Engine nacelle for a supersonic aircraft

Details Engine nacelle for a supersonic aircraft Engine nacelle for a supersonic aircraft

B - Operations, Transporting

64

D

B64D 29/00 (2006.01) F02C 7/042 (2006.01)

Patent

CA 2507168

The nacelle (1) comprises, upstream in the air inlet direction (E), an air inlet structure (6) provided upstream with an inlet face (9) which exhibits an elliptical conical cross section, defined by the intersection of a conical shock wave (17) generated by a conical compression ramp (16) and of a first plane (10) which is inclined with respect to a second plane orthogonal to a longitudinal general direction of the nacelle (1) so that the free side (13) of the inlet face (9) is set back, in the air inlet direction (E), with respect to the opposite side (14) intended to face the aircraft.

- La nacelle (1) comporte, en amont dans le sens (E) d'entrée d'air, une structure d'entrée d'air (6) pourvue en amont d'une face d'entrée (9) qui présente une section conique elliptique, définie par l'intersection d'une onde de choc conique (17) engendrée par une rampe de compression conique (16) et d'un premier plan (10) qui est incliné par rapport à un second plan orthogonal à une direction générale longitudi- nale de la nacelle (1) de sorte que le côté libre (13) de la face d'entrée (9) est en retrait, dans le sens (E) d'entrée d'air, par rapport au côté opposé (14) destiné à venir en regard de l'avion.

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