Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40 PDF Download
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Author: Louis S. Stivers
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
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Book Description
Author: Louis S. Stivers
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
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Book Description
Author: Louis S. Stivers
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Author: Royal Aeronautical Society
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1156
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Author: W. F. Lindsey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24
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Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.
Author: Don W. Jillie
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 36
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Author: Samuel Ralph Pate
Publisher:
ISBN:
Category :
Languages : en
Pages : 95
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Author: Mitchel H. Bertram
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Author: DON W. JILLIE
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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The effects of leading-edge bluntness and sweep on boundary-layer transition on flat plate models were investigated at Mach numbers of 2.00, 2.50, 3.00, and 4.00. The effect of sweep on transition was also determined on a flat plate model equipped with an elliptical nose at a Mach number of 0.27. Models used for the supersonic investigation had leading-edge radii varying from 0.0005 to 0.040 inch. The free-stream unit Reynolds number was held constant at 15 million per foot for the supersonic tests and the angle of attack was 0 degrees. Surface flow conditions were determined by visual observation and recorded photographically. For the models with the blunter leading edges, the transition Reynolds number (based on free-stream flow conditions) was approximately doubled by an increase in Mach number from 2.50 to 4.00; and nearly the same result was predicted from shock-loss considerations. At all supersonic Mach numbers, increases in sweep reduced the transition Reynolds number and the amount of reduction increased with increases in bluntness. The shock-loss method considerably underestimated the sweep effects, with swept wings. (Author).
Author: L. N. Cattafesta
Publisher:
ISBN:
Category :
Languages : en
Pages :
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