@techreport{oai:jaxa.repo.nii.ac.jp:00039964,
 author = {渡辺, 光則 and 野村, 茂昭 and 山本, 行光 and 吉沢, 昭 and 穂積, 弘一 and 小山, 忠勇 and Watanabe, Mitsunori and Nomura, Shigeaki and Yamamoto, Yukimitsu and Yoshizawa, Akira and Hozumi, Koichi and Koyama, Tadao},
 month = {Jul},
 note = {極超音速流中に置かれた鈍頭度の大きいカプセル形状模型の頭部中心から超音速ジェットの逆噴射を行い、広い迎角範囲にわたって空力特性への影響を実験的に調べた。試験は航技研50cmφ極超音速風洞を用いて、マッハ数7.1、レイノルズ数4.0×10(exp 4)(1/cm)および迎角0〜15度の試験条件で行われた。風洞模型はジェミニ型と呼ばれるカプセル形状で、鈍頭度4.0の扁平な球形頭部に逆円錐・円柱の後部を持った形状である。模型頭部の中心から基準マッハ数3.05の超音速ジェットの逆噴射を行い、模型表面の圧力分布の測定およびシュリーレン写真によるジェットと衝撃波の干渉の可視化を行った。測定した表面圧力分布を積分して抵抗係数、揚力係数および揚抗比を求め、衝撃波/ジェットの干渉写真と合わせて検討した結果、逆噴射ジェットの流量が空力特性に大きな影響を及ぼし、その結果が迎角に大幅に依存することが分かった。, The effects of supersonic retrojets on the aerodynamic characteristics of a capsule type model with a spherical nose of large bluntness were investigated experimentally in a hypersonic flow. Tests were conducted in the NAL phi 50 cm hypersonic wind tunnel at conditions of Mach number 7.1, Reynolds number of 4.0 x 10(exp 4) (1/cm) and angles of attack from 0 to 15 degrees. The capsule model has the so-called GEMINI type configuration: a spherical forebody with bluntness ratio of 4.0 (spherical nose radius/base radius) followed by a conical boat-tail and a cylinder. The tests were conducted by focusing on the effect of the blowing rate of a supersonic retrojet of a nominal Mach number 3.05 ejected perpendicularly at the capsule nose center and on the effect of model attack angles. The retrojet was found to have a large effect on drag and lift coefficients that were calculated by integrating the measured pressure distributions. The aerodynamic interaction phenomena between a main flow and a retorojet were studied to understand those effects by investigating schlieren pictures and surface pressure distribution., 資料番号: AA0001080000, レポート番号: NAL TR-1329},
 title = {極超音速流中における超音速逆噴射のカプセル空力特性への影響},
 year = {1997}
}