Shockwave mitigation system for supersonic aircraft

1. A method of shock wave mitigation in supersonic vehicles, comprising:

generating an earthward propagating wing compression shockwave from a curved wing;

expelling a first supersonic exhaust plume having a first average velocity from an engine, the engine having an engine housing;

reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing using the engine;

expelling a bypass exhaust plume having a second average velocity adjacent to the first supersonic exhaust plume, the second average velocity being slower than the first average velocity; and

inhibiting coalescence of an engine exhaust plume compression shockwave extending from the first supersonic exhaust plume using the bypass exhaust plume;

wherein the step of reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing using the engine further comprises reflecting the wing compression shockwave off of the engine housing.

2. The method of claim 1 , further comprising moving the engine housing to meet the wing compression shockwave.

3. The method of claim 2 , wherein the step of moving the engine housing comprises translating the engine along the axis of freestream air flow about the engine.

4. The method of claim 1 , further comprising:

slidably moving the wing relative to a fuselage slidably coupled to the wing;

wherein the wing compression shockwave is moved relative to the engine to meet the engine housing.

5. A method of shock wave mitigation in supersonic vehicles, comprising:

generating an earthward propagating wing compression shockwave from a curved wing;

expelling a first supersonic exhaust plume having a first average velocity from an engine, the engine having an engine housing;

reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing using the engine;

expelling a bypass exhaust plume having a second average velocity adjacent to the first supersonic exhaust plume, the second average velocity being slower than the first average velocity; and

inhibiting coalescence of an engine exhaust plume compression shockwave extending from the first supersonic exhaust plume using the bypass exhaust plume

wherein the engine has a first nozzle expelling the first supersonic exhaust plume and a second nozzle expelling a bypass exhaust plume that has an average velocity that is slower than an average velocity of the first supersonic exhaust plume.

6. A method of shock wave mitigation in supersonic vehicles, comprising:

generating an earthward propagating wing compression shockwave from a curved wing;

expelling a first supersonic exhaust plume having a first average velocity from an engine, the engine having an engine housing;

moving the engine housing to meet the wing compression shockwave;

reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing using the engine housing;

expelling a bypass exhaust plume having a second average velocity adjacent to the first supersonic exhaust plume, the second average velocity being slower than the first average velocity; and

inhibiting coalescence of an engine exhaust plume compression shockwave extending from the first supersonic exhaust plume using the bypass exhaust plume.

7. A method of shock wave mitigation in supersonic vehicles, comprising:

generating an earthward propagating wing compression shockwave from a curved wing;

expelling a first supersonic exhaust plume having a first average velocity from an engine, the engine having an engine housing;

moving the engine housing to meet the wing compression shockwave by translating the engine along the axis of freestream air flow about the engine;

reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing using the engine housing;

expelling a bypass exhaust plume having a second average velocity adjacent to the first supersonic exhaust plume, the second average velocity being slower than the first average velocity; and

inhibiting coalescence of an engine exhaust plume compression shockwave extending from the first supersonic exhaust plume using the bypass exhaust plume.

8. A method of shock wave mitigation in supersonic vehicles, comprising:

generating an earthward propagating wing compression shockwave from a curved wing;

expelling a first supersonic exhaust plume having a first average velocity from an engine, the engine having an engine housing;

reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing using the engine housing;

slidably moving the wing relative to a fuselage slidably coupled to the wing, wherein the wing compression shockwave is moved relative to the engine to meet the engine housing;

expelling a bypass exhaust plume having a second average velocity adjacent to the first supersonic exhaust plume, the second average velocity being slower than the first average velocity; and

inhibiting coalescence of an engine exhaust plume compression shockwave extending from the first supersonic exhaust plume using the bypass exhaust plume.

9. A method of shock wave mitigation in supersonic vehicles, comprising:

generating an earthward propagating wing compression shockwave from a curved wing toward the first supersonic exhaust plume;

expelling a first supersonic exhaust plume having a first average velocity from an engine, the engine having an engine housing;

reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing using the engine;

expelling a bypass exhaust plume having a second average velocity adjacent to the first supersonic exhaust plume, the second average velocity being slower than the first average velocity; and

inhibiting coalescence of an engine exhaust plume compression shockwave extending from the first supersonic exhaust plume using the bypass exhaust plume

wherein the curved wing has an outboard portion shape selected from the group consisting of straight and upward curving;

wherein a high-pressure underwing to freestream low pressure interface channels a sound propagating vector at an inclination to the ground and parallel to the ground, respectively.