@techreport{oai:jaxa.repo.nii.ac.jp:00043494,
 author = {高木, 正平 and サリック, ウイリアム and Takagi, Shohei and Saric, W. S.},
 month = {Sep},
 note = {The three-dimensional boundary-layer experiments were conducted on a 45 degrees swept wing in the ASU unsteady Wind Tunnel. Crossflow-dominated transition was produced on a very smooth surface with contoured end liners to simulate infinite swept-wing flow. The model surface was carefully polished and buffed up to plus or minus 3 mum to minimize roughness effects on transition. Fixed-wavelength vortices, traveling wave and inflectional breakdown were subsequently observed prior to turbulent state as before, but the transition location moved further 10%-20% downstream of the chordlength. In order to control traveling wave and inflectional breakdown, two kinds of acoustic sounds, which tune up the traveling wave and breakdown, respectively, were introduced visualizing the surface flow via two-or three-dimensional roughness elements. No acoustic effect was observed in visualization., 資料番号: NALSP0015020, レポート番号: NAL SP-15},
 title = {後退翼に沿う三次元境界層遷移について},
 year = {1991}
}