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Investigation of Supersonic-Compressor Rotors Designed with External Compression

Description: Report presenting an investigation of the possibility of utilizing the relatively good characteristics of the spike-type diffuser in the supersonic compressor. Results regarding the overall performance, inlet conditions, outlet conditions, entrance flow conditions, and estimated performance of subsonic portion of rotor passage are provided.
Date: September 24, 1954
Creator: Jahnsen, Lawrence J. & Hartmann, Melvin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of ground on the low-speed aerodynamics control, and control hinge-moment characteristics of a delta-wing-fuselage model with trailing-edge controls

Description: Report presenting an investigation to determine the effect of ground on the low-speed aerodynamic, control, and control hinge-moment characteristics of a 3-percent-thick, delta-wing-fuselage configuration. Aerodynamic forces and moments and hinge-moment data were obtained for a range of angles of attack, ground heights, and a designated Mach and Reynolds number.
Date: September 24, 1954
Creator: Scallion, William I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at supersonic speed (M = 1.53) of the pressure distribution over a 63 degrees swept airfoil of biconvex section at several angles of attack

Description: Report presenting the results of an investigation at supersonic speed of the distribution of pressure over the surface of a swept airfoil of biconvex section at various angles of attack. The measurements are compared with supersonic lifting-surface theory, which generally indicated good agreement except over the regions of the airfoil influenced by the subsonic trailing edge and the tips. Results regarding the pressure distribution, boundary-layer studies, and normal force and pitching moment a… more
Date: September 24, 1948
Creator: Katzen, Elliott D.; Frick, Charles W. & Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination and Use of the Local Recovery Factor for Calculating the Effectiveness Gas Temperature for Turbine Blades

Description: In an experimental investigation of local recovery factors for a blade having a pressure distribution similar to that of a typical reaction-type turbine blade, it a was found that the recovery factors were essentially independent of Mach number, Reynolds number, pressure gradient, and position on the blade surface except for regions where the boundary layer was probably in the transition range from laminar to turbulent. The recommended value of local subsonic recovery factor for use in calculat… more
Date: September 24, 1951
Creator: Esgar, Jack B. & Lea, Alfred L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effect of a Nacelle at Various Chordwise and Vertical Positions on the Aerodynamic Characteristics at High Subsonic Speeds of a 45 Degrees Sweptback Wing With and Without a Fuselage

Description: Report presenting an investigation of a nacelle at various chordwise positions and vertical locations on a semispan model of a wing with and without a fuselage through a range of Mach numbers. The investigation was made to determine the interference characteristics between the nacelle and the model and to determine the effect of the fuselage on nacelle interference.
Date: September 24, 1951
Creator: Silvers, H. Norman; King, Thomas J., Jr. & Pasteur, Thomas B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Use of the Rolled-Up Vortex Concept for Predicting Wing-Tail Interference and Comparison With Experiment at Mach Number of 1.62 for a Series of Missile Configurations Having Tandem Cruciform Lifting Surfaces

Description: Report presenting a method for predicting wing-tail interference as applied to the calculation of tail efficiency parameters, lift characteristics, and center-of-pressure locations for a series of generalized missile configurations. The calculations are also compared to experimental data. The rolled-up vortex concept appears to give good results in the prediction of tail efficiency with angle of attack for inline configurations.
Date: September 24, 1952
Creator: Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of an annular turbojet combustor having reduced pressure losses and using propane fuel

Description: Report presenting an investigation to develop a high-combustion-efficiency turbojet combustor with pressure losses typical of those encountered in current turbojet engines. A total of 13 air-entry hole modifications was investigated to obtain a combustor design with high combustion efficiencies and a satisfactory outlet radial temperature profile. Results regarding combustor development and the performance of Model 28I are provided.
Date: September 24, 1953
Creator: Norgren, Carl T. & Childs, J. Howard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Correlation of Flight and Wind-Tunnel Measurements of Roll-Off in Low-Speed Stalls on a 35 Degree Swept-Wing Aircraft

Description: Memorandum presenting flight and wind-tunnel measurements made of the low-speed stalling characteristics on a swept-wing jet aircraft. Included in the study are the effects on the stalling characteristics of a number of wing modifications. Results regarding the roll-off characteristics and maximum lift and stalling characteristics are provided.
Date: September 24, 1953
Creator: Anderson, Seth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of noise field and velocity profiles of an afterburning engine

Description: Report presenting sound pressure levels, frequency spectrum, and jet velocity profiles for an engine-afterburner combination at various values of afterburner fuel-air ratio. Lower sound pressure levels were obtained from a current fighter aircraft with a different afterburner configuration. Results regarding the jet temperature, jet Mach number and velocity, and sound measurements are provided.
Date: September 24, 1954
Creator: North, Warren J.; Callaghan, Edmund E. & Lanzo, Chester D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Measurements of Wing Buffeting on 1/16-Scale Model of Douglas D-558-II Research Airplane

Description: Report presenting exploratory measurements of the fluctuations of wing bending moment during normal performance and wind-tunnel testing of a model of the Douglas D-558-II from Mach numbers 0.60 to 0.96. The effects of leading-edge chord-extensions and pylon-mounted underwing external stores were investigated. Results regarding the general nature of buffeting measurements, frequency distribution of buffeting response, interpretation of model buffeting measurements, and effects of changes in mode… more
Date: September 24, 1956
Creator: Kemp, William B., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies

Description: From Introduction: "Presented in this report are the basic data obtained from investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbody design."
Date: September 24, 1956
Creator: Henry, Beverly Z., Jr. & Cahn, Maurice S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of hydrogen fuel in a full-scale afterburner

Description: Report presenting a performance investigation using hydrogen fuel in a full-scale afterburner with particular study of fuel-injector configurations and afterburner length. A total of seven fuel-injector configurations, some concentric ring and some radial bar, were investigated at a specified burner inlet velocity over a range of burner-inlet total pressures.
Date: September 24, 1957
Creator: Groesbeck, Donald E.; Prince, William R. & Ciepluch, Carl C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of a Determination of Temperatures of Flames by Means of K-Band Microwave Attenuation

Description: "The temperature effects on the attenuation of K-band microwaves, at a frequency of 26,500 plus or minus 30 megacycles per second, through natural-gas and propane flames containing added alkali halide salts, were investigated over a temperature range from 1900 to 2500 K. The preliminary data of this investigation indicated that the attenuation varies appreciably with the sodium-line-reversal temperatures of the flames and is independent of the particular hydrocarbon fuels that were used for tem… more
Date: September 24, 1951
Creator: Rudlin, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of nitrogen tetroxide and water concentration on freezing point and ignition delay of fuming nitric acid

Description: Report presenting an investigation of the interrelated effects of water and nitrogen tetroxide in fuming nitric acid with respect to the freezing points of the acid and ignition delays with several fuels. Results regarding freezing-point experiments, ignition-delay experiments, coincidence of acid compositions giving low freezing points and short ignition delays, and hypotheses on the opposing effects of nitrogen tetroxide and water on ignition delay are provided.
Date: September 24, 1953
Creator: Miller, Riley O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of the Minimum Drag of Two Versions of a Modified Delta-Wing Fighter as Obtained From Flight Tests of Rocket-Boosted Models and Equivalent Bodies Between Mach Numbers of 0.80 and 1.64

Description: Report presenting an investigation to determine the reduction in minimum drag that could be obtained at supersonic speeds by redesigning the fuselage and reducing the wing and tail thickness of a modified delta-wing fighter-type airplane. Results regarding the mass-flow ratio, total-pressure recovery, and drag are provided.
Date: September 24, 1956
Creator: Hastings, Earl C., Jr. & Mitcham, Grady L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cooling Characteristics of the V-1650-7 Engine 2 - Effect of Coolant Conditions on Cylinder Temperatures and Heat Rejection at Several Engine Powers

Description: From Summary: "An investigation has been conducted on a V-1650-7 engine to determine the cylinder temperatures and the coolant and oil heat rejections over a range of coolant flows (50 to 200 gal/min) and oil inlet temperatures (160 to 2150 F) for two values of coolant outlet temperature (250 deg and 275 F) at each of four power conditions ranging from approximately 1100 to 2000 brake horsepower. Data were obtained for several values of block-outlet pressure at each of the two coolant outlet te… more
Date: September 24, 1947
Creator: Povolny, John H.; Bogdan, Louis J. & Chelko, Louis J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tank Investigation of the EDO Model 142 Hydro-Ski Research Airplane

Description: A tank investigation has been conducted of a 1/10-size powered-dynamic model of the Edo model 142 hydra-ski research airplane. The results of tests of two configurations are presented: One included a large ski and a ski well; the other, a small ski without a well. Water take-offs would be possible with the available thrust for either configuration: however, the configuration with the large ski emerged sooner and had less resistance from ski emergence until take-off. Longitudinal stability and l… more
Date: September 24, 1951
Creator: Ramsen, John A.; Wadlin, Kenneth L. & Gray, George R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Experimental Investigation of Sting-Support Effects on Drag and a Comparison with Jet Effects at Transonic Speeds

Description: "This paper presents the results of an investigation of sting-support interference on afterbody drag at transonic speeds. Stings with varying diameter, cone angle, and cylindrical length were tested at the rear of a model with various afterbody shapes. The data were obtained at an angle of attack of 0 deg. and at Mach numbers from 0.80 to 1.10. It was found that, in general, the addition of a sting caused a drag reduction" (p. 1).
Date: September 24, 1956
Creator: Cahn, Maurice S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration-Cooled Walls with Application to Turbine Blade Cooling

Description: An approximate method for development of flow and thermal boundary layers in laminar regime on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout boundary layer is assumed. Shape parameters for approximated velocity and temperature profiles and functions necessary for solution of boundary-layer equations are presented as… more
Date: September 24, 1951
Creator: Eckert, E. R. G. & Livingood, John N. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Noise Field and Velocity Profiles of an Afterburning Engine

Description: From Summary: "Sound pressure levels, frequency spectrum, and jet velocity profiles are presented for an engine-afterburner combination at various values of afterburner fuel - air ratio. At the high fuel-air ratios, severe low-frequency resonance was encountered which represented more than half the total energy in the sound spectrum. At similar thrust conditions, lower sound pressure levels were obtained from a current fighter air craft with a different afterburner configuration. The lower soun… more
Date: September 24, 1954
Creator: North, Warren J.; Callaghan, Edmund E. & Lanzo, Chester D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of Hydrogen Fuel in a Full-Scale Afterburner

Description: Memorandum presenting a performance investigation using hydrogen fuel in a full-scale afterburner conducted with particular study of fuel-injector configurations and afterburner length. A total of seven fuel-injector configurations, grouped by type as concentric ring or radial bar, were investigated at a specified burner-inlet velocity and range of burner-inlet total pressures.
Date: September 24, 1957
Creator: Groesbeck, Donald E.; Prince, William R. & Ciepluch, Carl C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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