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Published June 4, 2015 | Submitted
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Aerodynamic Studies in the Shock Tube


In order to utilize the shock tube for quantitative investigations of some aerodynamic problems a thin platinum film resistance thermometer was developed for heat transfer rate measurements. The present report describes the construction and calibration of the heat transfer gage. Since the experimental technique presents a major problem this investigation has been carried out in the straight section of the shock tube where the flow conditions are well defined and readily measured. These flow conditions were calculated utilizing the most recent NBS data on air properties at high temperatures. The flow conditions were also measured utilizing the heat transfer gage and several independent experimental techniques, and good agreement was found with the equilibrium flow calculations after an initial period of 30 - 50 μ sec. Measurements of the heat transfer rate at the forward stagnation point and on the circumference of a circular cylinder are reported and compared with the theoretical calculations of L. Lees. A method for deduction of surface pressure distribution from the laminar boundary-layer heat transfer data is also presented.

Additional Information

Hypersonic Research Project Memorandum No. 38. Army Ordnance Contract NO. DA-04-495-Ord-19. Army Project No. 5B0306004. Ordnance Project No. TB3-0118. OOR Project No. 1600-PE.

Attached Files

Submitted - Memorandum_No._38.pdf


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October 23, 2023