@techreport{oai:jaxa.repo.nii.ac.jp:00043175,
 author = {高梨, 進 and Takanashi, Susumu},
 month = {Nov},
 note = {A numerical solution of the transonic integral equations is presented for three-dimensional transonic wing design. The objective of the design problem is to determine the wing geometry which realizes a prescribed pressure distribution on the wing surface. This boundary value problem can be formulated by the transonic integral equations with artificial viscosity terms. The resulting integral equations are sinrplified by introducing an approximate function for the space velocity distribution which reduces the three-dimensional problem to a two-dimensional one. The uniqueness of solution is guaranteed by imposing an additional condition, i. e., the closure condition at the trailing edge. To facilitate numerical evaluation of the definite integrals the wing surface is divided into a number of small rectangular panels. As a result, the singular integral equations are converted to a system of linear equations which can easily be solved by standard numerical techniques. An extension of the integral equation method to more general and versatile design procedure is described, and some of the design results for a transonic sweptback wing with an isobar pattern are also presented., 資料番号: NALSP0003033, レポート番号: NAL SP-3},
 title = {三次元遷音速積分方程式の数値解法とその応用},
 year = {1984}
}