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 Decade: 1940-1949
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Natural icing of an axial-flow turbojet engine in flight for a single icing condition

Natural icing of an axial-flow turbojet engine in flight for a single icing condition

Date: August 12, 1948
Creator: Acker, L. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary results of natural icing of an axial-flow turbojet engine

Preliminary results of natural icing of an axial-flow turbojet engine

Date: August 6, 1948
Creator: Acker, L. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary results of natural icing of an axial-flow turbojet engine

Preliminary results of natural icing of an axial-flow turbojet engine

Date: August 6, 1948
Creator: Acker, Loren W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine

Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine

Date: April 7, 1949
Creator: Acker, Loren W & Kleinknecht, Kenneth S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation

Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation

Date: February 14, 1947
Creator: Acker, Loren W. & Kleinknecht, Kenneth S.
Description: Flight and ground investigations have been made to compare an exhaust-ejector installation with a standard exhaust-collector-ring installation on air-cooled aircraft engines in a twin-engine airplane. The ground investigation allowed that, whereas the standard engine would have overheated above 600 horsepower, the engine with exhaust ejectors cooled at take-off operating conditions at zero ram. The exhaust ejectors provided as much cooling with cowl flaps closed as the conventional cowl flaps induced when full open at low airspeeds. The propulsive thrust of the exhaust-ejector installation was calculated to be slightly less than the thrust of the collector-ring-installation.
Contributing Partner: UNT Libraries Government Documents Department
Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method

Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method

Date: April 11, 1947
Creator: Adams, Richard E. & Silsby, Norman S.
Description: A 1/12-scale model of a horizontal tail of a fighter airplane was tested through the transonic speeds in the high-speed flow over an airplane wing, the surface of which served as a reflection plane for the model. Measurements of lift, elevator-hinge moment, angle of attack, and elevator angle were made in the Mach number range from 0.75 to 1.04 for elevator deflections ranging from 10 degrees to minus 10 degrees, and for angles of attack of minus 1.2 degrees, 0.4 degrees, and 3.4 degrees. The equipment used to measure the hinge moments of the model proved to be unsatisfactory, and for this reason the hinge-moment data are considered to be only qualitative.
Contributing Partner: UNT Libraries Government Documents Department
Effects of combinations of aspect ratio and sweepback at high subsonic Mach numbers

Effects of combinations of aspect ratio and sweepback at high subsonic Mach numbers

Date: June 4, 1947
Creator: Adler, Alfred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements of a 34 degree swept-forward and swept-back NACA 65-009 airfoil of aspect ratio 2.7 as determined by flight tests at supersonic speeds

Drag measurements of a 34 degree swept-forward and swept-back NACA 65-009 airfoil of aspect ratio 2.7 as determined by flight tests at supersonic speeds

Date: February 20, 1947
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements of a swept-back wing having inverse taper as determined by flight tests at supersonic speeds

Drag measurements of a swept-back wing having inverse taper as determined by flight tests at supersonic speeds

Date: April 8, 1947
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements of symmetrical circular-arc and NACA 65-009 rectangular airfoils having an aspect ratio of 2.7 as determined by flight tests at supersonic speeds

Drag measurements of symmetrical circular-arc and NACA 65-009 rectangular airfoils having an aspect ratio of 2.7 as determined by flight tests at supersonic speeds

Date: March 7, 1947
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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