Normalization of Wind-Tunnel Data for NASA Common Research Model

A wind-tunnel test of an 80%-scale copy of the NASA Common Research Model was performed by the Japan Aerospace Exploration Agency using its 2  m×2  m transonic wind tunnel. The wind-tunnel model was fabricated by the Japan Aerospace Exploration Agency in consultation with NASA Langley Research Center and AIAA Drag Prediction Workshop committee members. The static aerodynamic forces and surface pressure distributions on the wing of the Japan Aerospace Exploration Agency model were measured at a relatively low Reynolds number of 2.27×106 due to tunnel capability limitations, where boundary-layer transition was simulated using optimized roughness. Measured data were compared with those of wind-tunnel tests of the Common Research Model obtained from NASA Langley Research Center’s National Transonic Facility as well as computational fluid dynamics predictions, both at a Reynolds number of 5.0×106. The comparison among these datasets required data normalization to the designed shape aligned at a reference condi...

[1]  Gregory G. Zilliac,et al.  A Comparison of the Measured and Computed Skin Friction Distribution on the Common Research Model , 2011 .

[2]  Edward N. Tinoco,et al.  Summary of Data from the Second AIAA CFD Drag Prediction Workshop (Invited) , 2004 .

[3]  S. Obayashi,et al.  Convergence acceleration of a Navier-Stokes solver for efficient static aeroelastic computations , 1995 .

[4]  Melissa B. Rivers,et al.  Experimental Investigations of the NASA Common Research Model (Invited) , 2010 .

[5]  Melissa B. Rivers,et al.  Experimental Investigation of the NASA Common Research Model , 2014 .

[6]  Kazuhiro Nakahashi,et al.  Some challenges of realistic flow simulations by unstructured grid CFD , 2003 .

[7]  Seigo Koga,et al.  Transonic Wind Tunnel Test of the NASA CRM: Volume 1 , 2014 .

[8]  Hiroshi Akima,et al.  A New Method of Interpolation and Smooth Curve Fitting Based on Local Procedures , 1970, JACM.

[9]  Craig A. Hunter,et al.  Support System Effects on the NASA Common Research Model , 2012 .

[10]  James H. Bell,et al.  Pressure-Sensitive Paint Measurements on the NASA Common Research Model in the NASA 11-ft Transonic Wind Tunnel , 2011 .

[11]  Seigo Koga,et al.  Wall and support interference corrections of NASA common research model wind tunnel tests in JAXA , 2013 .

[12]  Edward N. Tinoco,et al.  Summary of Data from the Fifth AIAA CFD Drag Prediction Workshop , 2013 .

[13]  P. Spalart.  A One-Equation Turbulence Model for Aerodynamic Flows , 1992 .

[14]  Seigo Koga,et al.  Analysis of NASA Common Research Model Dynamic Data in JAXA Wind Tunnel Tests , 2013 .

[15]  Edward N. Tinoco,et al.  Summary of the Fourth AIAA CFD Drag Prediction Workshop , 2010 .

[16]  S. Balakrishna,et al.  Analysis of NASA Common Research Model Dynamic Data , 2011 .

[17]  Kazuomi Yamamoto,et al.  Comparison Study of Drag Prediction for the 4th CFD Drag Prediction Workshop using Structured and Unstructured Mesh Methods , 2010 .

[18]  Melissa B. Rivers,et al.  Experimental Investigations of the NASA Common Research Model in the NASA Langley National Transonic Facility and NASA Ames 11-Ft Transonic Wind Tunnel (Invited) , 2011 .

[19]  John C. Vassberg,et al.  Summary of Data from the First AIAA CFD Drag Prediction Workshop , 2002 .

[20]  Daniel P. Raymer,et al.  Aircraft Design: A Conceptual Approach , 1989 .

[21]  Melissa B. Rivers,et al.  Further Investigation of the Support System Effects and Wing Twist on the NASA Common Research Model , 2012 .

[22]  P. Spalart.  Strategies for turbulence modelling and simulations , 2000 .

[23]  John C. Vassberg,et al.  Development of a Common Research Model for Applied CFD Validation Studies , 2008 .

[24]  S. Obayashi,et al.  Convergence acceleration of an aeroelastic Navier-Stokes solver , 1994 .

[25]  K. Nakahashi,et al.  Reordering of Hybrid Unstructured Grids for Lower-Upper Symmetric Gauss-Seidel Computations , 1998 .