Jet engine nacelle for a supersonic aircraft

1. A power plant for an aircraft having a structure establishing a maximum Mach number at which the aircraft is capable of flying, said power plant comprising:

at least a jet engine;

a jet engine nacelle comprising, upstream in the air inlet direction, an air inlet structure provided upstream with an inlet face; and

a conical compression ramp which is mounted coaxially with respect to the nacelle, at the level of the inlet face of the air inlet structure, wherein:

said inlet face of the air inlet structure includes an elliptical conical cross section defined by the intersection of (i) a conical shock wave generated by the conical compression ramp for a particular Mach number that is greater than said maximum Mach number at which the aircraft is capable of flying and (ii) a first plane which is inclined with respect to a second plane orthogonal to a longitudinal general direction of the nacelle,

said first plane is inclined with respect to said second plane by an angle of inclination which is such that the maximum width of the inlet face corresponds to the width of the nacelle at the level of a central part of the nacelle intended to receive a fan,

the free side of said inlet face is set back, in the air inlet direction, with respect to the opposite side intended to face the aircraft, and

the inlet face of the air inlet structure having said shape of the elliptical conical cross section causes an actual shock wave generated by the conical compression ramp during flight to not be ingested by the jet engine at any Mach number at which the aircraft is capable of flying.

2. The power plant of claim 1 , wherein said first plane is inclined with respect to said second plane by an angle of inclination which lies between 50° and 30 °.

3. The power plant of claim 2 , wherein said angle of inclination is substantially equal to 20.6°.

4. The power plant of claim 1 , wherein said air inlet structure has a shape going from said elliptical conical cross section to a U-shaped cross section which is defined on the basis of an arc of a circle, whose radius depends on the length of the radius of the fan of the jet engine which will be mounted in said nacelle.

5. A supersonic aircraft, which comprises at least one power plant of the type of that specified under claim 1 .

6. A method for designing a power plant for an aircraft having a structure defining a maximum Mach number at which the aircraft is capable of flying, the method comprising:

designing a jet engine nacelle having an air inlet structure with an air inlet face;

designing a conical compression ramp that is coaxial with respect to the nacelle at the level of the inlet face;

designing the inlet face to have an elliptical conical cross section that is defined by the intersection of (i) a conical shock wave generated by the conical compression ramp at a Mach number that is greater than the maximum Mach number at which the aircraft is capable of flying and (ii) a first plane which is inclined with respect to a second plane, which is orthogonal to a longitudinal general direction of the nacelle, wherein:

said first plane is inclined with respect to said second plane by an angle of inclination which is such that the maximum width of the inlet face corresponds to the width of the nacelle at the level of a central part of the nacelle intended to receive a fan,

the free side of the inlet face is set back, in the air inlet direction, with respect to the opposite side that faces the aircraft, and

the inlet face of the air inlet structure having said shape of the elliptical conical cross section causes an actual shock wave generated by the conical compression ramp during flight to not be ingested by the jet engine at any Mach number at which the aircraft is capable of flying.

7. The method of claim 6 , wherein the first plane is inclined with respect to the second plane by an angle of inclination which lies between 5° and 30°.

8. The method of claim 7 , wherein the angle of inclination is substantially equal to 20.6°.

9. The method of claim 6 further comprising designing the air inlet structure with a shape going from an said elliptical conical cross section to a U-shaped cross section defined on the basis of an arc of a circle whose radius depends on the length of the radius of the fan.