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 condition, because the wing deformation of the wind-tunnel models deformed due to the dynamic pressure and the Reynolds number was different between the Japan Aerospace Exploration Agency and the National Transonic Facility tests. In this paper, the normalization procedures, in addition to basic wind-tunnel corrections, are proposed and the corrected results are examined. Presented as Paper 2013-0493 at the 51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Grapevine (Dallas/Ft. Worth Region), TX, 7-10 January 2013
Normalization of Wind-Tunnel Data for NASA Common Research Model
Journal of aircraft ; 52 , 5
2015
Article (Journal)
English
Grid Assessment Using the NASA Common Research Model (CRM) Wind Tunnel Data
British Library Conference Proceedings | 2013
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