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Oklahoma Historical Society
1,298
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428
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242
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130
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65
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34
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33
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32
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30
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28
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768
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699
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508
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422
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335
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Office of Scientific & Technical Information Technical Reports
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182 More
Serial/Series Title
States
Year
Month
Language
Some Properties of Wing and Half-Body Arrangements at Supersonic Speeds
Report presenting an investigation of the certain wing-body combinations as measured by the lift-drag ratio for two arrangements: a half-cone mounted under a triangular wing and a half Newtonian ogive similarly mounted. The configurations were tested for a range of Mach numbers from 1.5 to 5.0. Results regarding the comparison of a half-cone versus a full cone and calculated maximum lift-drag ratio are provided.
Date:
July 22, 1957
Creator:
Migotsky, Eugene & Adams, Gaynor J.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Wing Loads on a Flexible Swept-Wing Jet Bomber During Push-Pull Maneuvers
Report presenting measurements of the loads of the wing of a Boeing B-47A medium bomber using strain-gage instrumentation during 23 symmetrical push-pull maneuvers at a variety of altitudes, Mach numbers, and gross weights. Time histories of aerodynamic shear, bending moment, and torque at each of four spanwise stations on the left wing and one on the right wing were created. Based on the results, presently available methods seem to be capable of predicting additional and basic loads accurately within the range of flight conditions in the test.
Date:
July 23, 1957
Creator:
Gainer, Patrick A. & Harper, Paul W.
Object Type:
Report
System:
The UNT Digital Library
Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations
Memorandum presenting a survey of the problems introduced by the increased longitudinal stability and the reduced directional stability of aircraft operating in the low supersonic speed range. The longitudinal stability increases markedly at supersonic speeds and results in high drags due to trimming and in limited control for maneuvering. The vertical-tail contribution is shown to be affected by many factors including the wing position, the fuselage shape, and the horizontal-tail position.
Date:
July 12, 1957
Creator:
Spearman, M. Leroy
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel tests of the static longitudinal characteristics at low speed of a swept-wing airplane with blowing flaps and leading-edge slats
Report presenting a wind-tunnel investigation of a high-wing airplane with an aspect ratio 6.75 wing with approximately 36 degrees of sweepback to determine the lift effectiveness obtainable with trailing-edge blowing flaps in combination with leading-edge slats. Flap effectiveness and stability were maintained to high angles of attack by control of leading-edge flow separation with slats. An analysis of the take-off performance, landing performance, and comparisons with flight data are provided.
Date:
July 5, 1957
Creator:
James, Harry A. & Maki, Ralph L.
Object Type:
Report
System:
The UNT Digital Library
Notes on a Large-Scale Statistical Program for the Establishment of Maneuver-Loads Design Criteria for Military Airplanes
Report presenting an outline of a proposed statistical program to collect data for the establishment of more realistic maneuver-loads design criteria. Some sample experimental data are also included to indicate possible methods of statistical analysis and the potential sample size needed for the program.
Date:
July 17, 1957
Creator:
Mayer, John P.; Stone, Ralph W., Jr. & Hamer, Harold A.
Object Type:
Report
System:
The UNT Digital Library
The aerodynamic characteristics of a body in the two-dimensional flow field of a circular-arc wing at a Mach number of 2.01
From Introduction: "The present report is concerned with the characteristics of a body in the two-dimensional flow field of a circular-arc wing of rectangular plan form."
Date:
July 2, 1957
Creator:
Gapcynski, John P. & Carlson, Harry W.
Object Type:
Report
System:
The UNT Digital Library
Time-History Data of Maneuvers Performed by a Republic F-84F Airplane During Squadron Operational Training
Report presenting a control-motion study program with a Republic F-84F using a cross section of tactical maneuvers performed during squadron operational training. Time-history figures, airspeed and Mach number envelopes, and other aerodynamic characteristics are provided.
Date:
July 22, 1957
Creator:
Hamer, Harold A.; Mayer, John P. & Case, Donald B.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a supersonic-inlet - turbojet-engine combination at Mach 2.0 and angles of attack up to 6 degrees
Report presenting data obtained on a supersonic-inlet-turbojet-engine combination at a free-stream Mach number of 2.0 and a range of angles of attack. Although the engine did not influence inlet pressure recovery, data indicate that the engine may have increased the compressor-face distortions at angle of attack.
Date:
July 1957
Creator:
Hearth, Donald P. & Musial, Norman T.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of Wing-Aileron Flutter Characteristics of a 1/4-Scale Dynamic Model of the X-1E Airplane
Report presenting testing of some of the flutter characteristics of a 1/4-scale model of the X-1E airplane wing and aileron in the transonic tunnel. The wing was tested as part of a complete model of an airplane over a Mach number range of 0.4 to 1.05 and a range of angles of attack. No stall flutter or classical flutter was encountered, but the results indicate that unstable aerodynamic damping is present on the ailerons at transonic speeds. Results regarding free play, angle of attack, aileron viscous dampers, and aileron tabs are provided.
Date:
July 10, 1957
Creator:
Gibson, Frederick W.; Igoe, William B. & Maloney, P. R.
Object Type:
Report
System:
The UNT Digital Library
Exploratory Tests of the Behavior of Several Materials in a Supersonic Air Jet at 4,000 Degrees Fahrenheit
"Several materials have been tested in the ceramic-heated jet (laboratory model) at a Mach number of 1.96 with a stagnation temperature of approximately 4,000 degrees Fahrenheit. Test models made of molybdenum were less affected by temperature than titanium, stainless steel, and an alloy of 90 percent tungsten, 6 percent nickel, and 4 percent copper. Titanium and steel burn with highly exothermic reactions when subjected to the 4,000 degrees Fahrenheit air jet" (p. 1).
Date:
July 29, 1957
Creator:
Hopko, Russell N. & Trout, Otto F., Jr.
Object Type:
Report
System:
The UNT Digital Library
Transonic Flutter Investigation of a Cantilevered, Aspect-Ratio-4, 45 Degree Sweptback, Untapered Wing With Three Different Pylon-Mounted External Store Configurations
Report presenting an investigation of the transonic flutter characteristics of a cantilevered, aspect-ratio-4, 45 degree sweptback, untapered wing with three different pylon-mounted external-store configurations. An additional study was created during the investigation to find a store configuration with a substantially higher flutter speed than what was obtained with the other two stores. Results regarding general comments, the investigation of store types A and B, node-line survey, and the investigation of store type C are provided.
Date:
July 5, 1957
Creator:
Ruhlin, Charles L. & Boswinkle, Robert W., Jr.
Object Type:
Report
System:
The UNT Digital Library
Some Effects of Wing Height on the Vertical-Tail Pressure Distributions of a Complete Model in Sideslip at High Subsonic Speeds
Report presenting an investigation in the high speed tunnel of some effects of wing height and angle of attack on the vertical-tail pressure distribution of a complete model in sideslip at high subsonic speeds. The 45 degree swept wing had an aspect ratio of 4, a taper ratio of 0.30, and NACA 65A006 airfoil sections parallel to the model plane of symmetry. Results regarding vertical-tail loads and vertical-tail center of pressure are provided.
Date:
July 17, 1957
Creator:
Few, Albert G., Jr. & Alford, William J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Foreign-object retention and flow characteristics of retractable engine-inlet screens
Report presenting an investigation to determine and improve on the foreign-object-retention capabilities and pressure-loss characteristics of rectractable engine-inlet screens. Testing occurred with two commerically made retractable screens installed in the engine-inlet sections for which they were designed. Results regarding the retention for both the original and modified screens and pressure tests are provided.
Date:
July 26, 1957
Creator:
Steffen, Fred W. & Rodert, Lewis A.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the Low-Speed Performance and Static Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing-Body-Tail Combination With Blowing Over Trailing-Edge Flaps
Report presenting an investigation in the full-scale tunnel to determine the effects of boundary-layer control by blowing over trailing-edge flaps on the low-speed performance and static longitudinal stability characteristics of a 60 degree delta wing-body-tail combination with variable flap positioning and leading-edge devices. Results regarding the flap lift characteristics at zero angle of attack, tail-off characteristics, tail-on characteristics, and low-speed performance characteristics are provided.
Date:
July 29, 1957
Creator:
Scallion, William I. & Cannon, Michael D.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study 2: design and experimental performance of turbine with low-velocity-turning stator and standard rotor
Report presenting a low-velocity-turning stator designed to reduce secondary-flow loss cores by turning the flow at low velocities and accelerating it in passages of constant flow angle with reduced cross-channel pressure gradients. Turbine performance was measured to determine the effect of low-velocity turning in the stator on the overall turbine performance. Results regarding the stator performance, overall turbine performance, and rotor exit surveys are provided.
Date:
July 18, 1957
Creator:
Rohlik, Harold E.; Wintucky, William T. & Scribbe, Herbert W.
Object Type:
Report
System:
The UNT Digital Library
Injection Principles for Liquid Oxygen and Heptane Using Nine-Element Injectors in an 1800-Pound-Thrust Rocket Engine
Memorandum presenting a study of six nine-element injectors for the liquid-oxygen-heptane propellant system in an 1800-pound-thrust rocket engine. The characteristic velocities for comparable injector types were about the same as those obtained from the two-element study. The level of performance was generally higher for the nine-element injectors.
Date:
July 18, 1957
Creator:
Neu, Richard F.
Object Type:
Report
System:
The UNT Digital Library
Exploratory investigation of aerodynamic effects of external combustion of aluminum borohydride in airstream adjacent to flat plate in Mach 2.46 tunnel
Report presenting pressure distributions associated with stable combustion of aluminum borohydride in the supersonic stream adjacent to a short, 13-inch chord, and an extended, 25-inch chord, flat-plate model. High-speed direct and schileren motion pictures of the flame and associated shock waves were taken. Results regarding the description of the combustion and associated stream disturbances, static-pressure change at model reference surface caused by combustion, lift forces resulting from combustion, base pressure change caused by combustion, stream-parameter measurements during combustion, and surface temperature changes during combustion are provided.
Date:
July 29, 1957
Creator:
Dorsch, Robert G.; Serafini, John S. & Fletcher, Edward A.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Limitations Imposed on One-Spool Ducted-Fan-Engine Designs by Compressors and Turbines at Flight Mach Numbers of 0, 0.6, and 0.8
Memorandum presenting an analysis of one-spool ducted-fan engines in order to determine the primarily limitations on ducted-fan-engine design and to compare this type with the turboprop and turbojet engines for the same application. Designs were studied at flight Mach numbers of 0 and 0.6 at sea level and Mach numbers of 0.6 and 0.8 at the tropopause. Results regarding the discussion of charts, effect of design parameters on turbine stress, effect of design parameters, effect of design parameters on thrust specific fuel consumption, and effect of design parameters on thrust per unit total weight flow are provided.
Date:
July 18, 1957
Creator:
Cavicchi, Richard H.
Object Type:
Report
System:
The UNT Digital Library
The Effects at Subsonic Speeds of Wing Fences and a Tail on the Longitudinal Characteristics of a 63 Degree Swept-Wing Fuselage Combination
Report presenting wind-tunnel testing to evaluate the effects of wing fences and a tail on the longitudinal characteristics of a highly swept wing in combination with a fuselage. The model, which had a cambered and twisted wing with a leading-edge sweepback of 63 degrees and an aspect ratio of 3.5, was tested with fences of various shapes and swept and unswept horizontal tails. Results regarding exploratory tests, final-configuration tests, static longitudinal stability factors, and maximum lift-drag ratios are provided.
Date:
July 2, 1957
Creator:
Buell, Donald A. & Kolbe, Carl D.
Object Type:
Report
System:
The UNT Digital Library
Reaction of Fluorine With Carbon as a Means of Fluorine Disposal
Memorandum presenting an experimental investigation showing that amorphous carbon, such as wood charcoal, is readily applicable to fluorine disposal by a specified chemical reaction. Fluorine and fluorine-oxygen and fluorine-nitrogen mixtures containing as little as 6.5 percent fluorine reacted spontaneously with fresh dry charcoal.
Date:
July 18, 1957
Creator:
Schmidt, Harold W.
Object Type:
Report
System:
The UNT Digital Library
Experimental and theoretical aerodynamic characteristics of two low-aspect-ratio delta wings at angles of attack to 50 degrees at a Mach number of 4.07
Report presenting an investigation conducted in the 9- by 9-inch Mach number 4 blowdown jet to determine the aerodynamic characteristics of two double-wedge-section delta wings of aspect ratio 1.3 and 2.3 to angles of attack of 50 degrees at a Mach number of 4.07. The results are compared with the predictions of linear theory, two-dimensional shock-expansion theory, Newtonian-impact theory, and a method which utilizes the shock-wave and expansion-wave equations expanded by the two-dimensional hypersonic-flow similarity parameter.
Date:
July 10, 1957
Creator:
Smith, Fred M.
Object Type:
Report
System:
The UNT Digital Library
Propellant vaporization as a criterion for rocket-engine design : experimental effect of fuel temperature on liquid-oxygen - heptane performance
Characteristic exhaust velocity of a 200-pound-thrust rocket engine was evaluated for fuel temperatures of -90 degrees, and 200 degrees f with a spray formed by two impinging heptane jets reacting in a highly atomized oxygen atmosphere. Tests covered a range of mixture ratios and chamber lengths. The characteristic exhaust-velocity efficiency increased 2 percent for a 290 degree f increase in fuel temperature. This increase in performance can be compared with that obtained by increasing chamber length by about 1/2 inch. The result agrees with the fuel-temperature effect predicted from an analysis based on droplet evaporation theory. Mixture ratio markedly affected characteristic exhaust velocity efficiency, but total flow rate and fuel temperature did not.
Date:
July 26, 1957
Creator:
Heidmann, M. F.
Object Type:
Report
System:
The UNT Digital Library
Flight Measurements and Calculations of Wing Loads and Load Distributions at Subsonic, Transonic, and Supersonic Speeds
"Presented in this report is a summary of local and net angle-of-attack wing-panel loads measured in flight on six airplanes. In addition, a comparison of these loads measured in flight with calculations based on simple theory is presented" (p. 1).
Date:
July 2, 1957
Creator:
Malvestuto, Frank S.; Cooney, Thomas V. & Keener, Earl R.
Object Type:
Report
System:
The UNT Digital Library
Arrangements of jet engine and airframe for increased range
Report presenting an evaluation of a number of factors affecting engine-airframe arrangements in terms of range. Appropriate equations are developed and evaluated for a range of Mach numbers, ramjet and turbojet engines at several cycle temperatures, and two airplane lift-drag ratios. Some of the factors explored include inlet locations, jet cant for lift, engine moments for trim, a combination of the three factors, and the use of boundary layer in the engine.
Date:
July 26, 1957
Creator:
Luidens, Roger W.
Object Type:
Report
System:
The UNT Digital Library