Procedures for Estimating Inlet External and Internal Performance PDF Download
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Author: B. M. Sharp
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 284
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Book Description
Author: B. M. Sharp
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 284
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Book Description
Author: Larry K. Ratliff
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 164
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Book Description
Author: Paul H. Kutschenreuter
Publisher:
ISBN:
Category :
Languages : en
Pages : 23
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Book Description
The problem of determining performance levels of supersonic/hypersonic combustion inlet models is presented. Previous approaches to this problem are discussed and g40thod involving force balance determination of the internal drag is proposed. Results of a computational procedure formulated for calculating inlet performance levels from measured internal drag values are presented. Effects of chemical reactions and exit flow profile nonuniformity are accounted for. Levels of anticipated accuracy, using this technique, are adequate for present applications over a Mach Number range of 8 to 25. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Book Description
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 366
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Book Description
Author: M. R. Mendenhall
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 774
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 444
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Book Description
Author: Michael J. Hemsch
Publisher: AIAA (American Institute of Aeronautics & Astronautics)
ISBN:
Category : Science
Languages : en
Pages : 774
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Book Description
This two-volume set includes discussions of the physics of the fluid mechanics phenomena associated with tactical missile flight and the full range of prediction methods required to analyze current and future missiles. It's a valuable resource for missile aerodynamicists, designers, and researchers.
Author:
Publisher:
ISBN:
Category : Fluid dynamic measurements
Languages : en
Pages : 452
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Book Description
Author: Leonard J. Obery
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 21
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Book Description
An inlet with combined external and internal compression, formed by spike and cowl oblique shocks, and an over-all length of 2.5 inlet diameters was investigated at Mach numbers from 3.0 to 2.0 over a range of angles of attack. At the design Mach number of 3.0 the low angle cowl, which turned the flow supersonically, generated two internal shocks and focused them on the centerbody surface. These compression waves, with their high pressure gradient, were cancelled by abrupt centerbody turning. This investigation showed that with proper boundary-layer control on the centerbody this method of internal compression did not adversely affect the high performance of the inlet.
