The goal of the Contrails project is to help preserve and disseminate the technical record of 20th century aerospace research, highlighting in particular the research endeavors of the Illinois Tech community.

Measurements of Pressure and Speed of Flow in a Spark-Heated Hypersonic Wind Tunnel

Report Number: AEDC TDR 62-218
Author: Karamcheti, Krishnamurty
Author: Vali, Walter
Author: Kyser, James B.
Author: Rasmussen, Maurice L.
Corporate Author: Stanford University
Laboratory: Arnold Engineering Development Center
Date of Publication: 1962-11
Pages: 57
Contract: AF 40(600)-930
Project: 8952
Task: 895210
AD Number: AD0288668

The nature of the flow and state of the gas in the nozzle and test section of the Stanford spark-heated hypersonic wind tunnel was studied. Attention is given only to the pressure and speed-of-flow measurements. Results are presented for pitot pressures and wall static pressures. The speed of flow in the test section is derived from measurements made by spark-schlieren photographs of a disturbance created in the flow by means of a spark discharge. On the basis of these measurements, it is concluded that the actual stagnation enthalpy of the stream is likely to be different from the enthalpy calculated according to current practice. As a consequence, it is shown that serious errors may occur in the calculated values for the state of the flow, and in theoretical estimates of quantities such as stagnation-point heat-transfer rates.

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