Design of nozzle for tunnel which operates between limits Mach number 1.0 to Mach number 2.0; in arriving at solution, aerodynamic as well as mechanical phases of problem are considered. Bibliography. Thesis Submitted to Case School of Applied Science in Partial Fulfillment of Requirements for Degree of Master of Science in Mechanical Engineering.
Design of variable-throat rectangular nozzle for supersonic wind tunnel
Nat Advisory Committee Aeronautics -- Publ
1947
68 pages
20 Supp sheets
Article (Journal)
English
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NTIS | 1965
|NTIS | 1965
|Nozzle Throat Optimization for Supersonic Jet Noise Reduction
British Library Conference Proceedings | 2012
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