Basic Pressure Measurements at a Mach Number of 1.43 on a Thin 45 Deg Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations PDF Download
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Category :
Languages : en
Pages : 82
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Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic and cubic twist variations along the span. All the twisted wings had 0deg twist at the 10-percent-semispan station and 6deg twist at the tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4deg to 20deg. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 x 10(exp 6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 x 10(exp 6) during tests at a stagnation pressure of 0.5 atmosphere.
Author:
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Category :
Languages : en
Pages : 82
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Book Description
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic and cubic twist variations along the span. All the twisted wings had 0deg twist at the 10-percent-semispan station and 6deg twist at the tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4deg to 20deg. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 x 10(exp 6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 x 10(exp 6) during tests at a stagnation pressure of 0.5 atmosphere.
Author: John P. Mugler
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Category :
Languages : en
Pages : 73
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Author: John P. Jr Mugler
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Category : Wall pressure (Aerodynamics)
Languages : en
Pages : 78
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Book Description
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic, and cubic twist variations along the span. All the twisted wings had 0 degrees twist at the 10-percent-semispan station and 6 degrees twist at he tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4 degrees to 20 degrees. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 X 10(6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 X 10(6) during tests at a stagnation pressure of 0.5 atmosphere.
Author:
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ISBN:
Category :
Languages : en
Pages : 44
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Author: Thomas L. Fischetti
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ISBN:
Category : Aerodynamic load
Languages : en
Pages : 94
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Book Description
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.
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Category : Aeronautics
Languages : en
Pages : 1386
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Category :
Languages : en
Pages : 20
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Author: Jack D. Stephenson
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Category : Aeronautics
Languages : en
Pages : 86
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Author: H. Herbert Jackson
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Category : Mach number
Languages : en
Pages : 32
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Author: Frank J. Centolanzi
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ISBN:
Category : Mach number
Languages : en
Pages : 82
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