@techreport{oai:jaxa.repo.nii.ac.jp:00043772,
 author = {河崎, 俊夫 and 河本, 巌 and 戸田, 勧 and KAWASAKI, Toshio and KAWAMOTO, Iwao and TODA, Susumu},
 month = {Dec},
 note = {Free flight model FFM-1O equipped with NAL-7 rocket motor has been developed for the purpose of investigating the aerodynamic characteristics of a supersonic aircraft at subsonic and supersonic speeds.  In order to attain supersonic speed by use of a relatively small thrust motor, particular attentions was paid to the reduction of weight. To reduce the weight of FFM-10, it is most effective to reduce the thickness of the wing and the fuselage.  As the result, lift distributions on the wing and the fuselage cause the deflections of the wing and fuselage, which bring about reduction of the lift distributions on them. In other words, the aerodynamic derivatives for a flexible FFM-10 become smaller than those for the solid case.  The present paper treats the theoretical estimation of the reductions in aerodynamic derivatives such as CLa, C,,,.a, Cra and Cgu2 for a flexible FFM-10, and the wind tunnel data for FFM-10 are revised by taking these reductions into account., 資料番号: NALTM0188000, レポート番号: NAL TM-188},
 title = {自由飛行模型FFM-10の空力微係数におよぼす機体弾性変形の影響について},
 year = {1970}
}