@techreport{oai:jaxa.repo.nii.ac.jp:00044772,
 author = {鈴木, 弘一 and 竹内, 理 and SUZUKI, Koichi and TAKEUCHI, Osamu},
 month = {Dec},
 note = {Geometrical imperfection in a Wind-Tunnel model sometimes leads to erroneous test results. This report describes experimental results in a transonic flow of 2-dimensional pressure distribution over three wing models of the same configuration with slight profile errors. The tests were performed at Mach numbers of 0.5～0.85 and attack angles of 0 deg～4 deg. It was found that in the subcritical regime, pressure distribution was not markedly influenced by the small error in profile shape. However, at a design Mach number of about 0.75 a strong affect was noted and accuracy became crucial especially near the leading edge. The effects of pressure distribution changes due to model shape errors were observed on several aerodynamic parameters such as lift-curve slope, drag coefficient, and drag-divergence Mach number. Changes in these parameters due to model shape error were also shown. Actual model configurations were accurately measured, and the data used in numerical estimation of pressure distribution for prescribed shapes. The result clearly indicated the trend of the experimental results., 資料番号: NALTR0518000, レポート番号: NAL TR-518},
 title = {風胴膜型の精度と試験結果について},
 year = {1977}
}