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Source Flow Effects In Conical Hypervelocity Nozzles

Report Number: AEDC TDR 62-116
Author: Whitfield, Jack D.
Author: Norfleet, Glenn D.
Corporate Author: Arnold Engineering Development Center Arnold Air Force Station Tenn
Laboratory: Arnold Engineering Development Center
Date of Publication: 1962-06
Pages: 20
Contract: AF 40(600)-800
Project: 8952
Task: 895202
AD Number: AD0276724

Source flow effects in conical hypervelocity nozzles are studied by means of a simple Newtonian theory for slender conical bodies. Experiments were conducted to examine the validity of this simple theoretical approach and a semiempirical theory is developed to assess the magnitude of source flow effects. Significant source flow effects were found, and the need for contoured hypervelocity wind tunnel nozzles is shown.

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