@techreport{oai:jaxa.repo.nii.ac.jp:00044930,
 author = {石黒, 登美子 and 神谷, 信彦 and 河合, 伸坦 and 小口, 慶子 and ISHIGURO, Tomiko and KAMIYA, Nobuhiko and KAWAI, Nobuhiro and OGUCHI, Keiko},
 month = {May},
 note = {The Purpose of Part II of the paper is to present a user’s manual for the FORTRAN program which is coded following the numerical procedure developed for design of transonic airfoils. This procedure, described in Part I, has the following characteristics: 1)It can solve the inverse problem irrespective of the presence of shock waves. 2)The airfoil geometry is designed so that the width of the trailing edge is the required one. 3)The boundary layer calculation is included in this procedure: An actual airfoil geometry is obtained by subtracting a displacement thickness of a boundary layer from an airfoil geometry., 資料番号: NALTR0673000, レポート番号: NAL TR-673},
 title = {Transonic Airfoil Design of Full Potential Flow II. Development of the FORTRAN Code},
 year = {1981}
}