@techreport{oai:jaxa.repo.nii.ac.jp:00044059,
 author = {山本, 行光 and 渡辺, 光則 and 野村, 茂昭 and 穂積, 弘一 and 小山, 忠勇 and YAMAMOTO, Yukimitsu and WATANABE, Mitsunori and NOMURA, Shigeaki and HOZUMI, Koichi and KOYAMA, Tadao},
 month = {Oct},
 note = {Hypersonic wind tunnel tests were made to determine the aerodynamic characteristics of some capsule type re-entry bodies at Mach number 7.1 and at angles of attack from 0°to 20°.The Reynolds number based on maximum body diameter varied from 4.5 × 105 to 18×105.Tests were made to determine the appropriate nose and shoulder radii of these capsules necessary to obtain optimum configurations for the aerodynamic requirements.The nose radius R1 is changed from 2 to 4 and shoulder radius R2 from 0 to 0.1,which are nondimensionalized by the maximum radius R3 of the sharp shoulder capsules,respectively.Results of the tests indicate that higher lift to drag ratio L/D and lower trim angles δ can be obtained by increasing the nose radius.The same trends are shown when decreasing the shoulder radius.The Reynolds number shows a slight effect on the lift and drag coefficients CL,CD,but no remarkable differences can be seen in other aerodynamic coefficients., 資料番号: NALTM0476000, レポート番号: NAL TM-476},
 title = {カプセル型回収体の極超音速三分力測定試験},
 year = {1982}
}