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  5. Investigation of influence of the deviation of the trailing edge of supercritical wing airfoil on its aerodynamic characteristics

Investigation of influence of the deviation of the trailing edge of supercritical wing airfoil on its aerodynamic characteristics

I.А. Kaleniuk
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The influence of deviation of the trailing edge of supercritical wing airfoil McDonnell/Douglas DSMA-523 in the range of Mach numbers 0,48  M  0,95 and angles of attack –10    10 , with Reynolds numbers Re  106 has been investigated. It is shown that the deviation of the trailing edge of airfoil up can increase the critical Mach number. The deviation of the trailing edge of the airfoil down allows one to increase an aerodynamic efficiency. Practical recommendations for the use deviation of the trailing edge of the airfoil on existing aircrafts have been given.
Keywords: supercritical airfoil, Mach number, angle of attack, lift coefficient, drag coefficient, trailing edge
Reference:
Kaleniuk, Y.A. (2011), "Yssledovanye vlyianyia otklonenyia zadnei kromky krыlovoho profylia na eho aэrodynamycheskye kharakterystyky" , Scientific Works of Kharkiv National Air Force University, Vol. 3(29), pp. 49-51.