Wind-tunnel Investigation of Effects of Trailing-edge Geometry on a NASA Supercritical Airfoil Section PDF Download
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Author: Charles D. Harris
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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Author: Charles D. Harris
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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Book Description
Author: Michael J. Mann
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 348
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Book Description
The effects of wing trailing-edge control surfaces on the static transonic aerodynamic characteristics of a transport configuration with a supercritical wing were studied. The configuration was tested with both an area-ruled fuselage and a cylindrical fuselage. The Mach number range was from 0.80 to 0.96 and the angle of attack range was from -1 deg to 12 deg. The Reynolds number was 1,580,000 based on the mean aerodynamic chord. Tabular data are presented.
Author:
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Category : Aerodynamic load
Languages : en
Pages : 72
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Author: Robert J. Nuber
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 80
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 464
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Three high lift systems for a 9.3 percent blunt based, supercritical airfoil were designed, fabricated, and wind tunnel tested. A method for calculating the viscous flow about two dimensional multicomponent airfoils was evaluated by comparing its predictions with test data. A comparison of high lift systems derived from supercritical airfoils with high lift systems derived from conventional airfoils is presented. The high lift systems for the supercritical airfoil were designed to achieve maximum lift and consisted of: (1) a single slotted flap, (2) a double slotted flap and a leading edge slat, and (3) a triple slotted flap and a leading edge slat. Aerodynamic force and moment data and surface pressure data are presented for all configurations and boundary layer and wake profiles for the single slotted flap configuration. The wind-tunnel models, test facilities and instrumentation, and data reduction are described.
Author:
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Category : Aeronautics
Languages : en
Pages : 548
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Author: Harold S. Johnson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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