@article{oai:jaxa.repo.nii.ac.jp:00035499,
 author = {岡本, 哲史 and 毛利, 浩 and OKAMOTO, Tetusi and MORI, Hirosi},
 issue = {228},
 journal = {東京帝國大學航空研究所報告, Report of Aeronautical Research Institute, Tokyo Imperial University},
 month = {Apr},
 note = {飛行機の高速化に伴ひ翼の摩擦抗力を減少せしめる事及び造波失速を遲らす事が問題になつて來た.翼の摩擦抗力を減少せしめるためには根本策として翼表面の境界層を出來るだけ層流に保つ事が望ましく,遷移が壓力上昇勾配に關係する事を考へれば翼表面に沿ふ壓力上昇勾配を出來るだけ緩かにする事が必要になる.このためには翼の最大厚位置を從來のものより幾分後退せしめねばならぬ.斯くすれば翼表面の最低壓力を高める事にもなるから,この事は造波失速の見地から見ても好都合の事である.かかる種類の翼型は既に我國でも設計されてゐるが,これらは凡て厚さ分布を多項式で表はしてゐる.この論文ではやり方を變へて厚さ分布即ち對稱翼型を吹出しと吸込みの組合せに依つて求めて見た.その結果これ迄にあまり得られてゐない樣な,壓力分布が翼の大部分で平坦になる樣な翼型を得る事が出來た., In order to reduce the frictional drag of the aerofoil it is desirable that the flow in the boundary layer retains laminar as possible along the surface. As the increasing pressure gradient is a cause of early transition from laminar to turbulent flow, it is necessary to make small the increasing pressure gradient along the surface. For this purpose the point of the maximum thickness of the aerofoil section must be shifted suitably backward. In the present paper the symmetrical aerofoil sections of such kinds were designed by the method of sources and sinks and the aerofoils with nearly uniform pressure distribution were obtained., 資料番号: SA4148262000},
 pages = {462--478},
 title = {Design of Symmetrical Aerofoil Sections Suitable for High Speeds.},
 volume = {17},
 year = {1942}
}