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Wind Tunnel Investigation at Low Speed of Aerodynamic Characteristics of Army Chemical Corps Model E-112 Bomblets with Span Chord Ratio of 2 - 1

Description: "An experimental investigation has been made in the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E-112 bomblets with span-chord ratio of 2:1. A detailed analysis has not been made; however, the results showed that all the models were spirally unstable and that a large gap between the model tips and end plates tended to reduce the instability" (p. 1).
Date: December 26, 1956
Creator: Letko, William
Partner: UNT Libraries Government Documents Department

Pressure Distributions and Aerodynamic Characteristics of Several Spoiler-type Controls on a Trapezoidal Wing at Mach Numbers of 1.61 and 2.01

Description: Memorandum presenting an investigation at Mach numbers of 1.61 and 2.01 to examine the characteristics of a series of nine spoiler-type controls on a trapezoidal wing with the leading edge swept back 23 degrees, an aspect ratio of 3.1, and a taper ratio of 0.4. Results regarding pressure distributions, spanwise loadings, and integrated coefficients are provided.
Date: July 26, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
Partner: UNT Libraries Government Documents Department

Full-Scale Wind-Tunnel Tests of a 35 Degree Swept-Wing Fighter Airplane With a Spoiler-Slot-Deflector Lateral Control System

Description: Memorandum presenting an investigation to determine the low-speed aerodynamic characteristics of a 35 degree swept-wing fighter airplane with a segmented spoiler-slot deflector lateral control system installed ahead of the conventional ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the airplane and spoiler-slot-deflector effectiveness data were obtained through the complete angle-of-attack range with the ailerons neutral and with the ailerons drooped in conjunction with the normal flaps. Results regarding longitudinal characteristics, spoiler-deflector characteristics, and hinge-moment characteristics are provided.
Date: October 26, 1956
Creator: Scallion, William I.
Partner: UNT Libraries Government Documents Department

Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds

Description: Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.
Date: October 26, 1956
Creator: Jorgensen, Leland H. & Katzen, Elliott D.
Partner: UNT Libraries Government Documents Department

An Investigation of Ejection Releases of Submerged and Semisubmerged Dynamically Scaled Stores From a Simulated Bomb Bay of a Fighter-Bomber Airplane at Supersonic Speeds

Description: Report presenting an investigation of the release characteristics of several dynamically scaled store shapes from a simulated bomb bay at Mach numbers of 1.39, 1.60, and 1.98. A streamline store, a blunt-nose store with wedge-type fins of low aspect ratio, and a bluff store with a skirt were tested. Results regarding pitching motions, ejection velocity, effect of increase in altitude, and addition of plate or spike to the nose of the store are provided.
Date: December 26, 1956
Creator: Lee, John B. & Carter, Howard S.
Partner: UNT Libraries Government Documents Department

Investigation of a 1/22-Scale of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Static Longitudinal Stability and Control and Performance Characteristics at Transonic Speeds

Description: Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 in the transonic tunnel at Mach numbers from 0.60 to 1.13. Results in this report include the static longitudinal stability and control characteristics, the effect of various configuration modifications on lift-drag ratio, the effect of subsonic and supersonic inlets and external stores, and the effect of area-distribution modifications on performance.
Date: April 26, 1956
Creator: Luoma, Arvo A.
Partner: UNT Libraries Government Documents Department

High-temperature oxidation and ignition of metals

Description: "A study of the high-temperature oxidation of several aircraft construction materials was undertaken to assess the possibility of ignition under high-temperature flight conditions.Tests have been made both in open and closed jets, and, in addition, the burning of metals has been observed under static conditions in a pressurized vessel containing either air, oxygen, or nitrogen. When heated in an atmosphere of oxygen or when heated and plunged into a supersonic airstream, titanium, iron, carbon steel, and common alloys such as 4130 were found to have spontaneous-ignition temperatures in the solid phase (below melting) and they melted rapidly while burning" (p. 1).
Date: March 26, 1956
Creator: Hill, Paul R.; Adamson, David; Foland, Douglas H. & Bressette, Walter E.
Partner: UNT Libraries Government Documents Department

Measurements of Boundary-Layer Transition at Low Speed on Two Bodies of Revolution in a Low-Turbulence Wind Tunnel

Description: Memorandum presenting an investigation of the location of transition from laminar to turbulent flow in the boundary layer on two bodies of revolution at zero angle of attack in a low-turbulence wind tunnel. One body was a prolate spheroid of fineness ratio 9.0 made out of aluminum and the other was a modified prolate spheroid of fineness ratio 7.5 made out of steel and covered with fiberglass and resin.
Date: September 26, 1956
Creator: Boltz, Frederick W.; Kenyon, George C. & Allen, Clyde Q.
Partner: UNT Libraries Government Documents Department

Light Diffusion Through High-Speed Turbulent Boundary Layers

Description: Memorandum presenting the optical transmission characteristics of turbulent boundary layers in air on a flat plate with negligible heat transfer measured photometrically for ranges of Mach number from 0.4 to 2.5. The results indicated that the scattering from a collimated beam of white light which penetrates a turbulent boundary layer depends mainly on the integral across the layer of the difference between the free-stream density and the local boundary-layer density.
Date: May 26, 1956
Creator: Stine, Howard A. & Winovich, Warren
Partner: UNT Libraries Government Documents Department

Supersonic-Area-Rule Design and Rocket-Propelled Flight Investigation of a Zero-Lift Straight-Wing-Body-Nacelle Configuration Between Mach Numbers 0.8 and 1.53

Description: Memorandum presenting an application of the supersonic area rule concept to the deign of a straight-wing-body combination with large symmetrically mounted nacelles located at the 70-percent-semispan station. The pressure drag from the configuration with nacelles was found to be significantly less than that from a corresponding configuration without nacelles throughout the Mach number range.
Date: April 26, 1956
Creator: Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Investigation of unsteady flow past four NACA 6-percent-thick airfoil sections

Description: Report presenting an investigation of the intensity of root-mean-square pressure pulsations and root-mean-square normal-force-coefficient fluctuations conducted on two high-lift airfoils and two 6-series airfoils. Results regarding the factors affecting comparison of data from various test facilities, root-mean-square pressure pulsations, and root-mean-square force fluctuations are provided.
Date: July 26, 1956
Creator: Lindsey, Walter F. & Ladson, Charles L.
Partner: UNT Libraries Government Documents Department

Analysis of some parameters used in correlating blowing-type boundary-layer control data

Description: Report presenting an examination of the limitations of the use of jet momentum coefficient as a correlating factor in comparing tests of blowing-type boundary-layer control. Theoretical and experimental data indicate that it should be an acceptable parameter where the duct pressures are large.
Date: September 26, 1956
Creator: Kelly, Mark W.
Partner: UNT Libraries Government Documents Department

Aerodynamic heat transfer and zero-lift of a flat windshield canopy on the NACA RM-10 research vehicle at high Reynolds numbers for a flight Mach number range from 1.5 to 3.0

Description: Report presenting the aerodynamic heat-transfer properties and zero-lift drag of a typical pilot's canopy as determined by a rocket-model flight test through a range of Mach and Reynolds numbers. The canopy had a 63 degree sweptback flat windshield, circular cross section, and an equivalent body fineness ratio of 7.0. Results regarding the canopy temperature distribution, canopy pressure distribution, heat-transfer coefficient, and drag are provided.
Date: September 26, 1956
Creator: Hoffman, Sherwood & Chauvin, Leo T.
Partner: UNT Libraries Government Documents Department

Free-flight investigation of the control effectiveness of a differentially deflected horizontal tail at Mach numbers from 0.8 to 1.6

Description: Report presenting a free-flight investigation of the control effectiveness of a differentially deflected horizontal tail. The results were compared with and found to be in general agreement with estimates derived from other free-flight tests, wind tunnel tests, and theory. Results regarding the rolling moment, yawing moment, and overall rolling effectiveness are provided.
Date: April 26, 1956
Creator: Mitchell, Jesse L. & Vitale, A. James
Partner: UNT Libraries Government Documents Department

Pressure distributions and aerodynamic characteristics of several spoiler-type controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at two Mach numbers to examine the characteristics of a series of nine spoiler-type controls on a trapezoidal wing with the leading edge swept back 23 degrees, an aspect ratio of 3.1, and a taper ratio of 0.4. Results of the tests indicated that the incremental pressure distributions due to spoiler were in agreement with previous results as long as the spoiler was not too close to a break in the wing surface or the wing tip.
Date: July 26, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
Partner: UNT Libraries Government Documents Department

Injection principles for liquid oxygen and heptane using two-element injectors

Description: Report presenting a study of injection principles for liquid oxygen and heptane made with two-element injectors, as the previous study only included single-element injectors. Eight injectors, produced by two spray orientations of each of the four injection processes, were investigated. Results regarding atomization after mixing, atomization before mixing, atomization without mixing, fuel atomization without mixing, and overall comparisons of the injectors are provided.
Date: June 26, 1956
Creator: Heidmann, Marcus F.
Partner: UNT Libraries Government Documents Department

Full-scale wind-tunnel tests of a 35 degree swept-wing fighter airplane with a spoiler-slot-deflector lateral control system

Description: Report presenting an investigation to determine the low-speed aerodynamic characteristics of a 35 degree swept-wing fighter airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of conventional ailerons and operated as both individual units and combined segments. Results regarding longitudinal characteristics, spoiler-deflector characteristics, and hinge-moment characteristics are provided.
Date: October 26, 1956
Creator: Scallion, William I.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the damping in roll of the Bell X-1E research airplane and its components at supersonic speeds

Description: Experimental values of damping in roll at zero angle of attack of the Bell X-1E research airplane and various combinations of components were obtained at 5 different Mach numbers. The damping in roll of the model was of the order predicted by theory. Results regarding the contributions of the airplane components and comparisons of experimental values with theoretical values are provided.
Date: April 26, 1956
Creator: McDearmon, Russell W. & Clark, Frank L.
Partner: UNT Libraries Government Documents Department

Wind-tunnel tests of blowing boundary-layer control with jet pressure ratios up to 9.5 on the trailing-edge flaps of a 35 degree sweptback wing airplane

Description: Report presenting a full-scale wind-tunnel investigation to determine whether the effects of blowing high-velocity air over trailing-edge flaps could be adequately correlated by jet momentum over a range of jet velocities. Good correlation of lift with jet momentum was obtained over the range of jet pressure ratios.
Date: October 26, 1956
Creator: Kelly, Mark W. & Tucker, Jeffrey H.
Partner: UNT Libraries Government Documents Department

A theoretical study of the lifting efficiency at supersonic speeds of wings utilizing indirect lift induced by vertical surfaces

Description: Report presenting a theoretical study of the possibility of improving the lifting efficiency of aircraft flying at supersonic speeds using indirect lift, which can be induced on the wing by the fuselage shape and/or wing end plates. Results indicated that lifting efficiency of a planar wing may be improved by favorable interference induced by lateral forces on the end plates or on the sides of the fuselage.
Date: March 26, 1956
Creator: Rossow, Vernon J.
Partner: UNT Libraries Government Documents Department

Investigation at high subsonic speeds of some effects of sideslip on the aerodynamic loads on finned and unfinned bodies mounted from the wing of a swept-wing-fuselage model

Description: Report presenting an investigation in the high-speed 7- by 10-foot tunnel at a range of Mach numbers to determine the aerodynamic loads on finned and unfinned bodies in the presence of a swept wing. A tip-mounted body at 1.04 semispan and an underwing pylon-mounted body at 0.33 semispan were investigated. Results regarding the body loading characteristics and effect of angle of attack are provided.
Date: April 26, 1956
Creator: King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the effect of aspect ratio and chordwise location on effectiveness of plain spoilers on thin untapered wings at transonic speeds

Description: From Summary: "A wind-tunnel investigation has been made in the Langley high-speed 7- by 10-foot wind tunnel by use of the transonic-bump technique to study the effectiveness of spoiler-type controls on 9 unswept untapered wings. Full-span spoilers, projected to 7.5 percent wing chord along the 40-, 60-, 80-, and 100-percent wing chord lines, were tested on wings of aspect ratio 1 to 6 at Mach numbers from 0.6 to 1.10. Most of the data are presented without analysis."
Date: September 26, 1956
Creator: Hammond, Alexander D.
Partner: UNT Libraries Government Documents Department

External-stream effects on gross thrust and pumping characteristics of ejectors operating at off-design Mach numbers

Description: Report presenting an investigation in the 8- by 6-foot supersonic tunnel to determine the external-stream effects on the gross thrust and pumping characteristics of ejectors operating at off-design Mach numbers. Results regarding the pumping, thrust, and base characteristics, boattail drag characteristics, and stream effects on jet thrust for typical ejector installations are provided.
Date: June 26, 1956
Creator: Valerino, Alfred S. & Yeager, Richard A.
Partner: UNT Libraries Government Documents Department