@inproceedings{oai:jaxa.repo.nii.ac.jp:00038237,
 author = {Jeong, Shinkyu and Jeong, Shinkyu},
 book = {航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2002論文集, Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2002},
 month = {Mar},
 note = {Inverse method is applied to geometry estimation of wind tunnel models. By defining the pressure distribution obtained from wind tunnel test as the target of inverse method, approximate geometry estimation is possible. The inverse method used in this paper is based on Takanashi's concept that utilizes integral equations and residual-correction technique. Geometry of two wind tunnel models were estimated. One is 23.5 percent scale and the other is 8.5 percent scale of NEXST-1 (National Experiment Supersonic Transport). The deviation of the estimated value from the original CATIA geometry was within a reasonable order if manufacturing limitation is considered. The geometry of the 8.5 percent scale wind tunnel model was measured for validation by using a non-contact three-dimensional measuring device employing laser beam and auto-focus system. The result shows the validity of the present method for approximate geometry estimation., 資料番号: AA0045948016, レポート番号: NAL SP-57},
 pages = {89--93},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {Application of inverse method to mutual verification of CFD-EFD},
 volume = {57},
 year = {2003}
}