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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
Give us lumber for more PT's.

Give us lumber for more PT's.

Date: 1943
Creator: AEL.
Description: Color image of war ships at sea. In the foreground is a boat with "PT 34" painted on it, shining a light and speeding forward. In the background, a ship is sinking as explosive flames rise from it. Other ships and flames can be seen in the distance on the left.
Contributing Partner: UNT Libraries Government Documents Department
Lift and drag data for 30 pusher-propeller shaft housings on an NACA 65,3-018 airfoil section

Lift and drag data for 30 pusher-propeller shaft housings on an NACA 65,3-018 airfoil section

Date: November 1, 1943
Creator: Abbott, Frank T , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane

Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane

Date: May 1, 1942
Creator: Abbott, Frank T , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Lift and drag characteristics of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation

Lift and drag characteristics of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation

Date: December 1, 1941
Creator: Abbott, I H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Pressure-distribution measurements of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation

Pressure-distribution measurements of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation

Date: December 1, 1941
Creator: Abbott, I H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Numbers and Low Turbulence

Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Numbers and Low Turbulence

Date: March 1, 1942
Creator: Abbott, I. H.; Davidson, M. & Jacobs, E. N.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Interference effects of longitudinal flat plates on low-drag airfoils

Interference effects of longitudinal flat plates on low-drag airfoils

Date: November 1, 1942
Creator: Abbott, Ira H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation

Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation

Date: January 1, 1942
Creator: Abbott, Ira H
Description: Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
Contributing Partner: UNT Libraries Government Documents Department
Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane

Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane

Date: January 1, 1942
Creator: Abbott, Ira H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Summary of Airfoil Data

Summary of Airfoil Data

Date: January 1, 1945
Creator: Abbott, Ira H
Description: The historical development of NACA airfoils is briefly reviewed. New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils. The general methods used to derive the basic thickness forms for NACA 6 and 7-series airfoils together with their corresponding pressure distributions are presented. Detail data necessary for the application of the airfoils to wing design are presented in supplementary figures placed at the end of the paper. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Available data on high-lift devices are presented. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed, together with aerodynamic problems of application. (author).
Contributing Partner: UNT Libraries Government Documents Department
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