Full Read and Download Reference eBook
Performance Of External Compression Bump Inlet At Mach Numbers Of 15 To 20 Book in PDF, ePub and Kindle version is available to download in english. Read online anytime anywhere directly from your device. Click on the download button below to get a free pdf file of Performance Of External Compression Bump Inlet At Mach Numbers Of 15 To 20 book. This book definitely worth reading, it is an incredibly well-written.
Author : Paul C. Simon
Publisher :
Page : 46 pages
File Size : 15,94 MB
Release : 1957
Category : Aerodynamics, Supersonic
ISBN :
Author : Owen H. Davis
Publisher :
Page : 34 pages
File Size : 24,49 MB
Release : 1960
Category : Aerodynamics, Supersonic
ISBN :
Author : John L. Allen
Publisher :
Page : 24 pages
File Size : 18,73 MB
Release : 1960
Category : Airplanes
ISBN :
Author :
Publisher :
Page : 20 pages
File Size : 29,91 MB
Release : 1960
Category :
ISBN :
Author : John L. Allen
Publisher :
Page : 36 pages
File Size : 25,47 MB
Release : 1959
Category : Boundary layer
ISBN :
Author :
Publisher :
Page : 26 pages
File Size : 34,78 MB
Release : 1960
Category :
ISBN :
Author : John L. Allen
Publisher :
Page : 16 pages
File Size : 29,22 MB
Release : 1960
Category :
ISBN :
Author : Donald B. Smeltzer
Publisher :
Page : 252 pages
File Size : 16,24 MB
Release : 1970
Category : Aerodynamics, Supersonic
ISBN :
Author : Leroy L. Presley
Publisher :
Page : 58 pages
File Size : 47,57 MB
Release : 1960
Category : Aerodynamics
ISBN :
Author : Leonard J. Obery
Publisher :
Page : 21 pages
File Size : 23,45 MB
Release : 1957
Category : Aerodynamics, Supersonic
ISBN :
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.