Pressure-distribution Measurements Over an Extensible Leading-edge Flap on Two Wings Having Leading-edge Sweep of 42 Degree and 52 Degree PDF Download
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Author: Reino J. Salmi
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Author: Reino J. Salmi
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
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Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Author: P. Calvin Stainback
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 28
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Author: P. CALVIN. STAINBACK
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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An experimental investigation was conducted to measure the pressures on two 60 degree swept delta wings with cylindrical leading edges of 0.25-inch radii and dihedral angles of 0 and 45 degrees. The tests were conducted at a Mach number of 4.95 and a stagnation temperature of 400 F. The test-section unit Reynolds number was 15.19 x 10 to the 6th power and the angle of attack was varied from 0 to 20 degrees. The results of the investigation indicated that, in general, Newtonian theory would not predict the pressure distri ution on the model in a plane normal to the leading edge for angles of attac greater than zero. A method which utilizes a linear combination of viscous and inviscid pressure terms, developed by Creager for predicting pressures on blunt-leading-e ge delta wing at angles of attac, was in good agreement with the measured pressure distributions. The stagnationline pressure level could be predicted within!9 percent by using the ideal-gas normal-shock relationship with the normal component of the free-stream Mach number. (Author).
Author: Zachary T. Applin
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 40
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Author: Reed U. Jr Barnett
Publisher:
ISBN:
Category :
Languages : en
Pages : 39
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Author: Roy H. Lange
Publisher:
ISBN:
Category :
Languages : en
Pages : 72
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Author: Earl R. Keener
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 80
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Author: Arthur William Babister
Publisher:
ISBN:
Category :
Languages : en
Pages : 12
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Author: College of Aeronautics (Cranfield, Bedfordshire)
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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