The effect of wing plan form on the downwash behind wings is investigated. The theoretical downwash angles are computed and compared with experimental results. The results show that both experimentally and theoretically there is a decrease in downwash with an increase in sweep, but the downwash derivative behind swept-back wing increases with increase of angle of attack under effect of leading edge separation.

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Some experiments made in high speed wind-tunnels, at the 1st Technical Laboratory of Navy, during the War, are descrihed.
To investigate the relation between the scale effect and compressibility effect, drag tests and pressure distribution tests were made on sphere, cylinder and others. We obtained the results that the increase of Mach number corresponds qualitatively to the decrease of Reynolds number. Also for the maximum lift, we found the same pheno- mena, by the tests of thick and thin wings.
The characteristics of wing-profiles at high speed were compared. Tested wings were 4-digit and 5-digit series of NACA, laminar flow profiles of Japan, and others. On the good profiles at low speed as NACA 23012, the effect of compressibility is great, but on the laminar flow profiles, the effect is small, though the scale effect is great on such profiles in the range of tested Reynolds number.
The relation between the development of shock waves and performance of wingprofiles was also investigated by the Schlieren method.

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