Effects of wall to stagnation temperature ratio on hypersonic corner flows

Aziz Ş., Kavsaoǧlu M. Ş., Kaynak Ü.

35th AIAA Fluid Dynamics Conference and Exhibit, Toronto, Kanada, 6 - 09 Haziran 2005, (Tam Metin Bildiri)

  • Yayın Türü: Bildiri / Tam Metin Bildiri
  • Basıldığı Şehir: Toronto
  • Basıldığı Ülke: Kanada
  • Ankara Yıldırım Beyazıt Üniversitesi Adresli: Hayır

Özet

Numerical solutions of laminar, hypersonic, viscous, high temperature, perfect gas flows over compression corners are obtained. The effects of corner angle (θw) and wall to stagnation temperature ratio (Tw/T0) on flow variables, especially on surface pressure distributions and surface heat transfer rates are investigated. A three dimensional, compressible, Reynolds averaged thin layer Navier-Stokes code is used. The numerical method is a stream-wise upwind finite difference method with Lower Upper-Alternating Direction Implicit (LU-ADI) decomposition. Eight different free-stream and wall conditions and seven different corner angles ranging from θw=5° to 24° are considered. The results are presented in terms of boundary layer properties, surface pressure distribution, heat transfer rates and compared with the available experimental results and theory. © 2005 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.