@techreport{oai:jaxa.repo.nii.ac.jp:00044295,
 author = {柳沢, 三憲 and 石井, 孝雄 and YANAGIZAWA, Mitsunori and ISHII, Takao},
 month = {Mar},
 note = {The aerodynamic derivatives of a biconvex-flat airfoil (thickness ratio of 10 per cent), and double-wedge airfoils (thickness ratios of 10, 15, 20 percent), performing pitching oscillation in supersonic flow at the range of Mach number2-3, were measured and compared with the linearized theory, piston theory and Van Dyke's nonlinear theory which includes the effect of the airfoil thickness. The tested reduced frequency range was 0.01-0.05 and the Reynolds number range was 2.8 by 10(6)-3.6 by10(6) based on the chord length. In spite of the existence of the detached shock wave in front of the leading edge of the biconvex-flat airfoil, all experimental results agree quite well with the nonlinear theory. Schlieren photographs were taken in order to observe the flow field around the airfoils., 資料番号: NALTR0057000, レポート番号: NAL TR-57},
 title = {超音速二次元翼の非定常ピッチングモーメント係数の測定},
 year = {1967}
}