| 摘要 |
<p>1. An aircraft wing, having very critical profiling and comprizing on the top side, in a specific area of the profile chord, a device for influencing the compression shock, characterized in that the said device takes the form of a ventilating device (12) fir equalizing the differential pressure between the supersonic and the subsonic fields, that the said ventilating device (12) is comprized of a perforated wall strip (13), which extends along the direction of the wing span, having an equalizing chamber (14) underneath it, and that the width of the perforated wall strip (13), measured in the direction of the wing chord, has a value between 5 and 20 % of the local wing chord.</p> |
