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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
Flight investigations at low supersonic speeds to determine the effectiveness of cones and a wedge in reducing the drag of round-nose bodies and airfoils

Flight investigations at low supersonic speeds to determine the effectiveness of cones and a wedge in reducing the drag of round-nose bodies and airfoils

Date: March 3, 1949
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having aspect ratios of 1.5 and 2.7 as determined by flight tests at supersonic speeds

Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having aspect ratios of 1.5 and 2.7 as determined by flight tests at supersonic speeds

Date: February 24, 1947
Creator: Alexander, Sidney R & Katz, Ellis
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight tests to determine the effect of taper on the zero-lift drag of wings at low supersonic speeds

Flight tests to determine the effect of taper on the zero-lift drag of wings at low supersonic speeds

Date: July 13, 1947
Creator: Alexander, Sidney R & Nelson, Robert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Investigation to Determine the Aerodynamic Characteristics of Rocket-Powered Models Representative of a Fighter-Type Airplane Configuration Incorporating an Inverse-Taper Wing and a Vee Tail

Flight Investigation to Determine the Aerodynamic Characteristics of Rocket-Powered Models Representative of a Fighter-Type Airplane Configuration Incorporating an Inverse-Taper Wing and a Vee Tail

Date: November 2, 1948
Creator: Alexander, Sidney R.
Description: Two rocket-powered models representative of a fighter-type airplane were investigated in flight at Mach numbers up to 1.01 and 1.07 by the Langley Pilotless Aircraft Research Division at its testing station at Wallops Island, Va. These models incorporated an inverse-taper wing and a vee tail and were flown with controls undeflected and wing and stabilizer set at 0 deg incidence. Values of lateral acceleration, normal acceleration velocity, and drag were obtained by use of telemeters and a Doppler velocimeter radar unit. The results of this investigation indicated no unusual variation in the lateral acceleration characteristics. After the cessation of powered flight, the lateral oscillation quickly damped to zero. The data indicated that the airplane, at low lift coefficients, should not experience any abrupt trim changes until it attains a Mach number of 0.97. The change in normal-force coefficient associated with this trim change will amount to about 0.03 with the center of gravity located at 4.48% of the mean aerodynamic chord. At higher lift coefficients, on the basis of other data, the Mach number at which this trim change occurs would be expected to be decreased. The neutral point of the model at Mach numbers near 1.05 was estimated to ...
Contributing Partner: UNT Libraries Government Documents Department
Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Date: January 14, 1947
Creator: Alexander, Sidney R.
Description: Tests to evaluate the effect of a conical windshield on the drag of a bluff body at supersonic speeds were performed for the following configurations: a sharp nose fuselage with stabilizing fins,a blunt nose fuselage with a hemispherical shape, and a blunt nose fuselage with a conical point. Results of the drag coeeficient are described at Mach 1.0 and the greatest Mach number of 1.37.
Contributing Partner: UNT Libraries Government Documents Department
Flight Tests to Determine the Effect of Length of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Flight Tests to Determine the Effect of Length of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Date: January 29, 1947
Creator: Alexander, Sidney R. & Katz, Ellis
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.
Contributing Partner: UNT Libraries Government Documents Department
Flight tests to determine the drag of fin-stabilized parabolic bodies at transonic and supersonic speeds

Flight tests to determine the drag of fin-stabilized parabolic bodies at transonic and supersonic speeds

Date: April 21, 1948
Creator: Alexander, Sidney R; Chauvin, Leo T & Rumsey, Charles B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Estimation of the forces and moments acting on inclined bodies of revolution of high fineness ratio

Estimation of the forces and moments acting on inclined bodies of revolution of high fineness ratio

Date: November 14, 1949
Creator: Allen, H Julian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The interaction of boundary layer and compression shock and its effect upon airfoil pressure distributions

The interaction of boundary layer and compression shock and its effect upon airfoil pressure distributions

Date: April 10, 1947
Creator: Allen, H Julian; Heaslet, Max A & Nitzberg, Gerald E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a two-blade NACA 10-(3)(12)-03 propeller

Aerodynamic characteristics of a two-blade NACA 10-(3)(12)-03 propeller

Date: August 30, 1948
Creator: Allis, A E & Gray, W H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of one part of Von Karman's two-dimensional transonic similarity law to drag data of NACA 65-series wings

Application of one part of Von Karman's two-dimensional transonic similarity law to drag data of NACA 65-series wings

Date: August 24, 1948
Creator: Amer, Kenneth B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Chordwise and spanwise loadings measured at low speed on large triangular wings

Chordwise and spanwise loadings measured at low speed on large triangular wings

Date: April 19, 1949
Creator: Anderson, Adrien E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation at low speed of a large-scale triangular wing of aspect ratio two II : the effect of airfoil section modifications and the determination of the wake downwash

An investigation at low speed of a large-scale triangular wing of aspect ratio two II : the effect of airfoil section modifications and the determination of the wake downwash

Date: December 10, 1947
Creator: Anderson, Adrien E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation at low speed of a large-scale triangular wing of aspect ratio two III : characteristics of wing with body and vertical tail

An investigation at low speed of a large-scale triangular wing of aspect ratio two III : characteristics of wing with body and vertical tail

Date: October 14, 1949
Creator: Anderson, Adrien E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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