Shockwave mitigation system for supersonic aircraft
A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.
1. A method of shockwave 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;
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.
2. The method of claim 1 , 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.
3. The method of claim 2 , further comprising moving the engine housing to meet the wing compression shockwave.
4. The method of claim 3 , wherein the step of moving the engine housing comprises translating the engine along the axis of freestream air flow about the engine.
5. The method of claim 2 , 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.
6. The method of claim 1 , wherein the step of reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing further comprises:
reflecting the wing compression shockwave off of the first supersonic exhaust plume.
7. The method of claim 6 wherein reflecting the wing compression shockwave off of the first supersonic exhaust plume establishes an upward propagating reflected compression shockwave.
8. The method of claim 1 , wherein the step of reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing further comprises: reflecting the wing compression shockwave off of the engine.
9. The method of claim 1 , wherein the second average velocity is approximately the same velocity as a freestream velocity about the wing.
10. The method of claim 9 , wherein the bypass exhaust plume is expelled from the engine.
11. The method of claim 10 , wherein the bypass exhaust plume comprises air sourced from an air source selected from the group consisting of (i) bleed air taps from a compressor in the engine, (ii) bleed air taps at inlet shock ramps disposed at a front of the engine.
12. The method of claim 1 , wherein the engine has a first nozzle expelling the first supersonic exhaust plume and a second nozzle expelling the bypass exhaust plume that has an average velocity that is slower than an average velocity of the first supersonic exhaust plume.
13. The method of claim 1 , wherein the wing has a bottom surface shape configured to direct the compression shockwave toward the engine.
14. The method of claim 1 , wherein the step of generating an earthward propagating wing compression shockwave from the curved wing comprises propagating a majority of the compression shockwave toward a rear portion of the engine housing.
15. The method of claim 1 , wherein the step of generating a earthward propagating wing compression shockwave from the curved wing comprises propagating substantially all of the wing compression shockwave toward the engine housing.
16. The method of claim 1 , wherein the step of generating a downward propagating wing compression shockwave from the curved wing towards the earth comprises propagating substantially all of the compression shockwave toward the first supersonic exhaust plume.
17. The method of claim 16 , 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 for the straight outboard portion shape and parallel to the ground for the upward curving outboard portion shape.
18. The method of 1 , wherein the engine is selected from the group consisting of a jet engine, turbojet engine, ramjet engine, scramjet engine, high bypass turbojet, variable cycle engine, and adaptive-cycle engine.
19. The method of claim 1 , wherein reflecting a majority of the earthward propagating wing compression shockwave back towards the curved wing comprises reflecting less than the entire earthward propagating wing compression shockwave back towards the curved wing.
20. A method of shock wave mitigation in supersonic vehicles, comprising:
generating an earthward propagating wing compression wave region from a curved wing;
expelling a first supersonic exhaust plume having a first average velocity from an engine, the engine having an engine housing;
translating the engine to expel the first supersonic exhaust plume immediately upstream from the earthward propagating wing compression wave region;
wherein the earthward propagating wing compression wave region is inhibited from coalescing into a compression shockwave by the first supersonic exhaust plume.
21. The method of claim 20 , further comprising:
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 fust average velocity; and
inhibiting coalescence of an engine exhaust plume compression shockwave extending from the first supersonic exhaust plume using the bypass exhaust plume.