| 摘要 |
<p>The invention concerns aviation technology and can be used in the production of power units for light and ultra-light aircraft as a puller or pusher propeller, irrespective of its direction of rotation. The invention in question facilitates, inter alia, stabilization of the speed of the propeller during take-off and landing, allows the range of rotational speeds to be maintained within 3-5 % and allows the thrust of the propeller to be maximized during take-off. The propeller comprises a hub (1) and blades (2). The blades (2) incorporate a twist and their configuration depends on the profiles (3) at ten representative sections (4). The angles (ζ°) of the profiles can be adjusted. The representative sections (4) are set at intervals along the blade span (r^¨B7 = 0.15 RB; 0.25 RB; 0.35 RB and so forth). The configuration of each blade is determined by the distribution of width along its span and by the interval h. The family of profiles (3) between the third representative section (4) (r^¨B7 = 0.35 RB) and the ninth (r^¨B7 = 0.95 RB) is ascertained from a table on the basis of the relationship between actual and maximum width.</p> |
