@techreport{oai:jaxa.repo.nii.ac.jp:00044754,
 author = {柳沢, 三憲 and 菊地, 一雄 and YANAGIZAWA, Mitsunori and KIKUCHI, Kazuo},
 month = {May},
 note = {The unsteady pressure distributions on an oscillating two-dimensional airfoil have been measured in the regions of subsonic and transonic flow, a Reynolds number range from 0.4×10(exp 6) to 2.0×10(exp 6) and a reduced frequency range from 0.01 to 0.1. Results of the experimental investigation are compared with those obtained by use of an incompressible theory and a doublet lattice method based on the lifting surface theory in the all Mach number ranges. In the subcritical regions the correction matrices to account for differences in the experimental and theoretical values have been calculated. In the supercritical regions the pressure deviations from the theoretical values due to the periodical motion of the shock are discussed and illustrated. Results, which are presented for supercritical flow with or without the shock, show that the transonic similarity law is valid in the unsteady reduced lift curve slope., 資料番号: NALTR0501000, レポート番号: NAL TR-501},
 title = {亜音速および遷音速における二次元振動翼面上の非定常圧力分布の測定},
 year = {1977}
}