Wind-tunnel Investigation of Favorable Interference to Increase Lift-drag Ratios of Supersonic Aircraft: Part Ii: an Optimized Wing-body-inlet Configuration PDF Download
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Author: Richard M. HARTLEY Publisher: ISBN: Category : Languages : en Pages : 46
Book Description
The results of wind-tunnel tests conducted at a Mach number of 2.87 to investigate favorable interference effects on wing-body-inlet configurations are presented. The engine air inlet location and the body indentation angle for maximum lift increments were determined. These favorable lift increments correspond to about 20 percent of the cruise lift required for an attack aircraft. A fence, attached to the wing to reflect the shock wave emanating from the engine air inlet and to intensify the pressure field, increased the inboard lift but not sufficiently to overcome the resulting loss in lift ffrom the outboard section of the wing. (Author).
Author: Richard M. HARTLEY Publisher: ISBN: Category : Languages : en Pages : 46
Book Description
The results of wind-tunnel tests conducted at a Mach number of 2.87 to investigate favorable interference effects on wing-body-inlet configurations are presented. The engine air inlet location and the body indentation angle for maximum lift increments were determined. These favorable lift increments correspond to about 20 percent of the cruise lift required for an attack aircraft. A fence, attached to the wing to reflect the shock wave emanating from the engine air inlet and to intensify the pressure field, increased the inboard lift but not sufficiently to overcome the resulting loss in lift ffrom the outboard section of the wing. (Author).
Author: Richard M. Hartley Publisher: ISBN: Category : Languages : en Pages : 34
Book Description
Wind-Tunnel tests at a Mach number of 2.87 were to measure the intensity and spatial distribution of low-pressure fields that radiate back from an indented side portion of a body and the high-pressure fields that radiate from the external wedge sides of an engine air inlet. The measured pressure distributions were integrated over a proposed thin flat-plate wing proposed for separating the body and inlet fields. The resulting favorable increase in normal-force coefficient was as much as 0.035 at zero angle of attack and corresponds to about 15 percent of the cruise lift required for an attack aircraft. (Author).
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 648
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Author: Richard M. HARTLEY
Author: Richard M. HARTLEY
Author: Richard M. Hartley
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Author: Mark R. Nichols
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