NUMERICAL INVESTIGATION OF THE INFLUENCE OF THE CONFIGURATION PARAMETERS OF A SUPERSONIC PASSENGER AIRCRAFT ON THE INTENSITY OF SONIC BOOM

Results of calculations of the sonic boom produced by a supersonic passenger aircraft in a cruising regime of fl ight at the Mach number M = 2.03 are presented. Consideration is given to the infl uence of the lateral dihedral of the wings and the angle of their setting, and also of different locations of the aircraft engine nacelles on the wing. An analysis of parametric calculations has shown that the intensities of sonic boom generated by a confi guration with a dihedral rear wing and by a confi guration with set wings remain constant, in practice, and correspond to the intensity level created by the optimum confi guration. Comparative assessments of sonic boom for tandem confi gurations with different locations of the engine nacelles on the wing surface have shown that the intensity of sonic boom generated by the confi guration with an engine nacelle on the windward side can be reduced by ~14% compared to the confi guration without engine nacelles. In the case of the confi guration with engine nacelles on the leeward size of the wing, the profi le of the sonic-boom wave degenerates into an N-wave, in which the intensity of the bow shock is signifi cantly reduced.
   
Author:  V. F. Volkov and I. I. Mazhul′
Keywords:  supersonic fl ow, sonic boom, monoplane, tandem confi guration, dihedral of the wing, engine nacelles
Page:  161