Volume 1, Issue 3, November 2013, Page: 91-98
Numerical Investigation on the Effect of Inlet Conditions on the Oblique Shock System in a High-Speed Wind Tunnel
Mohammad Reza Heidari, Islamic Azad University, Parand Branch, Tehran, IRAN
Mahdi Karami, Islamic Azad University, Parand Branch, Tehran, IRAN
Fata Mohammadi Fard, Islamic Azad University, Parand Branch, Tehran, IRAN
Received: Oct. 20, 2013;       Published: Nov. 30, 2013
DOI: 10.11648/j.ajpa.20130103.16      View  3263      Downloads  176
Abstract
The Present study is conducted to find out the best inlet conditions for designing process of a high-speed wind tunnel. The inlet conditions are appropriate for the cases that the real nozzle has not been calculated and downstream parts designers (such as test section and diffuser designers) need a reasonable upstream flow condition for their calculations. Inlet boundary condition of each case has been specified by User-Defined Function. The process of User-Defined Function (UDF) specification is time-consuming and is based on a try and error method. Several cases of inlet conditions have been designed and examined. The comparison of results is shown in terms of cross-sectional and axial distributions of parameters and contours of Mach number and static pressure. Finally, the 1.2 m-length Ogive curve with 0.5 degree initial angle and after that, the case of 1.2 m-length ducthave been chosen as the equivalent nozzles.
Keywords
High-Speed Flow, Wind Tunnel Design, Nozzle Curve Calculations, Computational Fluid Dynamics, Equivalent Nozzle
To cite this article
Mohammad Reza Heidari, Mahdi Karami, Fata Mohammadi Fard, Numerical Investigation on the Effect of Inlet Conditions on the Oblique Shock System in a High-Speed Wind Tunnel, American Journal of Physics and Applications. Vol. 1, No. 3, 2013, pp. 91-98. doi: 10.11648/j.ajpa.20130103.16
Reference
[1]
J.M.A.Longo,"Modeling of high-speed flow phenomena," RTO AVI Lecture series on Critical Technologies for High-speed Vehicle Development, Belgium, May, 2004.
[2]
R.E. Deem, "Pressure and heat-transfer distribution tests on a standard ballistic-type model HB-2 at mach 2 to 5, including the effects of shock impingement," Report S-R6, Douglas Aircraft Company, California, USA, Jun, 1963.
[3]
J.D. Gray, and E. E. Lindsay, "Summary report on aerodynamic characteristics of standard model HB-1 and HB-2," Technical report AEDC-TDR-63-137, Arnold engineering development center, USA, 1964.
[4]
S. Kuchi-Ishi, And E. Watanabe, "Comparative force/heat flux measurements between JAXA hypersonic test facilities using standard model HB-2 Part 1&2," JAXA research and development report, Japan Aerospace Exploration Agency, Japan, 2005.
[5]
J.D.Anderson, "Modern compressible flow with historical perspective," McGraw-Hill Inc., New York, 2003.
[6]
Group of writers, "Handbook of supersonic aerodynamics," Vol.6. Sec.17 Ducts, Nozzles and Diffusers, NAVWEPS Report 1488, 1964.
[7]
B. E. Launder, N. D. Sandham, "Closure strategies for turbulent and transitional flows," Cambridge University Press, Cambridge, UK, 2002.
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