National Advisory Committee for Aeronautics (NACA) - 13 Matching Results

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Buffeting of External Fuel Tanks at High Speeds on a Gruman F7F-3 Airplane

Description: Attempts were made to alleviate the buffeting of external fuel tanks mounted under the wings of a twin-engine Navy fighter airplane. The Mach number at which buffeting began was increased from 0,529 to 0.640 by streamlining the sway braces and by increasing the lateral rigidity of the sway brace system. Further increase of the Mach number, at which buffeting began to 0.725, was obtained by moving the external fuel tank to a position under the fuselage.
Date: January 29, 1947
Creator: Turner, Howard L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Data Obtained in the Flight Measurements to Determine the Stability and Control Characteristics of a C-54D Airplane (AAF No. 42-72713) and a Summary of the Test Program

Description: "The flight investigation of the C-54D airplane was initiated to determine the necessity of changes or additions to existing handling-qualities requirements to cove the case of instrument approaches with large airplanes. This paper gives a brief synopsis of the results and presents the measured data of tests to determine the stability and control characteristics. It was found that no new requirements were necessary to cover the problems of instrument approaches" (p. 1).
Date: December 29, 1947
Creator: Talmage, Donald B. & Reeder, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Development of Jet-Engine Nacelles for a High-Speed Bomber Design

Description: "The results of an experimental investigation made for the purpose of developing suitable jet-engine nacelle designs for a high-speed medium bomber are presented. Two types of nacelles were investigated, the first enclosing two 4000-pounds-thrust jet engines and a 65-inch-diameter landing wheel and the second enclosing a single 4000-pounds-thrust jet engine. Both types of nacelles were tested in positions underslung beneath the wing and centrally located on the wing" (p. 1).
Date: August 29, 1947
Creator: Dannenberg, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Thrust Augmentation of a Turbojet Engine by Water-Alcohol Injection

Description: Memorandum presenting an investigation of thrust augmentation by the injection of water-alcohol mixtures into the compressor inlets of a turbojet engine with a centrifugal-flow-type compressor at altitudes of sea level, 5000 feet, and 10,000 feet. The investigation was made to determine the water-alcohol mixture and the injection rate for optimum thrust augmentation. At a standard NACA altitude of 10,000 feet and an engine speed of 16,000 rpm, the mixture and injection rate for optimum thrust a… more
Date: September 29, 1947
Creator: Ellisman, Carl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Tests to Determine the Effect of Length of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Description: Flight tests were conducted to determine the effect of length of a conical windshield on the drag of a bluff body moving at supersonic speeds. A comparison is made between results obtained and results of previous drag tests of body-windshield combinations.The effect of increasing the length of the windshield is discussed.
Date: January 29, 1947
Creator: Alexander, Sidney R. & Katz, Ellis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation of Control Effectiveness of Full-Span 0.2-Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Section Thickness and Wing Sweepback

Description: Report discusses the development and testing of a rocket-propelled test vehicle to investigate aerodynamic control effectiveness at high subsonic, transonic, and supersonic speeds. Modifications to the section thickness and wing sweepback to improve performance are also described. A description of the vehicle, instrumentation, accuracy, and evaluation of testing results is included.
Date: May 29, 1947
Creator: Sandahl, Carl A. & Marino, Alfred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fuel Tests on an I-16 Jet-Propulsion Engine at Static Sea-Level Conditions

Description: Memorandum presenting an investigation of the effect of fuel composition and boiling point on the performance of the type of I-16 jet-propulsion engine. Testing occurred with 14 fuels embodying different types of hydrocarbon and with a range of boiling points. The results indicated that fuel composition and boiling range have a negligible effect on engine thrust, rotor speed, and gas temperatures for the principal types of hydrocarbon fuel when used for short periods of time.
Date: April 29, 1947
Creator: Bolz, Ray E. & Meigs, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The High-Speed Longitudinal Stability and Control of the Bell P-39N-1 Airplane as Calculated from Propeller-Off Tests of a 0.35-Scale Model

Description: "This report presents the result of tests of a 0.35-scale model of the Bell P-39N-l airplane. Included are the longitudinal-stability and - control characteristics of the airplane as indicated by tests of the model equipped with each of two different sets of elevators. The results indicate good longitudinal stability and control throughout the speed range encounterable in flight" (p. 1).
Date: January 29, 1947
Creator: Robinson, Robert C. & Perone, Angelo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The High-Speed Longitudinal Stability and Control of the Bell P-39N-1 Airplane as Calculated from Propeller-Off Tests of a 0.35-Scale Model

Description: "This report presents the results of tests of a .35-scale model of the Bell P-39N-1 airplane. Included are the longitudinal-stability and -control characteristics of the airplane as indicated by tests of the model equipped with each of two different sets of elevators. The results indicate good longitudinal stability and control throughout the speed range encounterable in flight" (p. 1).
Date: January 29, 1947
Creator: Robinson, Robert C. & Perone, Angelo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of carbon deposition in an I-16 jet-propulsion engine at static sea-level conditions

Description: Report presenting a study of the effect of fuel properties on carbon deposition in jet-propulsion engine combustors using seven fuels: kerosene, Diesel fuel oil, toluene, xylene, 62-octane gasoline, a commercial solvent, and AN-F-32 (JP-1) in an I-16 engine at static sea-level conditions and constant rotor speed. Results regarding the reproducibility of data, reduced exhaust-jet-nozzle area, and fuel comparison are provided.
Date: April 29, 1947
Creator: Jonash, Edmund R.; Barnett, Henry C. & Stricker, Edward G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel. Part III - Longitudinal-Control Characteristics TED No. NACA DE308, Part 3, Longitudinal-Control Characteristics, TED No. NACA DE308

Description: Tests have been conducted in the Langley high speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0,08-scale model of the Chance Vought XF7U-1 airplane. The longitudinal-control characteristics of the complete model are presented in the present report with a limited analysis of the results.
Date: July 29, 1947
Creator: Kuhn, Richard E. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics of a Semispan Model of the XF7U-1 Tailless Airplane at Transonic Speeds by the NACA Wing-Flow Method, TED No. NACA DE307

Description: From Summary: "An investigation was made by the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan model of the XF7U-1 tailless airplane. The 25-percent chord line of the wing of the model was swept back 35 deg. The airfoil sections of the wing perpendicular to the 25-percent chord line were 12 percent thick. Measurements were made of the normal force and pitching moment through an angle-of-attack range from about -3 deg t… more
Date: September 29, 1947
Creator: Sawyer, Richard H. & Trant, James P., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Study of Ram-Actuated Cooling Systems for Supersonic Aircraft

Description: An analysis has been made of the characteristics of several cooling cycles suitable for cockpit cooling of supersonic aircraft. All the cycles considered utilize the difference between dynamic and ambient static pressure to actuate the cooling system and require no additional power source. The results of the study indicate that as flight speeds become greater, increasingly complex systems are required to reduce the altitudes above approximately 35,000 feet, a system composed of an externally lo… more
Date: April 29, 1947
Creator: Stalder, Jackson R. & Wadleigh, Kenneth R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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