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Flight measurements by various methods of the drag characteristics of the XP-51 airplane

Description: Report discussing measurements of the overall drag coefficient of the XP-51 in dives using three different methods. The three instruments used to measure drag variation are compared for accuracy. A comparison of the drag results obtained from this test are also compared to the results obtained from previous wind tunnel testing.
Date: June 1946
Creator: Pearson, Henry A. & Beadle, Dorothy E.
Partner: UNT Libraries Government Documents Department

Some flight measurements on pressure distribution during tail buffeting

Description: Report presenting pressure-distribution measurements obtained from the horizontal tail surfaces of the Curtiss P-40K airplane during low-speed pull-ups to abrupt stall in which tail buffeting was experienced. The chordwise load distributions during buffeting are similar to those experienced during angle-of-attack changes. The location of the stall and frequency of stall disturbances are also described.
Date: October 1945
Creator: Boshar, John
Partner: UNT Libraries Government Documents Department

Test of 0.14-scale models of the control surfaces of Army Project MX-511 in attitudes simulating spins

Description: Report discussing the aerodynamic characteristics of the wing and isolated tail of the Bell XP-83 airplane in attitudes simulating spin conditions. Information about the the aileron hinge moment, angle of attack, and elevator hinge-moment is provided.
Date: April 1945
Creator: Hoggard, H. Page, Jr. & Hagerman, John R.
Partner: UNT Libraries Government Documents Department

Vibration surveys of the P-47-B rudder and fin-rudder assembly

Description: Report presenting a study of the flutter characteristics of the P-47 tail assembly, which included replacing the original fabric-covered rudder with a metal-covered rudder and reinforcing the fin. Figures are provided for different configurations and the cycles per second under the same conditions are provided.
Date: April 1943
Creator: Theodorsen, Theodore & Regier, Arthur A.
Partner: UNT Libraries Government Documents Department

Calculation of the aileron and elevator stick forces and rudder pedal forces for the Bell XP-83 airplane (project MX-511) in spins

Description: From Summary: "Aileron and elevator stick forces and rudder pedal forces for the Bell XP-83 airplane in spins have been calculated. The results indicate that the aileron and elevator stick forces may be excessive unless some suitable booster or more highly balanced control surfaces are used. The pilot will be able to move the surfaces only slightly from their normal floating locations."
Date: September 1945
Creator: Stone, Ralph W., Jr. & Schneiter, Leslie E.
Partner: UNT Libraries Government Documents Department

Vibration surveys of the P-40 rudder and fin-rudder assembly

Description: From Report: "The following surveys on the vibration response of the P-40 rudder and fin-rudder assembly were conducted during the fall of 1942 for the purpose of obtaining information on the flutter characteristics of high-speed airplanes of known performance. The tests on the rudder alone were made with the rudder suspended in a floating condition; the tests on the fin-rudder unit were made with the fin rigidly fastened to a concrete base." A variety of figures and diagrams for the assembly are provided.
Date: April 1943
Creator: Theodorsen, Theodore & Regier, Arthur A.
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

High-speed wind-tunnel tests of semispan horizontal tails with fabric-covered and metal-covered elevators for a bomber airplane

Description: From Summary: "This report contains the results of tests of a full-scale semispan horizontal tail plano of a bomber airplane. The effects of fabric distortion on the aerodynamic characteristics of the elevator are determined by comparing the aerodynamic characteristics of a fabric-covered elevator with those of a metal-covered elevator. In addition, the results of cutting holes in the balance seal, the effect of fixing transition, the tab effectiveness both sealed and unsealed, and the section drag of this tail plane are presented."
Date: December 18, 1944
Creator: Erickson, Albert L. & Nelson, Warren H.
Partner: UNT Libraries Government Documents Department

An investigation of the mutual interference effects of a tail-surface: stern propeller installation on a model simulating the Douglas XB-42 empennage

Description: Report discussing the mutual interference effects of tail surfaces and a stern propeller on a model of the XB-42.The main focus was to determine the effect of tail surface-propeller spacing upon the periodic tail surface loading coincident with propeller blade passage.
Date: November 9, 1944
Creator: Bartlett, Walter A., Jr. & Marino, Alfred A.
Partner: UNT Libraries Government Documents Department

Spray characteristics and take-off and landing stability of several modifications of a 1/8-size model of the PBN-1 flying boat: NACA model 192

Description: Report discussing tests on the PBN-1 airplane to determine the effects of modifications on spray characteristics and take-off and landing stability. Spray strips were found to reduce the spray over the bow at low speeds. The effects of changing the main step location and altering the elevator position are described.
Date: April 1945
Creator: Woodward, David R. & Zeck, Howard
Partner: UNT Libraries Government Documents Department

Tank tests of a powered dynamic model of a flying boat having an afterbody length-beam ratio of 4.7-Langley tank model 203C-1

Description: Report discussing the results of testing on a flying boat model with an afterbody length-beam ratio of 4.7 to determine its takeoff and landing stability and resistance characteristics.The range of stable trims was smaller than models with a conventional afterbody, but the range of stable positions for the center of gravity was about the same. Landing stability was satisfactory, and the hump resistance and trim is less than a boat with a smaller ratio.
Date: October 1945
Creator: Olson, Roland E. & Haar, Marvin I.
Partner: UNT Libraries Government Documents Department

Laboratory investigation of icing in the carburetor and supercharger inlet elbow of an aircraft engine 5: effect of injection of water-fuel mixtures and water-ethanol-fuel mixtures on the icing characteristics

Description: Report discussing the effects of internal coolants injected with fuel on the icing characteristics of a twin-barrel injection carburetor mounted on an engine-stage supercharger assembly. The tests were made at conditions that simulated war emergency power and at a variety of water-fuel ratios, carburetor-air temperatures, and carburetor-air relative humidities.
Date: December 1945
Creator: Renner, Clark E.
Partner: UNT Libraries Government Documents Department

Laboratory investigation of icing in the carburetor and supercharger inlet elbow of an aircraft engine 6: effect of modifications to fuel-spray nozzle on icing characteristics

Description: Report discussing modifications to the spray nozzle to prevent the formation of refrigeration icing in the induction system of an aircraft engine. Two fuel-injection systems, a spinner type and a drilled-inducer type, that prevent the formation of refrigerator icing satisfactorily were created.
Date: January 1946
Creator: Mulholland, Donald R. & Chapman, Gilbert E.
Partner: UNT Libraries Government Documents Department

Laboratory investigation of icing in the carburetor and supercharger inlet elbow of an aircraft engine 2: determination of the limiting-icing conditions

Description: From Summary: "The carburetor and engine-stage supercharger assembly of a fighter aircraft were laboratory-tested to determine the icing characteristics of the induction system under three simulated engine power conditions with varying carburetor-air temperature, relative humidity, simulated-rain injection, rain and fuel temperature, fuel-air ratio, and fuel of different distillation characteristics."
Date: December 1945
Creator: Essex, Henry A.; Keith, Wayne C. & Mulholland, Donald R.
Partner: UNT Libraries Government Documents Department

Laboratory investigation of icing in the carburetor and supercharger inlet elbow of an aircraft engine 3: heated air as a means of de-icing the carburetor and supercharger inlet elbow

Description: Report discussing the use of a twin-barrel injection carburetor and a supercharger inlet elbow to establish the relation between wet- and dry-bulb temperatures of the de-icing air and time required to recover from air-flow loss due to icing. The tests were performed at several power conditions, icing conditions, temperatures, and dry and humidified air. De-icing time was found to be a function of the nature of the ice formation and of the wet-bulb temperature of the de-icing air.
Date: December 1945
Creator: Lyons, Richard E. & Coles, Willard D.
Partner: UNT Libraries Government Documents Department

Laboratory investigation of icing in the carburetor and supercharger inlet elbow of an aircraft engine 4: effect of throttle design and method of throttle operation on induction-system icing characteristics

Description: From Summary: "In order to eliminate the formation of ice on the carburetor throttle plates of an aircraft-engine induction system, two modifications of the throttle design and a variation in the method of throttle operation of the twin-barrel injection carburetor were tested." The modifications were investigated under severe icing conditions at normal power, maximum cruising power, and 60-percent normal power. The only modification that appeared to provide deicing assistance were the electrically heated throttle plates.
Date: January 1946
Creator: Chapman, G. E. & Zlotowski, E. E.
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