抄録
Shock-wave boundary-layer interaction flow field near the sharp leading edge of a flat plate is investigated. Measurements of impact pressure distributions and Schlieren visualization are made under the flow conditions: M∞=10, 3<x<13 in a hypersonic gun tunnel. Preliminarily, a shape of a Pitot tube is improved to avoid unfavorable disturbance to flow field and to measure accurately for the short duration. The relationship between the measured impact pressure distributions and the structure of the flow field is discussed. The inviscid layer seems to be merged into the viscous layer at x= {-.7em}\
aisebox{1.1ex}{.} {.1em}\
aisebox{-0.2ex}{.} 10.
