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 Decade: 1940-1949
 Year: 1947
 Month: October
 Collection: National Advisory Committee for Aeronautics Collection
An analysis of airspeeds and Mach numbers attained by Lockheed Constellation airplanes in transcontinental operations during the early summer of 1946

An analysis of airspeeds and Mach numbers attained by Lockheed Constellation airplanes in transcontinental operations during the early summer of 1946

Date: October 10, 1947
Creator: Steiner, Roy
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of performance of jet engine from characteristics of components I : aerodynamic and matching characteristics of turbine component determined with cold air

Analysis of performance of jet engine from characteristics of components I : aerodynamic and matching characteristics of turbine component determined with cold air

Date: October 1, 1947
Creator: Goldstein, Arthur W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical and experimental investigation of bolted joints

Analytical and experimental investigation of bolted joints

Date: October 1947
Creator: Rosenfeld, Samuel J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Boundary-layer momentum equations for three-dimensional flow

Boundary-layer momentum equations for three-dimensional flow

Date: October 1, 1947
Creator: Tetervin, Neal
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Changes found on run-in and scuffed surfaces of steel chrome plate, and cast iron

Changes found on run-in and scuffed surfaces of steel chrome plate, and cast iron

Date: October 1, 1947
Creator: Good, J N & Godfrey, Douglas
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of a 15-percent-chord and a 35-percent-chord plain flap on the NACA 0006 airfoil section at high subsonic speeds

Characteristics of a 15-percent-chord and a 35-percent-chord plain flap on the NACA 0006 airfoil section at high subsonic speeds

Date: October 2, 1947
Creator: Ilk, Richard J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Coefficient of Friction, Oil Flow and Heat Balance of a Full-Journal Bearing

Coefficient of Friction, Oil Flow and Heat Balance of a Full-Journal Bearing

Date: October 1, 1947
Creator: Orloff, P. I.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cooling of gas-turbines VII : effectiveness of air cooling of hollow turbine blades with inserts

Cooling of gas-turbines VII : effectiveness of air cooling of hollow turbine blades with inserts

Date: October 20, 1947
Creator: Bressman, Joseph R & Livingood, John N B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of coupled modes and frequencies of swept wings by use of power series

Determination of coupled modes and frequencies of swept wings by use of power series

Date: October 20, 1947
Creator: Anderson, Roger A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Development of Outboard Nacelle for the XB-36 Airplane

Development of Outboard Nacelle for the XB-36 Airplane

Date: October 31, 1947
Creator: Nuber, Robert J.
Description: An investigation of two 1/14 scale model configurations of an outboard nacelle for the XB-36 airplane was made in the Langley two-dimensional low-turbulence tunnels over a range of airplane lift coefficients (C (sub L) = 0.409 to C(sub L) = 0.943) for three representative flow conditions. The purpose of the investigation was to develop a low-drag wing-nacelle pusher combination which incorporated an internal air-flow system. The present investigation has led to the development of a nacelle which had external drag coefficients of similar order of magnitude to those obtained previously from tests of an inboard nacelle configuration at the corresponding operating lift coefficients and from approximately one-third to one-half of those of conventional tractor designs having the same ratio of wing thickness to nacelle diameter.
Contributing Partner: UNT Libraries Government Documents Department
The effect of changing the ratio of exhaust-valve flow capacity to inlet-valve flow capacity on volumetric efficiency and output of a single- cylinder engine

The effect of changing the ratio of exhaust-valve flow capacity to inlet-valve flow capacity on volumetric efficiency and output of a single- cylinder engine

Date: October 1, 1947
Creator: Eppes, James V D; Livengood, James C & Taylor, C Fayette
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of finite span on the airload distributions for oscillating wings. II - Methods of calculation and examples of application

Effect of finite span on the airload distributions for oscillating wings. II - Methods of calculation and examples of application

Date: October 1, 1947
Creator: Reissner, Eric & Stevens, John E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of sample size on the determination of maximum gust velocities in clouds

The effect of sample size on the determination of maximum gust velocities in clouds

Date: October 10, 1947
Creator: Press, Harry
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of variation in diameter and pitch of rivets on compressive strength of panels with Z-section stiffeners: panels of various stiffener spacings that fail by local buckling

Effect of variation in diameter and pitch of rivets on compressive strength of panels with Z-section stiffeners: panels of various stiffener spacings that fail by local buckling

Date: October 1, 1947
Creator: Dow, Norris F & Hickman, William A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Estimation of range of stability derivatives for current and future pilotless aircraft

Estimation of range of stability derivatives for current and future pilotless aircraft

Date: October 8, 1947
Creator: Pitkin, Marvin & Ankenbruck, Herman O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of performance and operating characteristics of a tail-pipe burner for a turbojet engine

Experimental investigation of performance and operating characteristics of a tail-pipe burner for a turbojet engine

Date: October 30, 1947
Creator: Gabriel, David S; Martinson, E Vincent & Essig, Robert H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099): Lateral- and Directional-Stability and Control Characteristics

Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099): Lateral- and Directional-Stability and Control Characteristics

Date: October 24, 1947
Creator: Anderson, Seth B. & Cooper, George E.
Description: This report contains the flight-test results of the lateral and directional-stability and control phase (including tests with wing-tip tanks) of a general flying-qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). These tests were conducted at indicated airspeeds up to 494 miles per hour (0.691 Mach number) at low altitude and up to 378 miles per hour (0.816 Mach number) at high altitude. These tests showed that the flying qualities of the airplane were for the most part in accordance with the requirements of the Army Air Forces Stability and Control Specifications. The only major deficiency noted was the negative lateral stability with the wing-tip tanks installed.
Contributing Partner: UNT Libraries Government Documents Department
Free-Spinning-Tunnel Tests of a 1/16-Scale Model of the Chance Vought XF5U-1 Airplane, TED No. NACA 2349

Free-Spinning-Tunnel Tests of a 1/16-Scale Model of the Chance Vought XF5U-1 Airplane, TED No. NACA 2349

Date: October 17, 1947
Creator: White, Richard P.
Description: Spin tests of a 1/16-scale model of the Chance Vought XF5U-1 airplane have been performed in the Langley 20-foot free-spinning tunnel. The effect of control position and movement upon the erect and inverted spin and recovery characteristics ae well as the effects of propellers, of stability flaps, and of various revisions to the design configuration have been determined for the normal fighter loading. The investigation also included spin recovery parachute, tumbling, and pilot-escape tests. For the original design configuration, with or without windmilling propellers, the recovery characteristics of the model were considered unsatisfactory. Increasing the maximum upward deflection of the ailavators from 45 deg to 65 deg resulted in greatly improved recovery characteristics. Dimensional revisions to the original airplane configuration, which satisfactorily improved the general spin and recovery characteristics of the model, consisted of: (1) a supplementary vertical tail 34 inches by 59 inches (full-scale) attached to a boom 80 inches aft of the trailing edge of the airplane in the plane of symmetry, (2) a large semispan undersurface spoiler placed along the airplane quarter-chord line and opened on the outboard side in a spin, or (3) two additional vertical tails 64 inches by 52 inches (full-scale) located at the ...
Contributing Partner: UNT Libraries Government Documents Department
Friction at high sliding velocities

Friction at high sliding velocities

Date: October 1, 1947
Creator: Johnson, Robert L; Swikert, Max A & Bisson, Edmond E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A further investigation of the meteorological conditions conducive to aircraft icing

A further investigation of the meteorological conditions conducive to aircraft icing

Date: October 1, 1947
Creator: Lewis, William; Kline, Dwight B & Steinmetz, Charles P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Generalized performance comparison of large conventional, tail boom, and tailless airplanes

Generalized performance comparison of large conventional, tail boom, and tailless airplanes

Date: October 1, 1947
Creator: Ankenbruck, Herman O & Mckinney, Marion O , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Impact theory for seaplane landings

Impact theory for seaplane landings

Date: October 1, 1947
Creator: Benscoter, S U
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of high-lift and stall-control devices on a NACA 64-series 42 degree sweptback wing with and without fuselage

Investigation of high-lift and stall-control devices on a NACA 64-series 42 degree sweptback wing with and without fuselage

Date: October 1, 1947
Creator: Graham, Robert R & Conner, D William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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 V - Wing-Alone Tests and Effect of Modifications to the Vertical Fins, Speed Brakes, and Fuselage TED No. NACA DE308, Part V, Wing-Alone Tests and Effect of Modifications to the Vertical Fins, Speed Brakes, and Fuselage, TED No. NACA DE308

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 V - Wing-Alone Tests and Effect of Modifications to the Vertical Fins, Speed Brakes, and Fuselage TED No. NACA DE308, Part V, Wing-Alone Tests and Effect of Modifications to the Vertical Fins, Speed Brakes, and Fuselage, TED No. NACA DE308

Date: October 10, 1947
Creator: Kuhri, Richard E. & Myers, Boyd C., II
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 wing-alone tests and the effect of the various vertical-fin modifications, speed-brake modifications, and fuselage modifications on the aerodynamic characteristics in pitch and yaw are presented in the present paper with a limited analysis of the results. Also included are tuft studies of the flow for some of the modifications tested.
Contributing Partner: UNT Libraries Government Documents Department
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