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Free-jet tests of a 6.5-inch-diameter ram-jet engine at Mach numbers 1.81 and 2.00

Description: Report presenting testing of a 6.5-inch-diameter ramjet engine with a design Mach number of 2.13 and a short-flame-length combustor. Performance characteristics are provided for a range of Mach numbers and fuel-air ratios. Results regarding thrust, drag tests, static pressure, and combustion efficiencies are provided.
Date: March 7, 1951
Creator: Faget, Maxime A.; Watson, Raymond S. & Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department

Effect of formation position on load factors obtained on F2H airplanes

Description: Report presenting results of a four-plane formation flight with twelve pull-up maneuvers in the form of plots of maximum load factor attained versus airplane position for three combinations of four F2H airplanes. The load factor was generally found to increase toward the end of the formation, and movements of the lead plane that are too sharp might cause excessive loads on the last plane in the formation.
Date: December 7, 1951
Creator: Huss, Carl R. & Hamer, Harold A.
Partner: UNT Libraries Government Documents Department

A wind-tunnel investigation of the static stability characteristics of a 1/8-scale ejectable pilot-seat combination at a Mach number of 0.8

Description: Report presenting an investigation of a model of an ejectable pilot seat combination with and without stabilizing fins. The main purpose of the investigation was to determine the static aerodynamic characteristics and effectiveness of various stabilizing fins at a high subsonic Mach number. Results regarding stability and force characteristics for the combinations are provided.
Date: December 7, 1951
Creator: Visconti, Fioravante & Nuber, Robert J.
Partner: UNT Libraries Government Documents Department

Hydrodynamic investigation of a 1/13-scale model of the consolidated vultee skate 7 seaplane equipped with twin hydro-skis : TED No. NACA DE 342

Description: Report presenting an investigation in Langley tank no. 2 to determine the hydrodynamic characteristics of the Consolidated Vultee Skate 7 seaplane with twin hydro-skis suitable for use on water or snow. Results regarding the take-off stability in smooth and rough water, landing stability, spray characteristics, and resistance are provided.
Date: November 7, 1951
Creator: McKann, Robert E.; Coffee, Claude W. & Arabian, Donald D.
Partner: UNT Libraries Government Documents Department

Cooperative Investigation of Relationship Between Static and Fatigue Properties of Heat-Resistant Alloys at Elevated Temperatures

Description: Memorandum presenting a study of the relationship between the static and dynamic properties of heat-resistant alloys at high temperatures. An auxiliary objective is to provide a better basis for evaluating the results from the various types of fatigue machines.
Date: March 7, 1951
Creator: NACA Subcommittee on Heat-Resisting Materials
Partner: UNT Libraries Government Documents Department

Investigation of Turbine-Outlet Temperature Distribution of XJ34-WE-32 Turbojet Engine

Description: Turbine-outlet radial temperature distributions of an XJ34-WE-32 turbojet engine were investigated in the altitude wind tunnel at the NACA Lewis laboratory over a range of pressure altitudes, engine-inlet air temperatures and flight Mach numbers at or near rated engine conditions. From blade stress considerations, the turbine-outlet temperature distribution was considered satisfactory at altitudes up to 25,000 feet at corrected engine speeds corresponding to rated speed (12,500 rpm); however, operation at either higher corrected engine speeds or higher altitudes resulted in an inversion of the turbine temperature distribution that was detrimental to turbine life. Installation of a compressor-outlet mixer greatly improved the turbine radial temperature distribution.
Date: November 7, 1951
Creator: Prince, W. R. & Wintler, J. T.
Partner: UNT Libraries Government Documents Department

Investigation of off-design performance of shock-in-rotor type supersonic blading

Description: An analysis of the off-design performance of shock-in rotor-type supersonic blading is presented. The over-all losses are assumed divided into two groups;normal-shock losses, and external-wave losses. Throughout the range of relative entrance Mach numbers from 1.35 to starting, the largest losses can be attributed to the normal shock. An improvement in performance would be expected with a reduction of the normal-shock losses by the introduction of external compression waves.
Date: May 7, 1951
Creator: Graham, Robert C.; Klapproth, John F. & Barina, Frank J.
Partner: UNT Libraries Government Documents Department

Correlation of supersonic convective heat-transfer coefficients from measurements of the skin temperature of a parabolic body of revolution (NACA RM-10)

Description: Report presenting local coefficients of convective heat transfer as measured from skin temperature along the body of an RM-10 NACA research missile, which consisted of a parabolic body of revolution. Results regarding recovery factors, adiabatic wall temperatures, Nusselts, Prandtl, and Reynolds numbers, and boundary-layer transition are provided.
Date: March 7, 1951
Creator: Chauvin, Leo T. & de Moraes, Carlos A.
Partner: UNT Libraries Government Documents Department

Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with self-supporting free-floating fuel tanks attached to the wing tips

Description: Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with self-supporting, free-floating fuel tanks attached to the wing tips. The results showed that the flight behavior of the configuration could be made satisfactory when sufficient restoring moment was supplied. Results regarding the flight behavior, rolling motions, motions of the bomber and attached tanks, and flight records for different gearing ratios are provided.
Date: August 7, 1951
Creator: Bennett, Charles V. & Cadman, Robert B.
Partner: UNT Libraries Government Documents Department

An investigation of single-degree-of-freedom snaking oscillations on a model of a high-speed research airplane by the NACA wing-flow method

Description: Report presenting an investigation by the wing-flow method to determine the snaking characteristics of a scale partial-model of a research airplane. Additionally, the snaking characteristics of 11 modified configurations of the research-airplane model were determined as well as a model that had a greater fineness ratio.
Date: August 7, 1951
Creator: Johnson, Harold I. & Faber, Stanley
Partner: UNT Libraries Government Documents Department

An investigation of the effect of vertical-fin location and area on low-speed lateral stability derivatives of a semitailless airplane model

Description: Report presenting the effects of a low-speed wind-tunnel investigation to determine the effects of vertical-fin location and area on the static and rotary lateral stability characteristics of semitailless airplane models. Results regarding straight flow, yawing flow, and rolling flow are provided.
Date: March 7, 1951
Creator: Fisher, Lewis R. & Michael, William H., Jr.
Partner: UNT Libraries Government Documents Department

Tank investigation of the Grumman JRF-5 airplane with a single hydro-ski and an extended afterbody

Description: Report presenting results from a tank investigation of a powered dynamic model of the Grumman JRF-5 airplane fitted with a single hydro-ski and extended afterbody. Results indicated that the afterbody extension in place of a tail ski reduced the maximum resistance by 10 percent. Removal of the wing-tip skids gave a further reduction in maximum resistance of 3 percent.
Date: August 7, 1951
Creator: Ramsen, John A. & Gray, George R.
Partner: UNT Libraries Government Documents Department

Average skin-friction coefficients from boundary-layer measurements in flight on a parabolic body of revolution (NACA RM-10) at supersonic speeds and at large Reynolds numbers

Description: Report presenting boundary-layer measurements on rocket-powered free-flight models to determine average skin-friction coefficients. The test body, NACA RM-10, was a fin-stabilized parabolic body of revolution of fineness ratio 12.2 with a blunt base to provide space for a rocket jet. Results regarding the skin-friction and boundary-layer profiles and experimental and theoretical curves are provided.
Date: March 7, 1951
Creator: Rumsey, Charles B. & Loposer, J. Dan
Partner: UNT Libraries Government Documents Department

Langley 9-Inch Supersonic Tunnel Tests of Several Modifications of a Supersonic Missile Having Tandem Cruciform Lifting Surfaces: Three-Component Data Results of Models Having Ratios of Wing Span to Tail Span Equal to 1

Description: Memorandum presenting tests in the 9-inch supersonic tunnel to investigate the factors that determine the magnitude of the wing-tail interference effects on the static longitudinal stability of supersonic missile configurations with low-aspect-ratio, tandem, cruciform lifting surfaces and to develop a missile configuration with a minimum variation in static margin due to wing-tail interference effects.
Date: March 7, 1951
Creator: Rainey, Robert W.
Partner: UNT Libraries Government Documents Department

Langley 9-Inch Supersonic Tunnel Tests of Several Modifications of a Supersonic Missile Having Tandem Cruciform Lifting Surfaces: Three-Component Data Results of Models Having Ratios of Wing Span to Tail Span Equal to and Less Than 1 and Some Static Rolling-Moment Data

Description: Memorandum presenting lift, drag, and pitching-moment data and some static rolling-moment data are presented for missile configurations having wing-tail-span ratios equal to and less than 1. The configurations include variations in wing and tail plan forms, wing-tail-span ratios, body length, and nose shape.
Date: March 7, 1951
Creator: Rainey, Robert W.
Partner: UNT Libraries Government Documents Department