Paper deals with development for converting Langley 19-ft pressure tunnel for transonic operation; good test section Mach number distributions were obtained up to Mach number 1.26 for length equal to one tunnel height with slot length equal to 2 tunnel heights; performance with short diffusers was never as good as with 6.4° diffuser; rapid test section Mach number changes were achieved by bleeding h-p air into slot flow plenum chamber.
Development of 8-inch by 8-inch slotted tunnel for Mach numbers up to 1.28
NASA -- Tech Note
1961
72 pages
Report
English
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