Sidewall boundary-layer removal effects on wall adaptation in the Langley 0.3-meter transonic cryogenic tunnel
Author:
Affiliation:
1. Vigyan Research Associates, Inc., Hampton, VA
2. NASA, Langley Research Center, Hampton, VA
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1989-148
Reference18 articles.
1. Most of the measurement points in the boundary-layer lie in the outer region of the turbulent boundary-layer. Hence a power-law approximation was used to extrapolate the data from the wall to the first tube. The index n in the power law (y a u'/) is about 7 for all conditions with no removal, in the Mach number range 0.3-0.8 (figure 7). However, n was shown to be highly dependent on the boundary-layer removal rate, increasing from about 7 with no removal to about 13 with removal (figure 8). The measured velocity profiles for different non-zero boundary-layer removal rates show good correlation (figure 9), when plotted in terms of the momentum thickness (y/B).
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