Investigation of Vortex Movements about a Wing in Steady Subsonic Flow Undergoing a Large Angle-of-attack Change in a Blast-induced Gust PDF Download
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Author: Donald R. McFarland
Publisher:
ISBN:
Category :
Languages : en
Pages : 41
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Author: Donald R. McFarland
Publisher:
ISBN:
Category :
Languages : en
Pages : 41
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Book Description
Author: Donald R. McFarland
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
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Author: Donald R. McFarland
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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Measurements were made of the vortex movements about an airfoil undergoing a blast of sufficient strengt to exceed momentarily the stall angle by a large amount. This report extends the previously reported low-speed data to the intermediateAND HIGH SUBSONIC VELOCITIE . A heated shockdriven tunnel was used to provide a high subsonic, steady, free jet of short duration to simulate the model flight. Small high-explosive charges were used to produce scaled blast waves. Generally, the trailing-edge vortices travel at the fluid stream velocities, whereas leading-edge vortices travel at lower speeds. Comparison of a modified Rott theory and vortex data produced by the blast wave alone shows less agreement at the higher velocities than the low-speed data previ usly reported. The results indicate that the identity of the leading-edge vortex is lost in the presence of the supercritical flow over the wing model. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 432
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Author:
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Category : Shock (Mechanics)
Languages : en
Pages : 848
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Author: Defense Documentation Center (U.S.)
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Category : Technology
Languages : en
Pages : 1766
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Author: United States. National Aeronautics and Space Administration
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Category :
Languages : en
Pages :
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
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Author:
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ISBN:
Category : Science
Languages : en
Pages : 944
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Author:
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ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1196
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