Shock Curvature due to Boundary-Layer Effects in a Shock Tube

Journal Article · Fri Sep 01 04:00:00 EDT 1961 · Physics of Fluids (New York)

DOI:https://doi.org/10.1063/1.1706450· OSTI ID:4841189

Hartunian, R. A.

A two-dimensional, linearized treatment, including real gas effects, of shock curvature in a shock tube is presented. An expression for shock shape as a function of shock Mach number and initial pressure of the test gas is presented. The results are compared with the available experimental data obtained in argon at low shock strengths and in air at high shock Mach numbers. Within the scatter of the data in the latter experiments, there is relatively good agreement with theory, while theory falls approximately 30 plus or minus 10% above the data in argon. Some of this disagreement is attributed to application of the two- dimensional theoretical result to axisymmetric shock tubes of finite dimensions used in the experiments. (auth)

• Research Organization: Aerospace Corp., Los Angeles
• Sponsoring Organization: USDOE
• NSA Number: NSA-15-030137
• OSTI ID: 4841189
• Journal Information: Physics of Fluids (New York), Journal Name: Physics of Fluids (New York) Journal Issue: 9 Vol. 4; ISSN 0031-9171; ISSN PFLDAS
• Publisher: American Institute of Physics
• Country of Publication: Country unknown/Code not available
• Language: English

Related Subjects

AIR
ARGON
GASES
MEASURED VALUES
PHYSICS
PRESSURE
SHOCK WAVES
TUBES