An Experimental Investigation of a Transverse Jet Ejecting from a Flat Plate Into a Subsonic Free Stream PDF Download
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Author: Troy A. Street Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 468
Book Description
An experimental investigation of the surface static pressures on a flat plate due to a jet injecting transversely into a subsonic free stream was conducted. The free stream Mach numbers were 0.1, 0.2, 0.4, and 0.6 and the jet total pressure ranged from 0 to 1200 psig. The results are presented in tabular form with representative examples of the data shown graphically. (Author).
Author: Troy A. Street Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 468
Book Description
An experimental investigation of the surface static pressures on a flat plate due to a jet injecting transversely into a subsonic free stream was conducted. The free stream Mach numbers were 0.1, 0.2, 0.4, and 0.6 and the jet total pressure ranged from 0 to 1200 psig. The results are presented in tabular form with representative examples of the data shown graphically. (Author).
Author: Craig S. Shaw Publisher: ISBN: Category : Interference (Aerodynamics) Languages : en Pages : 100
Book Description
The induced static pressures due to a highly underexpanded sonic jet ejecting normally from a flat plate into a subsonic crosswind have been investigated. These pressure data have been recorded on the flat plate for a range of nominal jet-to-free-stream dynamic-pressure ratios from 0 to 1000 at free-stream Mach numbers of 0.1, 0.2, 0.4, and 0.6. The static pressure data measured on the flat plate are presented and correlated based upon the Riemann shock geometry in the jet plume. This data correlation improves with increasing free-stream Mach number.
Author: Publisher: ISBN: Category : Languages : en Pages : 312
Book Description
An experimental investigation of a sonic, underexpanded, transverse jet ejecting from a body of revolution into free streams of Mach number range 1. 75 to 4.5 was conducted. The jet was rolled, in 15-degree increments, into the yaw plane for an angle of attack range of -4 to + 10 degrees with a jet total-to-free stream static pressure ratio variations up to 100. Forces and moments were measured and the tabulated data are presented.
Author: Troy A. Street
Author: Troy A. Street
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Author: Craig S. Shaw
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Author: Danny K. Livingston
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Author: United States. Superintendent of Documents
Author: F. W. Spaid
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