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Flight and Test-Stand Investigation of High-Performance Fuels in Double-Row Radial Air-Cooled Engines 3: Comparison of Cooling Characteristics of Flight and Test-Stand Engines

Description: Report presenting the cooling characteristics of a 14-cylinder double-row radial air-cooled engines in a test stand and in flight. Three types of cooling tests were made for both engines: variable charge-air flow, variable cooling-air pressure drop, and variable fuel-air ratio. For the same operating conditions, the test-stand engine was found to run consistently cooler than the flight engine.
Date: February 1945
Creator: White, H. Jack; Blackman, Calvin C. & Dandois, Marcel
Partner: UNT Libraries Government Documents Department

High-speed wind-tunnel tests of a 1/14-scale model of a four-engine cargo airplane

Description: Report presenting tests on a scale model of a four-engine cargo airplane, which was tested in the high-speed wind tunnel. The high-speed characteristics of the airplane, particularly the longitudinal stability and control in dives were investigated. Test results indicated that no important changes in longitudinal stability or controllability occurred until the speed exceeded the predicted maximum level-flight speed by more than 38 percent.
Date: February 1943
Creator: Hamilton, William T.
Partner: UNT Libraries Government Documents Department

Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter

Description: From Introduction: "The research program included clean-up tests (unpublished data) and stability and control tests (reference 1) made in the NACA Langley full-scale tunnel. An investigation of the aerodynamic characteristics of the power-plant installation in the Cleveland altitude wind tunnel is discussed in this report."
Date: February 1946
Creator: Preston, G. Merritt; Black, Fred O., Jr. & Jagger, James M.
Partner: UNT Libraries Government Documents Department

Tests of a 1/17-scale model of the XBDR-1 airplane in the NACA gust tunnel

Description: Report presenting tests in the gust tunnel on a scale model of the XBDR-1 airplane to verify the calculated effective gust factor. Tests were made for three gust shapes, one forward velocity, and one wing loading. The test results and analysis were in good agreement and the results of the analysis indicated that there was an appreciable change in effective gust factor for the center-of-gravity movement considered.
Date: February 1944
Creator: Reisert, Thomas D.
Partner: UNT Libraries Government Documents Department

Tests of a 1/14-Scale Powered Model of the XB-36 Airplane in the Langley 19-Foot Pressure Tunnel 1: Stalling Characteristics and Aileron Effectiveness of Several Wing and Flap Arrangements

Description: Report discussing an investigation into the stalling characteristics, aileron effectiveness, and longitudinal stability of a scale model of the XB-36 airplane. The model was tested with the original configuration as well as with several modifications to the outboard panels and flap arrangement.
Date: February 1945
Creator: Alexander, S. R. & Sivells, James C.
Partner: UNT Libraries Government Documents Department

The Effect of Ethylene Dibromide on the Knock-Limited Performance of Leaded and Nonleaded S Reference Fuel

Description: Report discussing testing to determine the effect of ethylene dibromide on the knock-limited performance of S reference fuel. An increase in ethylene-dibromide content did appear to decrease the knock-limited performance of the fuel up to a certain point and at all but the extremes of fuel-air mixtures.
Date: February 1946
Creator: Kinney, George R. & Niemi, Richard O.
Partner: UNT Libraries Government Documents Department

The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine 3: Blends of 2,3-Dimethylpentane With 28-R

Description: Report discussing the knock-limited performance of blends of 2,3-dimethylpentane and 23-R fuel in an F-4 engine at three sets of conditions and three compression ratios. The knock-limited performance of 2,3-dimethylpentane has about the same sensitivity to compression ratio and inlet-air temperature as 28-R fuel.
Date: February 10, 1945
Creator: Alquist, Henry E. & Tower, Leonard K.
Partner: UNT Libraries Government Documents Department

The Effects of a Highly Cambered Low-Drag Wing and of Auxiliary Flaps on the High-Speed Aerodynamic Characteristics of a Twin-Engine Pursuit Airplane Model

Description: Results are presented for tests of two wings, an NACA 230-series wing and a highly-cambered NACA 66-series wing on a twin-engine pursuit airplane. Auxiliary control flaps were tested in combinations with each wing. Data showing comparison of high-speed aerodynamic characteristics of the model when equipped with each wing, the effect of the auxiliary control flaps on aerodynamic characteristics, and elevator effectiveness for the model with the 66-series wing are presented. High-speed aerodynamic characteristics of the model were improved with the 66-series wing.
Date: February 19, 1944
Creator: Ganzer, Victor M.
Partner: UNT Libraries Government Documents Department

Cooling of a Double-Row Radial Engine by Water Injection to the Individual Cylinders

Description: "An injection system that supplies water to each cylinder of a double-row radial engine was tested...as part of a general investigation of the power-plant installation of a four-engine heavy bomber. The tests were conducted to determine the effectiveness of water injection in cooling the engine during take-off. The injection of 500 pounds of water at the take-off power condition reduced the maximum measured exhaust-valve-seat temperature 64 degrees Fahrenheit and the maximum spark-plug-gasket temperature 55 degrees Fahrenheit" (p. 1).
Date: February 1945
Creator: Monroe, Louis L. & Friedman, Harold E.
Partner: UNT Libraries Government Documents Department

Calibrations of Service Pitot Tubes in the Langley 24-Inch High-Speed Tunnel

Description: Report discusses calibration testing performed on a Kollsman type G-1 and an NAF No. 1 pitot tube at several Mach numbers and angles of attack. The effect of drain holes on the flow within the pitot tube was analyzed and the ability to estimate the error in the total pressure was created. The accuracy of the extrapolated and estimated values were found to be within reasonable limits.
Date: February 1946
Creator: Lindsey, W. F.
Partner: UNT Libraries Government Documents Department

Knock-Limited Blending Characteristics of Benzene, Toluene, Mixed Xylenes, and Cumene in an Air-Cooled Cylinder

Description: "An investigation was conducted to determine the knock-limited blending characteristics of leaded fuels containing selected aromatic fuel components (benzene, toluene, mixed xylenes, and cumene). Each of the aromatics was blended with an alkylate blending agent and with a virgin base stock. The blending characteristics of the resulting fuels were determined in a full-scale aircraft-engine cylinder" (p. 1).
Date: February 3, 1945
Creator: Hensley, Reece V. & Breitwieser, Roland
Partner: UNT Libraries Government Documents Department

Flight Measurements of the Flying Qualities of an F6F-3 Airplane (BuAer No. 04776) 2: Lateral and Directional Stability and Control

Description: Report discussing the lateral and directional stability and control of the F6F-3 airplane in a variety of flying conditions. Information about the control-free lateral oscillations, aileron control characteristics, maximum sideslip, dihedral effect, blow-up characteristics of the landing flaps, rudder, pitching moment, and power of the rudder trim tab and aileron trim tab is included.
Date: February 13, 1945
Creator: Williams, Walter C. & Reeder, John P.
Partner: UNT Libraries Government Documents Department

Flight Measurements of the Flying Qualities of an F6F-3 Airplane (BuAer No. 04776) 1: Longitudinal Stability and Control

Description: Report discussing flight measurements of the handling qualities of an F6F-3 obtained over the course of thirty flights and under a variety of conditions. The longitudinal stability and control of the plane were found to be satisfactory by the test pilots. Information about the elevator control, flaps, and the longitudinal trimming device is provided in greater detail.
Date: February 13, 1945
Creator: Williams, Walter C. & Reeder, John P.
Partner: UNT Libraries Government Documents Department

Generalized performance selection charts for single-engine pursuit airplanes

Description: Report presenting an investigation of the effect of wing loading, power loading, and aspect ratio on the performance of pursuit airplanes. The study is based on data combined from specifications, wind-tunnel, and flight tests of various airplanes and presented in graphs.
Date: February 1943
Creator: Ivey, H. Reese; Stickle, George W. & Brevoort, Maurice J.
Partner: UNT Libraries Government Documents Department

Flutter tests on SB2U model in 16-foot tunnel

Description: Report presenting testing of the flutter characteristics of the SB2U-2 airplane. The secondary purpose of the test, which ended up being the primary purpose, was to study the behavior of the airplane just below the flutter speed. Results regarding flutter amplitude, frequencies, and energy-absorbing qualities are provided.
Date: February 1943
Creator: Theodorsen, Theodore; Coleman, R. P. & Smith, N. H.
Partner: UNT Libraries Government Documents Department