Flow field calculation in supersonic mixed-compression aircraft inlets at angle of attack using the three-dimensional method of characteristics with discrete shock wave fitting
Language: English Series: Publication details: n.p. ; Purdue University, ; 1977Edition: Description: xiv,243 p; 22 cmISBN: 0Subject(s): | Aerodynamics, Supersonic | Shock waves| Item type | Current library | Call number | Status | Notes | Date due | Barcode | Item holds |
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Books
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Central Library, IITB | 621.454:533.6.07 Vad | Available | G40B12 | 116755 |
Total holds: 0
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