Effect of Gradient Reconstruction Method on Transonic Fan Performance Conference Paper uri icon


  • 2017 by Forrest L. Carpenter. This paper presents an investigation of the choice of gradient evaluation method on the performance of a transonic fan, namely NASA Rotor 67. Turbulent solutions were computed using gradients found via the Green-Gauss, un-weighted least-squares with QR decomposition (LSQR), weighted LSQR (WLSQR), and weighted essential non-oscillatory (WENO) methods. Partial speedlines at the design wheel speed were computed for each gradient case, and the flow at the near peak efficient point was analyzed. The un-weighted LSQR gradient solutions were found to under-predict all performance quantities, while the other three methods showed good agreement with experiment. Increased flow separation was found to be associated with the un-weighed LSQR solutions, leading to higher losses.

name of conference

  • 55th AIAA Aerospace Sciences Meeting

published proceedings

  • 55th AIAA Aerospace Sciences Meeting

author list (cited authors)

  • Carpenter, F. L., & Cizmas, P. G.

citation count

  • 1

complete list of authors

  • Carpenter, Forrest L||Cizmas, Paul G

publication date

  • January 2017