Flow over a wall-mounted, 2-D hump at high Reynolds number

This configuration is a wall-mounted Glauert-Goldschmied type body, geometrically similar to that employed in [1] Full details of the current case are given in [2-4]. The model is mounted between two glass endplate frames and both leading edge and trailing edges are faired smoothly with a wind tunnel splitter plate. This is a nominally two-dimensional experiment, although there are side-wall effects (3-D flow) near the end-plates.

The hump is 420 mm (hump cord length) long with the crest of 53.7 mm and is mounted on a splitter plate of thickness 12.7 mm, which extends 1935 mm upstream from the hump leading edge and 1129 mm downstream from the hump leading edge. The characteristic Reynolds number based on the hump length, is about 106 and the Mach number is 0.1.

Geometry of the flow configuration considered

Experimental data:

Experimental results containing base plate pressure and friction factor, and PIV of mean U and V velocity, uu, vv and uv stress components are available at different streamwise locations. Only the baseline case (no control) is studied in ATAAC. The present configuration was used as the test case on three computational workshops:

Accordingly, large numerical database obtained with different RANS models, LES and DES is available in addition to the experimental results.


  • [1] Seifert, A. and Pack, L. G. (2002): Active Flow Separation Control on Wall-Mounted Hump at High Reynolds Numbers. AIAA Journal, Vol. 40, No. 7, July 2002.
  • [2] Greenblatt, D., Paschal, K. B., Yao, C.-S., Harris, J., Schaeffler, N. W., Washburn, A. E. (2004): A Separation Control CFD Validation Test Case, Part 1: Baseline and Steady Suction. AIAA Paper No. 2004-2220 (also in AIAA Journal, Vol. 44, No. 12, 2006, pp. 2820-2830).
  • [3] Greenblatt, D., Paschal, K. B., Yao, C.-S., Harris, J. (2005): A Separation Control CFD Validation Test Case, Part 2: Zero Efflux Oscillatory Blowing. AIAA Paper No. 2005-0485 (also in AIAA Journal, Vol. 44, No. 12, 2006, pp. 2831-2845).
  • [4] Naughton, J. W., Viken, S. A., Greenblatt, D. (2004): Wall Shear Stress Measurements on the NASA Hump Model for CFD Validation. AIAA Paper No. 2004-2607 (also in AIAA Journal, Vol. 44, No. 6, 2006, pp. 1255-1265).

Topic revision: r1 - 2011-01-25 - 14:19:45 - FlavienBillard
30 Apr 2017
EU-Flag4ATAAC-website.jpg FP7-coo-RGB.gif

Public Pages:
home Home


Interested in Hybrid RANS-LES Modeling? 5th HRLM Symposium on 19-21 March 2014 See: www.hrlm-symposium.org hrlm_0.png

Related Links:


Advanced Turbulence Simulation for Aerodynamic Application Challenges
A Seventh Framework Project

Copyright © by the contributing authors. Unless noted otherwise, all material on this web site is the property of the contributing authors.