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Wind-tunnel tests of single- and dual-rotating pusher propellers having from three to eight blades

Description: Report presenting tests of 10-foot-diameter, single- and dual-rotating pusher propellers with three to eight blades that were conducted in the 20-foot propeller research tunnel as a continuation of previous investigations of tractor propellers. The propellers were mounted at the rear end of a streamline body in spinners that covered the hubs and part of the shanks. The effects as compared to previous testing differed only in degree of effect size.
Date: February 1942
Creator: Gray, W. H.
Partner: UNT Libraries Government Documents Department

Investigation of flow in an axially symmetrical heated jet of air

Description: The work done under this contract falls essentially into two parts: the first part was the design and construction of the equipment and the running of preliminary tests on the 3-inch jet, carried out by Mr. Carl Thiele in 1940; the second part consisting in the measurement in the 1-inch jet flow in an axially symmetrical heated jet of air. (author).
Date: December 1, 1943
Creator: Corrsin, Stanley
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of control-surface characteristics 17: beveled-trailing-edge flaps of 0.20, 0.30, and 0.40 airfoil chord on an NACA 0009 airfoil

Description: Report presenting force tests in two-dimensional flow in the 4- by 6-foot vertical tunnel to determine the aerodynamic characteristics of an NACA 0009 airfoil with flaps having chord at 3 locations of the airfoil chord and three degrees of the beveled trailing edges. The results indicated that, with a smooth leading edge, the increased trailing-edge angle on the flaps with sealed gaps decreased the slope of the control-fixed lift curve and the lift effectiveness.
Date: April 1944
Creator: Lockwood, Vernard E.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of control-surface characteristics 13: various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil

Description: Report presenting force tests in two-dimensional flow made on an NACA 66-009 airfoil with a flap having a chord 30 percent of the airfoil chord and a tab having a chord 20 percent of the flap chord. A plain flap and flaps having overhangs of 35 and 50 percent of the flap chord were tested with two gap variations: sealed and unsealed. Results regarding lift, flap hinge moments, pitching moments, drag, and tab characteristics are provided.
Date: July 1943
Creator: Gillis, Clarence L.
Partner: UNT Libraries Government Documents Department

Field of Flow About a Jet and Effect of Jets on Stability of Jet-Propelled Airplanes

Description: A theoretical investigation was conducted on jet-induced flow deviation. Analysis is given of flow inclination induced outside cold and hot jets and jet deflection caused by angle of attack. Applications to computation of effects of jet on longitudinal stability and trim are explained. Effect of jet temperature on flow inclination was found small when thrust coefficient is used as criterion for similitude. The average jet-induced downwash over tail plane was obtained geometrically.
Date: April 1, 1946
Creator: Ribner, Herbert S.
Partner: UNT Libraries Government Documents Department

Flight investigation at high Mach numbers of several methods of measuring static pressure on an airplane wing

Description: Report discusses an investigation into static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The results obtained from the three types of measuring devices and a comparison to theoretical calculations are presented.
Date: November 1944
Creator: Zalovcik, John A. & Daum, Fred L.
Partner: UNT Libraries Government Documents Department

Flight Investigation at High Speeds of Profile Drag of Wing of a P-47D Airplane Having Production Surfaces Covered with Camouflage Paint

Description: Wing section outboard of flap was tested by wake surveys in Mach range of 0.25 - 0.78 and lift coefficient range 0.06 - 0.69. Results indicated that minimum profile-drag coefficient of 0.0097 was attained for lift coefficients from 0.16 to 0.25 at Mach less than 0.67. Below Mach number at which compressibility shock occurred, variations in Mach of 0.2 had negligible effect on profile drag coefficient. Shock was not evident until critical Mach was exceeded by 0.025.
Date: March 1946
Creator: Zalovcik, John A. & Daum, Fred L.
Partner: UNT Libraries Government Documents Department

Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines 1: determination of cooling characteristics of flight engine

Description: Report discussing the cooling characteristics of a 14-cylinder double-row radial air-cooled engine in a four-engine airplane. The effects of charge-air flow, cooling-air pressure drop, and fuel-air ratio on the cooling characteristics were measured separately. The cooling equation, rear middle-barrel temperature, cooling-limited manifold pressure, and maximum cruising power versus temperature-limited power are described.
Date: December 20, 1944
Creator: Blackman, Calvin C.; White, H. Jack & Pragliola, Philip C.
Partner: UNT Libraries Government Documents Department

Flight and test-stand investigation of high-performance fuels in modified double-row radial air-cooled engines 1: determination of the cooling characteristics of the flight engine

Description: Report discussing the cooling characteristics of a modified 14-cylinder double-row radial air-cooled engine installed in a four-engine airplane at a pressure altitude of 7000 feet. Testing of the variable charge-air flow, variable cooling-air pressure drop, and variable fuel-air ratio was conducted. The cooling equation, temperature-limited performance, maximum engine temperatures, and other information predicted by calculations is described.
Date: July 9, 1945
Creator: Werner, Milton; Blackman, Calvin C. & White, H. Jack
Partner: UNT Libraries Government Documents Department

Flight and Test-Stand Investigation of High-Performance Fuels in Modified Double-Row Radial Air-Cooled Engines III: Knock-Limited Performance of 33-R as Compared with a Triptane Blend and 28-R in Flight

Description: A comparison has been made in flight of the antiknock characteristics of 33-R fuel with that of 28-R and a triptane blent. The knock-limited performance of the three fuels - 33-R, a blend of 80 percent 28-R plus 20 percent triptane (leaded to 4.5 ml TEL/gal), and 28-R - was investigated in two modified 14-cylinder double-row radial air-cooled engines. Tests were conducted on the engines as installed in the left inboard nacelle of an airplane. A carburetor-air temperature of approximately 85 deg F was maintained. The conditions covered at an engine speed of 2250 rpm were high and low blower ratios and spark advances of 25 deg and 32 deg B.T.C. For an engine speed of 1800 rpm only the high-blower condition was investigated for both 25 deg and 32 deg spark advances. For the conditions investigated the difference between 33-R and the triptane blend was found to be slight; the performance of 33-R fuel, however, was slightly higher than that of the triptane blend in the lean region. The knock-limited power obtained with the 33-R fuel was from 14 to 28 percent higher than that of the 28-R fuel for the entire range of test conditions; the greatest improvement was shown in the lean region.
Date: August 1945
Creator: Blackman, Calvin C. & White, H. Jack
Partner: UNT Libraries Government Documents Department

Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines 2: flight knock data and comparison of fuel knock limits with engine cooling limits in flight

Description: Report discussing a comparison of the antiknock characteristics of triptane with a temperature-sensitive blending agent and of the fuel knock limits with engine cooling limits. Estimates were also made of temperature-limited engine performance at several flight and engine conditions.
Date: December 30, 1944
Creator: White, H. Jack; Blackman, Calvin C. & Werner, Milton
Partner: UNT Libraries Government Documents Department

Flight and test-stand investigation of high-performance fuels in modified double-row radial air-cooled engines 2: flight knock data and comparison of fuel knock limits with engine cooling limits in flight

Description: Report discussing tests on three fuels in a 14-cylinder double-row radial air-cooled engine at different engine speeds, blower ratios, and spark settings.
Date: August 4, 1945
Creator: White, H. Jack; Pragliola, Philip C. & Blackman, Calvin C.
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

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