Flight Tests at Supersonic Speeds to Determine the Effect of Taper on the Zero-lift Drag of Sweptback Low-aspect-ratio Wings PDF Download
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Author: Murray Pittel
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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Book Description
Rocket-powered models have been flown to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings having thin, symmetrical, double-wedge airfoil sections. The range of the experimental data is from a Mach number M of 1.0 to 1.8, and theoretical comparisons are made for the test range above M = 1.2.
Author: Murray Pittel
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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Book Description
Rocket-powered models have been flown to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings having thin, symmetrical, double-wedge airfoil sections. The range of the experimental data is from a Mach number M of 1.0 to 1.8, and theoretical comparisons are made for the test range above M = 1.2.
Author: Murray Pittel
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 23
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Book Description
Rocket-powered models have been flown to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings having thin, symmetrical, double-wedge airfoil sections. The range of the experimental data is from Mach number 1.0 to 1.8, and theoretical comparisons are made for the test range above M = 1.2.
Author: John C. Heitmeyer
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 30
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1142
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Book Description
Author: Sidney R. Alexander
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 8
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Book Description
Tests were conducted on wings having taper ratios from 0 to 1 mounted on rocket propelled test bodies to determine the effect of taper on the zero lift drag of wings at low supersonic speeds. Detailed data on models and test conditions are provided. comparison is made between results of theoretical drag calculations of tapered wings and applicable experimental values derived. Maximum thickness, leading edge, and trailing edge sweep are used in determining drag coefficient. At a constant leading edge sweep of 45 degree, no orderly variation of drag coefficient with taper ratio occurs.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 442
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 620
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Book Description
