Wind tunnel tests were conducted at Mach 0.9 to 1.4; design Mach numbers of nozzles were 2.0 and 2.5 and number of clustered nozzles ranged from 2 to 6; some models were tested with configurations of extended, shrouded, flush, and canted nozzles, results obtained.
Investigation of net-thrust and base-pressure characteristics of cylindrical afterbodies with clustered supersonic nozzles at transonic Mach numbers
NASA -- Tech Notes
1961
46 pages
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Engineering Index Backfile | 1961
|