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Investigation of a Prototype Iroquois Turbojet Engine in an Altitude Test Chamber Coord. No. AF-P-6
"Operation of the original engine configuration disclosed a severe compressor stall problem at high altitude, which was largely attributed to a radial flow distortion entering the high-pressure compressor. Engine modifications for eliminating or alleviating the stall problem were investigated. These included use of variable high-pressure compressor inlet guide vanes, increased turbine-stator areas, and minor alterations in both the low- and high-pressure compressor rotors" (Abstract).
Date:
July 28, 1958
Creator:
McAulay, John E. & Groesbeck, Donald E.
System:
The UNT Digital Library
An Investigation of the Effect of Target Temperature on Projectile Penetration and Cratering
Results regarding testing of steel projectiles fired into copper targets at velocities from 5,000 to 11,500 feet per second, which indicated that as target temperature is increased, the crater size also increases. Twenty-two caliber steel cylinders and steel spheres were used as projectiles.
Date:
July 28, 1958
Creator:
Kinard, William H. & Lambert, C. H., Jr.
System:
The UNT Digital Library
An Investigation of the Effect of Target Temperature on Projectile Penetration and Cratering
Results regarding testing of steel projectiles fired into copper targets at velocities from 5,000 to 11,500 feet per second, which indicated that as target temperature is increased, the crater size also increases. Twenty-two caliber steel cylinders and steel spheres were used as projectiles.
Date:
July 28, 1958
Creator:
Kinard, William H. & Lambert, C. H., Jr.
System:
The UNT Digital Library
Turbulent Skin Friction at High Mach Numbers and Reynolds Numbers
From Summary: "For a number of years now, experimenters have been making measurements of skin friction. Formerly, the main interest was at low Mach numbers; later, measurements were made at supersonic Mach numbers. However, almost all of these measurements were over a limited range of Reynolds numbers. On the other hand, these measurements fairly well determined the effects of Mach number and heat transfer on skin friction. The purpose of this paper is to give the results of skin-friction measurements in turbulent boundary layers at high Mach numbers and high Reynolds numbers where data have not previously existed."
Date:
July 24, 1958
Creator:
Matting, Fred W. & Chapman, Dean R.
System:
The UNT Digital Library
Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane with External Fuel Tanks, TED No. NACA AD 3112
From Summary: "A supplementary investigation to determine the effect of external fuel tanks on the spin and recovery characteristics of a l/28-scale model of the North American FJ-4 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The model had been extensively tested previously (NACA Research Memorandum SL38A29) and therefore only brief tests were made to evaluate the effect of tank installation."
Date:
July 23, 1958
Creator:
Healy, Frederick M.
System:
The UNT Digital Library
The Effect of Compressor-Inlet Water Injection on Engine and Afterburner Performance
"A turbojet engine incorporating a conventional-type afterburner was operated over a range of afterburner pressure levels from 1000 to 2000 pounds per square foot absolute and a range of engine-inlet water-air ratios from 0 to 0.08. At each pressure level and water-air ratio, the afterburner fuel flow was varied from lean blowout to maximum burner-outlet temperature" (p. 1).
Date:
July 22, 1958
Creator:
Sivo, Joseph N.; Wanhainen, John P. & Jones, William L.
System:
The UNT Digital Library
The Effect of Compressor-Inlet Water Injection on Engine and Afterburner Performance
Report presenting testing of a turbojet engine incorporating a conventional-type afterburner over a range of afterburner pressure levels and engine-inlet water-air ratios. At each pressure level and water-air ratio, the afterburner fuel flow was varied from lean blowout to maximum burner-outlet temperature. Results regarding the effects of water vapor on engine performance, effects of water vapor on afterburner performance, and high Mach number performance with water injection are provided.
Date:
July 22, 1958
Creator:
Sivo, Joseph N.; Wanhainen, John P. & Jones, William L.
System:
The UNT Digital Library
Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines
Memorandum presenting performance calculations for hypothetical hydrogen expansion engines in which only a small part of the engine airflow passes through the heat exchanger. The flight path was representative of those for long-range, high-speed aircraft. Results regarding the off-design operation and engine performance are provided.
Date:
July 22, 1958
Creator:
Dugan, James F., Jr.
System:
The UNT Digital Library
Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines
Memorandum presenting performance calculations made for hypothetical hydrogen expansion engines in which only a small part of the engine airflow passes through the heat exchanger. The prescribed flight path was representative of those for long-range, high-speed aircraft. Results regarding the off-design operation and engine performance are provided.
Date:
July 22, 1958
Creator:
Dugan, James F., Jr.
System:
The UNT Digital Library
Performance of Five Short Multielement Turbojet Combustors for Hydrogen Fuel in Quarter-Annulus Duct
Report described five short multielement turbojet combustors for use with hydrogen fuel and their performance. Information about the combustion efficiency, temperature profiles, pressure loss, durability, and comparison with previous short combustors is included.
Date:
July 22, 1958
Creator:
Jones, Robert E. & Rayle, Warren D.
System:
The UNT Digital Library
Performance of five short multielement turbojet combustors for hydrogen fuel in quarter-annulus duct
Report presenting an investigation of five short multielement turbojet combustors designed for use with hydrogen fuel tested in a quarter-annulus duct. One combustor had an array of U-gutter flame-holders, while the other four were manifold arrays of swirl-can combustor elements. Results regarding combustion efficiency, temperature profiles, pressure loss, durability, comparison with previous short combustors, and operation with propane fuel are provided.
Date:
July 22, 1958
Creator:
Jones, Robert E. & Rayle, Warren D.
System:
The UNT Digital Library
Effects of Wing Sweep, Horizontal-Tail Configuration, and a Ventral Fin on Static Stability Characteristics of a Model With a Wing of Aspect Ratio 3 at Mach Numbers From 2.29 to 4.65
Report presenting an investigation to determine the effects on the static longitudinal and lateral stability characteristics of a model with a swept wing of aspect ratio 3, horizontal-tail height and dihedral, and a ventral fin. Tests were performed at a range of angles of attack and Mach numbers.
Date:
July 21, 1958
Creator:
Jaquet, Byron M. & Fournier, Roger H.
System:
The UNT Digital Library
Investigation of the aerodynamic characteristics of a model of a supersonic bomber configuration with a swept and an unswept wing at Mach numbers from 1.79 to 2.67
Report presenting an investigation at Mach numbers of 1.79 to 2.67 on a wing-fuselage combination and on the wing-fuselage combination with a complete tail configuration. Two wing plan forms were investigated on the fuselage, which differed in sweepback and taper ratio.
Date:
July 21, 1958
Creator:
Silvers, H. Norman & Zedekar, Raymond L.
System:
The UNT Digital Library
Operational problems of manned orbital vehicles
Report presenting an exploration of some of the problems of manned orbital vehicles, which introduce many problems in the fields of escape, piloting, orbit selection, flight termination, and range requirements. The effects of some of these problems, including some effects of configuration, are discussed.
Date:
July 21, 1958
Creator:
Drake, Hubert M.; Bellman, Donald R. & Walker, Joseph A.
System:
The UNT Digital Library
Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations
Report presenting some experimental data and calculations for a variety of aerodynamic shapes considered for use as manned reentry vehicles. Three types of vehicles were tested: non-lifting bodies, lifting bodies, and airplane-like vehicles. All of the configuration types were found to be suitable for use as manned reentry vehicles with certain fin and flap modifications for certain shapes.
Date:
July 21, 1958
Creator:
Penland, Jim A. & Armstrong, William O.
System:
The UNT Digital Library
A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds
Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.
Date:
July 21, 1958
Creator:
Heath, Atwood R., Jr. & Igoe, Ann W.
System:
The UNT Digital Library
A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds
Report presenting an investigation of the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination. The model had a wing of aspect ratio 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding chordwise pressure distributions, the effect of ailerons on wing section loadings, the effect of aileron on wing loading, and the effects of a deflected aileron on opposite-wing loading are presented.
Date:
July 21, 1958
Creator:
Heath, Atwood R., Jr. & Igoe, Ann W.
System:
The UNT Digital Library
Evaluation of Some Aerodynamic Controls for a Low Aspect Ratio Missile
"Results of a static stability controls investigation carried out with a very low-aspect-ratio delta-winged missile are presented. Control effectiveness comparisons are made for tail, canard, and nose control configurations with respect to angle of attack, angle of bank, and Mach number. Trim capabilities of the various configurations are also presented" (p. 1).
Date:
July 17, 1958
Creator:
Winovich, Warren & Higdon, Nancy S.
System:
The UNT Digital Library
Heat-Transfer Measurements on a Concave Hemispherical Nose Shape With Unsteady-Flow Effects at Mach Numbers of 1.98 and 4.95
Memorandum presenting heat-transfer rates and pressure fluctuations at Mach numbers of 1.98 and 4.95 measured at the stagnation point of a concave hemisphere for a range of Reynolds numbers based on free-stream conditions and model diameter. Results regarding heat-transfer characteristics, heat-transfer data, and schileren photographs and stagnation point pressure measurements are provided.
Date:
July 17, 1958
Creator:
Cooper, Morton; Beckwith, Ivan E.; Jones, Jim J. & Gallagher, James J.
System:
The UNT Digital Library
Simulator Investigation of Command Reaction Controls
Memorandum presenting an investigation of reaction controls that command velocity and attitude that compares them to the controls that command acceleration. Proportional acceleration reaction controls were found to be satisfactory over a much wide range of control effectiveness than were the on-off acceleration controls. The velocity and attitude controls were found to be superior to either of the acceleration controls.
Date:
July 17, 1958
Creator:
Holleman, Euclid C. & Stillwell, Wendell H.
System:
The UNT Digital Library
Effect of leading-edge-flap deflection on the wing loads, load distributions , and flap hinge moments of the Douglas X-3 research airplane at transonic speeds
Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the wing of the Douglas X-3 research airplane with various leading-edge-flap deflections. The load and hinge-moment characteristics of the leading-edge flap are presented for a range of Mach numbers with and without flap deflection. Results regarding chordwise load distributions, wing-section and wing-panel characteristics, span load and pitching-moment distributions, leading-edge-flap characteristics, and a comparison with wind-tunnel data are provided.
Date:
July 15, 1958
Creator:
Keener, Earl R.; McLeod, Norman J. & Taillon, Norman V.
System:
The UNT Digital Library
Effect of screens in reducing distortion and diffusion length for a 'dump' diffuser at a Mach number of 3.85
Report presenting an investigation of the effect of screens in a dump-type diffuser in the 2- by 2-foot supersonic wind tunnel at Mach number 3.85. Results of a slanted half screen of 0.41 solidity, positioned 0.263 inlet diameter from the cowl lip, are presented on a range basis, as this configuration allows for shortening of the subsonic diffuser.
Date:
July 15, 1958
Creator:
Wasserbauer, Joseph F.
System:
The UNT Digital Library
Experimental ablation cooling
Report presenting the results of an experimental investigation on the ablation of a number of promising materials for heating conditions comparable to those which maybe encountered by unmanned reentry satellite vehicles or heating conditions associated with reentry ballistic missiles. Results regarding exploratory tests, further Teflon tests, and graphite testing are provided.
Date:
July 15, 1958
Creator:
Bond, Aleck C.; Rashis, Bernard & Levin, L. Ross
System:
The UNT Digital Library
Investigation of the Performance and Internal Flow of a Variable-Area, Variable-Internal-Contraction Inlet at Mach Numbers of 2.00, 2.50, and 2.92
Memorandum presenting the performance of a variable-internal-contraction inlet without boundary-layer removal measured at Mach numbers of 2.00, 2.50, and 2.92. The total-pressure recovery at the design Mach number, 2.50, was 0.78. Results regarding total-pressure recovery and contraction ratio, flow unsteadiness and distortion, and summary data correlations are provided.
Date:
July 15, 1958
Creator:
Scherrer, Richard & Anderson, Warren E.
System:
The UNT Digital Library