System and method for fluid manipulation
By manipulating the fluid flow in the proximity of an object such as a fuselage, a wing, or the hull of ship, the wave drag associated with this object can be substantially reduced. This can be accomplished by locally changing both the fluid flow velocity and the pressure of the fluid flow.
1. A system for reducing wave drag, the system comprising:
a first fluid manipulation apparatus (“FMA”) configured to manipulate an interior fluid flow within a steamtube during a normal operating condition, and configured to change the speed and pressure of the interior fluid flow in a streamwise direction;
a second FMA configured to manipulate the interior fluid flow downstream of the first FMA, and configured to change the speed and pressure of the interior fluid flow in a streamwise direction;
a pressure containment apparatus (“PCA”) configured to act on the interior fluid flow downstream of at least a portion of the first FMA and upstream of at least a portion of the second FMA, and confugured to maintain a pressure difference between of the interior fluid flow and a free stream; and
a third FMA configured to manipulate the interior fluid flow downstream of at least a portion the first FMA and upstream of a least a portion of the second FMA, and configured to deliver a net linear momentum into the far wake of the third FMA within the streamtube during the nominal operating condition, wherein the net linear momentum has a non-zero component perpendicular to the free stream flow velocity,
wherein the free stream flow speed is greater than a wave speed within the free stream during the nominal operating condition, and wherein the fluid is compressible,
the system being configured to manipulate the interior fluid flow to reduce the wave drag of the third FMA.
2. The system of claim 1 , wherein the first FMA, and/or PCA, and/or second FMA comprises a intentional momentum carrying apparatus (“IMCA”), a converging duct, a converging diverging duct, or a diverging duct.
3. The system of claim 1 , wherein the first FMA, and/or PCA, and/or second FMA comprises an IMSA, a propeller, a rotor, a body force generating apparatus, or a thrust generating apparatus.
4. The system of claim 1 , wherein the fluid is a gas.
5. The system of claim 1 , wherein the first FMA is configured to decelerate the interior fluid flow and increase the pressure relative to the local free stream flow of the first FMA.
6. The system of claim 5 , wherein the first FMA is configured to decelerate the interior fluid flow relative to the local free stream flow of the first FMA to a subsonic fluid flow speed.
7. The system of claim 5 , wherein the first FMA is configured to decelerate the interior fluid flow relative to the local free stream flow of the first FMA to a transonic fluid flow speed.
8. The system of claim 5 , wherein the first FMA is configured to decelerate the interior fluid flow relative to the local free stream flow of the first FMA to a lower supersonic fluid flow speed.
9. The system of claim 1 , wherein the second FMA is configured to accelerate the interior fluid flow and decrease the pressure relative to the local free stream flow of the second FMA.
10. The system of claim 9 , wherein the second FMA is configured to accelerate the interior fluid flow relative to the local free stream flow of the second FMA to a speed equal to the free stream fluid flow speed.
11. The system of claim 9 , wherein the second FMA is configured to accelerate the interior fluid flow relative to the local free stream flow of the second FMA to a speed greater than the free stream fluid flow speed.
12. The system of claim 9 , wherein the second FMA is configured to accelerate the interior fluid flow relative to the local free stream flow of the second FMA to a speed less than the free stream fluid flow speed.
13. The system of claim 1 , wherein the PCA is configured to maintain a pressure difference between the interior fluid flow within the streamtube and an exterior fluid flow exterior to the streamtube.
14. The system of claim 1 , wherein the first FMA, PCA, or second FMA comprises a channel, wherein the streamtube passes through at least a portion of the channel, wherein the channel has a circular, rectangular, elliptical, or polygonal cross-section, and/or wherein the channel has a straight section, a bend, an elbow joints, or a turn.
15. The system of claim 1 , wherein the third FMA comprises a wing configured to generate a net lift force with a non-zero component perpendicular to a local free stream flow velocity vector of the wind and to transfer a net linear momentum into the fluid during the nominal operating condition.
16. The system of claim 1 , wherein the first FMA, PCA, second FMA, and/or third FMA comprises a fuselage.
17. The system of claim 1 , wherein the interior fluid flow is manipulated downstream of at least a portion of the first FMA and upstream of a least a portion of the second FMA by an intentional momentum carrying apparatus, a fuselage, a hull of a ship, and intentional momentum shedding apparatus, a turboshaft engine, a turbofan engine, a turboprop engine, a turbojet engine, a ramjet, a thrust apparatus, a drag apparatus, a pump jet, a propeller, a compressor, a combustion chamber, a turbine, or an afterburner.
18. The system of claim 1 , wherein the first FMA, PCA, and/or second FMA comprise an intentional momentum carrying apparatus (“IMCA”),
wherein a local free stream flow speed of the FMA is reduced by the IMCA relative to the free stream flow speed, and
wherein the IMCA comprises an outer surface and an inner surface.
19. The system of claim 18 , wherein the volume between the outer surface and the inner surface comprises at least part of a vehicle, wherein the outer and inner surfaces are configured to reduce the effect of wave drag of the vehicle in a free stream flow.
20. A system of claim 18 , wherein the outer surface is substantially parallel to a local free stream flow velocity vector of the IMCA during the nominal operating condition.
21. A system of claim 18 , wherein the IMCA comprises an annular cylinder, wherein the first FMA is located at an upstream end of the cylinder, and the second FMA located at a downstream end of the cylinder.
22. The system of claim 18 , wherein the outer surface is in the shape of a tapered cylinder, wherein the radius of the cylinder decreases in the downstream direction.
23. The system of claim 18 , wherein the cross-sectional geometry of the outer surface is circular, elliptical, rectangular, or polygonal when viewed in a direction aligned with the free stream flow.
24. The system of claim 18 , wherein the local free stream flow speed of the third FMA is reduced relative to the free stream flow speed by the action of the first FMA, PCA, and/or second FMA during the nominal operating condition.
25. The system of claim 18 , wherein the IMCA comprises a fuselage.
26. The system of claim 18 , wherein the third FMA comprises a wing.
27. The system of claim 18 , wherein the third FMA is located within the streamtube enclosed by the leading and trailing edges of the IMCA.
28. The system of claim 1 , wherein the third FMA is configured to deliver a net induced velocity into a far wake of the third FMA during the nominal operating condition, wherein at least a portion of the far wake of the third FMA is located within the interior fluid flow downstream of at least a portion of the first FMA and upstream of at least a portion of the second FMA, and wherein the induced velocity delivered by the third FMA into the far wake of the third FMA has a non-zero net component perpendicular to the local free stream flow in the far wake.
29. The system of claim 28 , wherein the induced velocity delivered by the third FMA into the far wake of the third FMA has a non-zero net component parallel to the local free stream flow in the far wake.
30. The system of claim 28 , wherein the third FMA comprises a wing configured to generate a net lift force with a non-zero component perpendicular to a local free stream flow velocity vector of the wing and to transfer a net linear momentum into the fluid during the nominal operating condition, and wherein at least a portion of the far wake of the wing is located within the interior fluid flow downstream of at least a portion the first FMA and upstream of at least a portion of the second FMA, and wherein the far wake of the wing extends into the free stream downstream of the second FMA.
31. The system of claim 30 , wherein the IMCA comprises a channel, wherein the streamtube passes through at least a portion of the channel, wherein the wingspan is less than half the effective diameter of the channel at the location of the wing.
32. The system of claim 30 , wherein the IMCA comprises a channel, wherein the streamtube passes through at least a portion of the channel, wherein the wingspan is less than one third and/or less than one quarter the effective diameter of the channel at the location of the wing.
33. The system of claim 30 , wherein the IMCA comprises a channel, wherein the streamtube passes through at least a portion of the channel, wherein the wingspan is less than one tenth the effective diameter of the channel at the location of the wing.
34. The part system of claim 1 , wherein the third FMA comprises a propeller or a rotor, a control surface, an intentional momentum carrying apparatus (“IMCA”), or an intentional momentum shedding apparatus (“IMSA”).
35. The system of claim 1 , wherein the first FMA, second FMA, and/or the PCA are configured to reduce the local free stream speed of the third FMA relative to the free stream flow speed.
36. The system of claim 35 , wherein the local free stream flow speed of the third FMA is reduced to a flow speed smaller than a wave speed within the local free stream flow of the third FMA.
37. The system of claim 35 , wherein the local free stream flow speed of the third FMA is reduced to a flow speed larger than a wave speed within the local free stream flow of the third FMA.
38. The system of claim 1 , wherein the nominal operating condition comprises steady nominal level cruise.
39. The system of claim 1 , wherein there is a net force in the downstream direction on at least a portion of the interior fluid flow during the nominal operating condition.
40. The system of claim 39 , wherein the net force is delivered via an IMSA, a turboshaft engine, a turbofan engine, a turboprop engine, a turbojet engine, a ramjet, a thrust apparatus, a pump jet, a propeller, an afterburner, a compressor, the combustion of fuel in a combustion chamber, or an electric motor driving an IMSA.
41. The system of claim 1 , wherein the first FMA, PCA, and/or second FMA comprises an outside surface having a leading edge and a trailing edge, wherein the cross-sectional area of the outside surface decreases in the downstream direction between the leading edge and the trailing edge.
42. The system of claim 1 , wherein the system comprises a duct apparatus, wherein the duct apparatus comprises the first FMA, and/or the second FMA, and/or the PCA.
43. The system of claim 1 , wherein the system comprises a channel, wherein the streamtube passes through at least a portion of the channel.
44. The system of claim 43 , wherein the first FMA, the PCA, or the second FMA are configured to vary the cross-sectional area of the channel.
45. The system of claim 44 , wherein the first FMA, the PCA, or the second FMA comprise a ramp or translating spike.