Free-flight and wind-tunnel data for a generic fighter configuration

1984 ◽  
Vol 21 (1) ◽  
pp. 5-13 ◽  
Author(s):  
G.L. Winchenbach ◽  
R. L. Uselton ◽  
W. H. Hathaway ◽  
R. M. Chelekis
Keyword(s):  
Wind Tunnel ◽  
Free Flight ◽  
Wind Tunnel Data

Comparison of free-flight and wind tunnel data for a generic fighterconfiguration

1982 ◽  
Author(s):  
G. WINCHENBACH ◽  
R. CHELEKIS ◽  
B. USELTON ◽  
W. HATHAWAY
Keyword(s):  
Wind Tunnel ◽  
Free Flight ◽  
Wind Tunnel Data

Comparisons of free-flight and wind-tunnel data on slender cones

AIAA Journal ◽  
1965 ◽  
Vol 3 (2) ◽  
pp. 379-380 ◽  
Author(s):  
JACK D. WHITFIELD ◽  
B. J. GRIFFITH
Keyword(s):  
Wind Tunnel ◽  
Free Flight ◽  
Wind Tunnel Data

A Kriging Approach for CFD/Wind-Tunnel Data Comparison

2005 ◽  
Vol 128 (4) ◽  
pp. 847-855 ◽  
Author(s):  
J.-C. Jouhaud ◽  
P. Sagaut ◽  
B. Labeyrie
Keyword(s):  
Wind Tunnel ◽  
Response Surface ◽  
Uncertain Parameters ◽  
Free Flight ◽  
Wind Tunnel Experiments ◽  
Data Comparison ◽  
Wind Tunnel Data ◽  
Compressible Turbulent Flow ◽  
Kriging Approach ◽  
Insight Into

A Kriging-based method for the parametrization of the response surface spanned by uncertain parameters in computational fluid dynamics is proposed. A multiresolution approach in the sampling space is used to improve the accuracy of the method. It is illustrated considering the problem of the computation of the corrections needed to recover equivalent free-flight conditions from wind-tunnel experiments. Using the surface response approach, optimal corrected values of the freestream Mach number and the angle of attack for the compressible turbulent flow around the RAE 2822 wing are computed. The use of the response surface to gain an insight into the sensitivity of the results with respect to other parameter is also assessed.

scholarly journals Aerodynamic Free-Flight Conditions in Wind Tunnel Modelling through Reduced-Order Wall Inserts

Fluids ◽  
2021 ◽  
Vol 6 (8) ◽  
pp. 265
Author(s):  
Narges Tabatabaei ◽  
Ramis Örlü ◽  
Ricardo Vinuesa ◽  
Philipp Schlatter
Keyword(s):  
Wind Tunnel ◽  
Layer Growth ◽  
Wind Tunnels ◽  
Good Representation ◽  
Free Flight ◽  
Local Pressure ◽  
Experimental Realization ◽  
Reduced Order ◽  
Moderate Reynolds Number ◽  
Wind Tunnel Data

Parallel sidewalls are the standard bounding walls in wind tunnels when making a wind tunnel model for free-flight condition. The consequence of confinement in wind tunnel tests, known as wall-interference, is one of the main sources of uncertainty in experimental aerodynamics, limiting the realizability of free-flight conditions. Although this has been an issue when designing transonic wind tunnels and/or in cases with large blockage ratios, even subsonic wind tunnels at low-blockage-ratios might require wall corrections if a good representation of free-flight conditions is intended. In order to avoid the cumbersome streamlining methods especially for subsonic wind tunnels, a sensitivity analysis is conducted in order to investigate the effect of inclined sidewalls as a reduced-order wall insert in the airfoil plane. This problem is investigated via Reynolds-averaged Navier–Stokes (RANS) simulations, and a NACA4412 wing at the angles of attack between 0 and 11 degrees at a moderate Reynolds number (400 k) is considered. The simulations are validated with well-resolved large-eddy simulation (LES) results and experimental wind tunnel data. Firstly, the wall-interference contribution in aerodynamic forces, as well as the local pressure coefficients, are assessed. Furthermore, the isolated effect of confinement is analyzed independent of the boundary-layer growth. Secondly, wall-alignment is modified as a calibration parameter in order to reduce wall-interference based on the aforementioned assessment. In the outlined method, we propose the use of linear inserts to account for the effect of wind tunnel walls, which are experimentally simple to realize. The use of these inserts in subsonic wind tunnels with moderate blockage ratio leads to very good agreement between free-flight and wind tunnel data, while this approach benefits from simple manufacturing and experimental realization.

scholarly journals An overview of X-38 Hypersonic Wind Tunnel data and comparison with numerical results

1997 ◽  
Author(s):  
Charles Campbell ◽  
Jose Caram ◽  
Scott Berry ◽  
Michael DiFulvio ◽  
Tom Horvath ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Numerical Results ◽  
Hypersonic Wind Tunnel ◽  
Wind Tunnel Data
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