Publication Date:
2019-07-13
Description:
The AEDC perforated-wall boundary condition has been incorporated into the NASA Ames OVERFLOW code and has been used to calculate the tunnel flow field in the AEDC Aerodynamic Wind Tunnel (16T) over a three-percent model of the Space Shuttle Launch Vehicle. Tunnel flow-field calculations have been performed for two supersonic flow-field conditions, including one near sonic condition. Wall interference assessments and analyses have been performed by making detailed comparisons of the tunnel flow-field calculations with corresponding free-air flow-field calculations and with tunnel data from different scale models. A capability to assess wall interference at low supersonic conditions and to improve data correlations with CFD results by adding the tunnel wall boundary condition is demonstrated.
Keywords:
AERODYNAMICS
Type:
AIAA PAPER 93-0420
,
AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States|; 17 p.
Format:
text
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