| 摘要 |
<p>631,785. Aircraft wings. VICKERS-ARMSTRONGS, Ltd., and RICHARDS, E. J. Nov. 25, 1947, No. 31222. [Class 4] In order to delay the formation of compressibility shock waves to the same extent over the whole span of a wing, the angle of sweep back of the quarter chord line is made greater over the inboard region than at the wing tip. The leading edge may be formed with two or more straight portions A1, A2, Fig. 1, having different angles of sweep back or by a smooth continuous curve C, Fig. 3. The trailing edge B may be straight as shown in Fig. 1, or similar to the leading edge, Figs. 2 and 4 (not shown).</p> |
