. VOL. 5: PAPERS SUBMITTED FOR THE PROCEEDINGS ONLY |
04 JUN 1964 |
192 pages |
| Authors:
Alan I. Slonim; OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS ANTENNA LAB
|
| The papers presented in this report were submitted for the Seventh Symposium on Electromagnetic Windows and are published in five volumes. Volume 5 includes the general field of radome design, performance, characteristics, and construction material. |
|
| PROCEEDINGS OF THE OSU-RTD SYMPOSIUM ON ELECTROMAGNETIC WINDOWS (7TH) 2-4 JUNE 1964. VOL. III: SESSION V: FABRICATION AND TESTING OF AIRBORNE RADOMES. SESSION VI: HYPERSONIC ENVIRONMENT, |
04 JUN 1964 |
|
| Authors:
Alan I. Slonim; OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS ANTENNA LAB
|
| The papers presented in this report were submitted for the Seventh Symposium on Electromagnetic Windows and are published in five volumes. Vol. 3 concerns Fabrication and Testing of Airborne Radomes and Hypersonic Environment. |
|
| PROCEEDINGS OF THE OSU-RTD SYMPOSIUM ON ELECTROMAGNETIC WINDOWS (7TH), 2-4 JUNE 1964. VOL. 2, SESSION 3: ELECTRICAL DESIGN. SESSION 4: STRUCTURAL DESIGN FOR LARGE RADOMES |
JUN 1964 |
229 pages |
| Authors:
Alan I. Slonim; C. H. Chiou; A. H. Schaufelberger; J. F. Harder; Stephen J. Gotkis; Peter Zuzolo; J. E. Burroughs; Eino J. Luoma; OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS ANTENNA LAB
|
| Electrical and structural properties of airborne and large fixed radomes were examined to gain understanding of failure and design criteria for their fabrication. The radomes shell and sandwich structures can be produced from a variety of non-metallic materials (e.g. fiberglass facings, thermoplastic and foam cores) and these are of interest to Plastec. |
|
| SONIC BOOM AND COMMUNITY RELATIONS, |
APR 1964 |
|
| Authors:
J. K. Power; George Bates ; FEDERAL AVIATION AGENCY WASHINGTON D C
|
| Some preliminary accomplishments of sonic boom research in predicting strength and location of sonic boom shock waves, determining the effects on light aircraft, and evaluating community tolerance to various levels of sonic boom intensity are reviewed. A brief summary of the implications of sonic boom with regard to supersonic transport design is included. |
|
| RESEARCH ON PHOTOGRAPHIC WINDOW PROBLEM IN SUPERSONIC AND HYPERSONIC AIRCRAFT. |
MAR 1964 |
|
| Authors:
NORTH AMERICAN AVIATION INC LOS ANGELES CALIF
|
| The purpose of the contract was twofold: (1) to attempt laboratory verification of the analytically predicted effects of environmentally-stressed windows on photographic image quality, and (2) to perform an engineering investigation directed toward the more precise determination of the window environment to be expected in a hypersonic vehicle, and the feasibility of reducing the severity of such an environment. Both objectives were fulfilled. It is recommended that flight tests be ... |
|
| VIBRATION OF A WING OF FINITE SPAN IN SUPERSONIC FLOW, |
11 DEC 1963 |
|
| Authors:
M. D. Khaskind; S. V. Fal'kovich; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
|
| NEW HIGH TEMPERATURE INFRARED TRANSMITTING GLASSES. |
31 OCT 1963 |
|
| Authors:
A. Ray Hilton; Charlie E. Jones; Maurice J. Brau; TEXAS INSTRUMENTS INC DALLAS
|
| For more than a year and a half Texas Instruments has been evaluating three-component (ternary) non-oxide glasses made from elements from groups IVA, VA, and VIA as possible high temperature (500 C) infrared window materials. Of particular importance are materials that can be used to take advantage of the atmospheric windows at 3 to 5 and 8 to 14 microns. Systems evaluated in the last six months are the Ge-PS, ... |
|
| GAS TURBINE AND JET ENGINE FUELS |
25 OCT 1963 |
21 pages |
| Authors:
William L. Streets; PHILLIPS PETROLEUM CO BARTLESVILLE OK
|
| Efforts included: (1) endurance testing of two promising new splash- cooled two-inch test combustor designs capable of operating under conditions simulating low-level tactical fighter attack missions and/or submarine search missions by a regenerative turboprop-equipped aircraft; (2) planning and statistical design of a test program to determine whether the 0.4 weight per cent maximum total sulfur now allowed in JP-5 fuel is a safe level for protection of modern turbine blading ... |
|
| ANALOG SIMULATION OF A THREAT WARNING PROCESSOR, |
OCT 1963 |
|
| Authors:
J. BEARD; O. Poree; P. Wierenga; MICHIGAN UNIV ANN ARBOR INST OF SCIENCE AND TECHNOLOGY
|
| The feasibility of calculating two threat estimators for warning aerospace vehicles of attack was investigated by analog simulation. The first of these estimators is the ratio of range (between target and attacking vehicle) to its time derivative (range rate). The second estimator is related to the first, and represents a more complicated function of range. Simulation results are presented for Mach 1,2, and 3 aircraft attacked by surface-to-air missiles. The ... |
|
| AERODYNAMIC HEATING AND STRUCTURAL TEMPERATURE RESPONSE, |
JUL 1963 |
1 pages |
| Authors:
Stanley C. Browning; ALLEGANY BALLISTICS LAB HERCULES POWDER CO CUMBERLAND MD
|
|
| CLIMATOLOGICAL SUMMARIES FOR THE SUPERSONIC AIRCRAFT, NEW YORK - SAN FRANCISCO ROUTE. |
JUN 1963 |
|
| Authors:
WEATHER BUREAU WASHINGTON D C
|
| Detailed climatological information is presented for a selected air route (New York to San Francisco and return) to provide needed information for the design and operation of a supersonic aircraft. This information is shown primarily for altitudes between 50,000 and 100,000 feet. |
|
| AIR VEHICLE FLIGHT PATH OPTIMIZATION. |
MAY 1963 |
|
| Authors:
GRUMMAN AIRCRAFT ENGINEERING CORP BETHPAGE N Y
|
| The means generally available for treatment of optimal air vehicle flight paths are limited from the viewpoint of practical numerical computations. The method of gradients has been applied to air vehicle problems of maximum range, minimum fuel, and minimum time subject to various constraints with considerable success. Two versions of the gradient method, gradient pro jection and a gradient/penalty function technique for handling terminal constraints have been employed. An integral ... |
|
| THE MEASUREMENT OF ATMOSPHERIC TURBULENCE AT VERY LOW ALTITUDE AND HIGH SPEED (MESURE DE LA TURBULENCE ATMOSPHERIQUE A TRES BASSE ALTITUDE ET GRANDE VITESSE), |
APR 1963 |
|
| Authors:
Jean Angelini; ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE)
|
|
| THE SONIC BOOM PROBLEM. |
MAR 1963 |
|
| Authors:
DEPUTY CHIEF OF STAFF RESEARCH AND DEVELOPMENT (AIR FORCE) WASHINGTON D C
|
| The memo summarizes the current state of knowledge relating to sonic boom generation, propagation, and effects, and attempts to judge the severity of the problem that will arise with the beginning of commercial supersonic flights. It is based on both recently published information and conversations with specialists throughout the country who are working in the sonic boom field. The latter include representatives of private industry as well as of Government ... |
|
| FREE-FLIGHT BALLISTICS RANGE TESTS OF MODELS FOR THE GE PROGRAM 1-62 |
31 DEC 1962 |
|
| Authors:
Jeanne B. Jusino; NAVAL ORDNANCE LAB WHITE OAK MD
|
| Data are presented for seven free-flight shots of models of the 1-62 program made in the Pres surized Ballistics Range No. 3 at the Naval Ordnance Laboratory. A drag curve was obtained for the Mach number range of 4 through 7. Stabil ity coefficients were also obtained and are pre sented in both graphical and tabular form. The Reynolds numbers for these shots were 0.5 to 2.4 million. Shadowgraph pictures ... |
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Reports by Keyword(s)
SUPERSONIC FLIGHT
