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Tests of a thermal ice-prevention system for a wing leading-edge landing-light installation

Description: Report discussing the creation of a thermal ice-prevention system of a bomber-type airplane to provide protection against ice and fog formations on the transparent fairing over the landing light in the wing leading edge. A comparison between the design performance and actual performance showed that the outer-surface heat-transfer coefficient was correctly predicted, but the inner-surface heat-transfer coefficient was four times as large, leading to failure of the plastic fairing.
Date: December 1944
Creator: Hillendahl, Wesley H.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the effects of spoilers on the characteristics of a low-drag airfoil equipped with a 0.25-chord slotted flap

Description: Report discussing the effects of circular-arc spoilers on the section characteristics of an NACA 66,2-216 airfoil with a 0.25-chord slotted flap. Spoilers were tested on the upper surface of the airfoil, on the lower surface, and on both simultaneously. Only the simultaneous placement of spoilers was found to provide satisfactory results as a lateral control device.
Date: July 23, 1945
Creator: Holtzclaw, Ralph W.
Partner: UNT Libraries Government Documents Department

Effect of the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger for thermal ice prevention

Description: From Summary: "This report presents the results of a flight investigation to determine the effect on the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger installed between the engine-exhaust collector ring and the turbosupercharger." The background, results, and discussion of the investigation are described.
Date: August 23, 1945
Creator: Look, Bonne C.
Partner: UNT Libraries Government Documents Department

An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 5: Effect of Thermal System on Airplane Cruise Performance

Description: Report presenting flight tests conducted to evaluate the effect of a thermal ice prevention system on the aerodynamic performance of a C-46 cargo airplane. The installation of the thermal ice-prevention system was found to reduce the indicated airspeed by about 6 miles per hour. Results regarding the overall performance change resulting from the installation of the thermal system, reduction of power attributed to heat-exchanger exhaust-gas back pressure, reduction of power attributed to the internal and external drag of the thermal system, and the additional airplane gross weight attributed to the thermal system are provided.
Date: May 1945
Creator: Selna, James
Partner: UNT Libraries Government Documents Department

Single-Cylinder Oil-Control Tests of Porous Chrome Plated Cylinder Barrels for Radial Air-Cooled Engines

Description: Report presenting a series of single-cylinder engine tests run to determine a satisfactory method of reducing oil consumption in radial air-cooled engines with flat-face compression rings as standard parts and equipped with cylinder barrels salvaged by porous chrome plating. Testing was conducted using porous chrome-plated cylinders with straight and choke bores with standard flat-face compression rings.
Date: January 1946
Creator: Johnson, Robert L. & Swikert, Max
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 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

Flight measurements of the effect on elevator stick forces of stabilizer incidence and elevator rib spacing on the P-63A-1-BE series airplane

Description: From Summary: "Flight tests were made to determine the cause and correction for the unusual stick-free instability of the original production P-63 airplane in high-speed straight flight." The rib spacing and stabilizer incidence of the original design were found to increase instability. When they were both altered, stability was improved and fabric deflection was reduced, but stick forces were not substantially altered.
Date: October 1945
Creator: Johnson, Harold I. & Mungall, Robert G.
Partner: UNT Libraries Government Documents Department

Flight tests of a rudder with a spring tab on an F6F-3 airplane (BuAer No.04776)

Description: Report discussing testing on an F6F-3 with a spring-tab rudder to determine the directional stability and control characteristics. Using the spring-tab rudder was found to result in lower trim-force change with speed and lower pedal forces in sideslips than the original rudder. Pilots were found to prefer the maneuverability of this configuration.
Date: March 1945
Creator: Williams, Walter C.
Partner: UNT Libraries Government Documents Department

Free-spinning, longitudinal-trim, and tumbling tests of 1/17.8-scale models of the Cornelius XFG-1 glider

Description: Report discussing testing on the spin and recovery characteristics, longitudinal-trimming characteristics at extreme angles of attack, and tumbling characteristics of a model of the Cornelius XFG-1 glider. The effects of loading, mass distribution, and center-of-gravity position were determined. They also explored the inverted spin characteristics and spin-recovery parachute requirements.
Date: January 1946
Creator: Stone, Ralph W., Jr. & Daughtridge, Lee T., Jr.
Partner: UNT Libraries Government Documents Department

Free-spinning-tunnel tests of a 1/23.75-scale model of the Douglas DC-3 airplane

Description: Report presenting testing of a model of the Douglas DC-3 airplane for several loading conditions. The load factor for the complete airplane, for the horizontal tail, and the force to start moving the elevator downward were estimated for some steady spins. Testing occurred at 2500 feet and 10,000 feet.
Date: June 1942
Creator: MacDougall, George F., Jr.
Partner: UNT Libraries Government Documents Department

Wind Tunnel Investigation of the Effects of Slot Shape and Flap Location on the Characteristics of a Low-Drag Airfoil Equipped with a 0.25-Chord Slotted Flap

Description: Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag.
Date: December 1944
Creator: Holtzclaw, Ralph W. & Weisman, Yale
Partner: UNT Libraries Government Documents Department

Tests of two models representing intermediate inboard and outboard wing sections of the XB-36 airplane

Description: Report presenting testing in the two-dimensional low-turbulence pressure tunnel and the two-dimensional low-turbulence tunnel of two models made by the Consolidated Aircraft Corporation, one of the outboard section and one of the inboard section.
Date: January 1943
Creator: Bogdonoff, Seymour M.
Partner: UNT Libraries Government Documents Department

Investigation of ice formation in the induction system of an aircraft engine 1: ground tests

Description: From Summary: "Ground tests were conducted on a twin-engine fighter airplane to study icing of an induction system incorporating an exhaust-driven turbosupercharger. The ground tests were made to determine the disposition of free water in the induction system of the airplane, to determine the charge-air heat rise available from the turbosupercharger, and to correlate actual airplane-test results with those of laboratory tests."
Date: March 1946
Creator: Essex, Henry A.; Zlotowski, Edward D. & Ellisman, Carl
Partner: UNT Libraries Government Documents Department

Investigation of ice formation in the induction system of an aircraft engine 2: flight tests

Description: From Summary: "Flight tests were conducted on a twin-engine fighter airplane at pressure altitudes up to 10,000 feet with simulated conditions of moderate, heavy, and excessive rain to determine the increase in enthalpy of the charge air due to the turbosupercharger, to determine the rate of enthalpy increase of the charge air resulting from a sudden increase of engine power, and to compare the conditions that caused induction-system icing in flight with those that resulted in icing of the same carburetor and supercharger inlet elbow in laboratory tests."
Date: June 1946
Creator: Essex, Henry A.; Ellisman, Carl & Zlotowski, Edward D.
Partner: UNT Libraries Government Documents Department

Investigation of slipstream effects on a wing-inlet oil-cooler ducting system of a twin-engine airplane in the Ames 40- by 80-foot wind tunnel

Description: Report discussing an investigation of wing-inlet oil-cooler ducts on a twin-engine airplane to determine internal and external-flow characteristics of the ducting installation. Testing was also performed on revised inlets to attempt to develop a ducting system with low overall losses throughout the operating range.
Date: March 10, 1945
Creator: Chapman, Dean R.
Partner: UNT Libraries Government Documents Department

Tests of Four Full-Scale Propellers to Determine the Effect of Trailing-Edge Extensions on Propeller Aerodynamic Characteristics

Description: Propellers with trailing-edge extensions were studied to determine aerodynamic characteristics. Trailing-edge extension increased power absorbed by propeller with little loss in efficiency. Power coefficient for maximum efficiency was greater for 20% camber type extension than for 20% straight type extension over range of advance ratio of 1.0 to 2.5 although camber type was less efficient. Efficiency was about the same for cruising and high-speed at a high power coefficient for propeller with extension.
Date: July 1945
Creator: Maynard, Julian D. & Evans, Albert J.
Partner: UNT Libraries Government Documents Department

Loss of xylidines in overwater storage of xylidine-blended fuel

Description: Tests were undertaken to determine the relationships for estimating the maximum amount of a water-soluble gasoline additive that will diffuse from the gasoline to the water when fuel is stored over the water and to determine from the relationships the amount of xylidines that will diffuse from the gasoline to the water in an overwater-storage system.
Date: March 1944
Creator: Tischler, Adelbert O. & Tischler, Adelbert O.
Partner: UNT Libraries Government Documents Department