Wind Tunnel Tests of Fuselages and Windscreens PDF Download
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Author: Edward Pearson Warner
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 552
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Book Description
The tests described herein were made in 1918, in the old four-foot wind tunnel at the Massachusetts Institute of Technology and at the request of the Engineering Division of the U.S. Army Air Service.
Author: Edward Pearson Warner
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 552
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Book Description
The tests described herein were made in 1918, in the old four-foot wind tunnel at the Massachusetts Institute of Technology and at the request of the Engineering Division of the U.S. Army Air Service.
Author: Edward E. Warner
Publisher:
ISBN:
Category :
Languages : en
Pages : 10
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Book Description
Author: Edward P. Warner
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Author: Ira H. Abbott
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
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Book Description
Author: Fred E. Weick
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 84
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Book Description
Author: Alan Pope
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 482
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Book Description
Author: Joseph L. Anderson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 120
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Book Description
At the request of the Air Technical Service Command, U. S. Army Air Forces, a 0.22-scale model of a twin-fuselage pursuit airplane was built and tested at the Ames Aeronautical Laboratory. The tests of this model were made in order that the aerodynamic characteristics of the airplane, especially at high speed, might be predicted.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Book Description
Author: James B. Delano
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 25
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Book Description
Tests were conducted in the NACA 8-foot high-speed wind tunnel to determine the loads and. the load distributions at high speeds for a number of windshields of the cockpit-canopy type. Drag data were obtained simultaneously with the load data. Ten windshields of various designs similar to those in general use were included in these tests. A new windshield designed to give low local loads and low drags was also tested. These windshields were mounted on the DC-3 fuselage and wing model. Pressure distributions were obtained for the wing alone and for fuselage mounted on the wing. From the pressure data an analysis was made of the interference effects between a windshield and the model. The tests were made at Mach numbers ranging from 0.12 to 0.71, and a study of the effects of compressibility on loads and drags was thereby permitted.
Author: S. F. J. Butler
Publisher:
ISBN:
Category :
Languages : en
Pages : 56
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Book Description
