@inproceedings{oai:jaxa.repo.nii.ac.jp:00036828,
 author = {吉田, 憲司 and 生越, 博景 and 石田, 洋治 and 野口, 正芳 and Yoshida, Kenji and Ogoshi, Hirokage and Ishida, Yoji and Noguchi, Masayoshi},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {May},
 note = {超音速層流制御(SLFC)を応用した空力設計システムを開発するために、遷移予測法の数値的研究とSLFCの影響についての実験的研究を行った。第1段階で、線形安定性の解析システムを開発し、いくつかの代表例において評価された増幅率について良い確認を得た。第2段階で、経験的e{N}法を用いて遷移予測システムを開発し、2代表例において評価N因子について良い確認を得た。第3段階で、いくつかの遷移データと超音速流におけるSLFCの影響とを得るために、独自に設計した、たわみデルタ翼モデルを用いて風洞試験を実施した。最後に、モデルの遷移特性の解析を試み、マッハ1.4の遷移においてNが約7の有用な結果を得た。, To develop an aerodynamic design system applying Supersonic Laminar Flow Control (SLFC), numerical study on a transition prediction method and experimental study on the effect of SLFC were performed. In the first phase of study, an analysis system of linear stability was developed and good validation for the estimated amplification rate in several typical cases was obtained. In the second phase, a transition prediction system was developed by applying an empirical e(sup N) method and good validation for the estimated N-factor was obtained in two typical cases. In the third phase, wind tunnel tests using an originally designed warped delta wing model were carried out to obtain some data of transition and the effect of SLFC under supersonic flow condition. And finally the transition characteristics analysis of the model was tried and the useful result of N approximately = 7 at transition at Mach 1.4 was obtained., 資料番号: AA0000440005, レポート番号: NAL SP-31},
 pages = {59--79},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {Numerical study on transition prediction method and experimental study on effect of supersonic laminar flow control},
 volume = {31},
 year = {1996}
}