Hypersonic laminar flow control

Patent metadata

Field	Value
Publication number	US-10071798-B2
Application number	US-201314443992-A
Country	US
Kind code	B2
Filing date	Nov 19, 2013
Priority date	Nov 19, 2012
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

A novel passive control technique for laminar flow over air transportation vehicles and space reentry vehicles flying at high supersonic and hypersonic speeds is disclosed. The control of laminar flow can be achieved by applying an array of surface roughness elements in the region before the laminar-turbulent transition. For example, an array of two-dimensional rings, stripes, or closely packed three-dimensional isolated roughness elements may be used to stabilize the instability waves and delay transition. The roughness elements may have a height between 40% and 60% of the local boundary-layer thickness. The exact location, height, and spacing of surface roughness elements may be determined by a numerical simulation strategy based on the most unstable second mode, e.g. using known e N transition prediction method, experimental measurement, or any other suitable technique.

First claim

What is claimed is:

1. A supersonic vehicle, comprising:
an exterior surface section having a leading edge for receiving compressible fluid flow over the exterior surface; and
one or more surface roughness elements disposed on the exterior surface section to damp disturbances of the flow over the exterior surface;
wherein the one or more surface elements are disposed on the exterior surface no closer to the leading edge than a synchronization point of mode S and mode F of the flow over the exterior surface section.

2. A method of damping disturbances of flow over a supersonic vehicle, comprising:
determine for an exterior surface section having a leading edge a most unstable frequency of compressible fluid flow over the exterior surface;
determine a synchronization point of mode S and mode F of the flow over the exterior surface section from the leading edge; and
dispose one or more surface roughness elements on the exterior surface section no closer to the leading edge than the synchronization point of mode S and mode F.

3. The supersonic vehicle of claim 1 , wherein the one or more surface elements are disposed on the exterior surface upstream of laminar-turbulent transition of the flow over the exterior surface section from the leading edge.

4. The supersonic vehicle of claim 3 , wherein the one or more surface roughness elements comprises a height from the exterior surface section of between 40% and 60% of a local boundary-layer thickness of the flow over the exterior surface section.

5. The supersonic vehicle of claim 1 , wherein the one or more surface roughness elements are spaced along the exterior surface section in a direction of the flow between ten and twenty times a height from the exterior surface of the one or more surface roughness elements.

6. The supersonic vehicle of claim 1 , wherein the one or more surface roughness elements comprise two-dimensional elements each formed by a cross-sectional area swept along a line substantially perpendicular to a direction of the flow along the exterior surface section.

7. The supersonic vehicle of claim 6 , wherein the exterior surface section comprises a two dimensionally bounded area and the two-dimensional elements comprise stripes having ends at edges of the two dimensionally bounded area.

8. The supersonic vehicle of claim 6 , wherein the exterior surface section comprises a three dimensional surface and the two-dimensional elements comprise rings such that each cross sectional area is swept along the line that closes on itself.

9. The supersonic vehicle of claim 1 , wherein the one or more surface roughness elements comprise three-dimensional elements each formed by surface bumps spaced along a line substantially perpendicular to a direction of the flow along the exterior surface section.

10. The supersonic vehicle of claim 9 , wherein the exterior surface section comprises a two dimensionally bounded area and each line of surface bumps ends at edges of the two dimensionally bounded area.

11. The supersonic vehicle of claim 9 , wherein the exterior surface section comprises a three dimensional surface and each line of surface bumps are disposed along the line that closes on itself.

12. The method of claim 2 , wherein the one or more surface elements are disposed on the exterior surface upstream of laminar-turbulent transition of the flow over the exterior surface section from the leading edge.

13. The method of claim 12 , wherein the one or more surface roughness elements comprises a height from the exterior surface section of between 40% and 60% of a local boundary-layer thickness of the flow over the exterior surface section.

14. The method of claim 2 , wherein the one or more surface roughness elements are spaced along the exterior surface section in a direction of the flow between ten and twenty times a height from the exterior surface of the one or more surface roughness elements.

15. The method of claim 2 , wherein the one or more surface roughness elements comprise two-dimensional elements each formed by a cross-sectional area swept along a line substantially perpendicular to a direction of the flow along the exterior surface section.

16. The method of claim 15 , wherein the exterior surface section comprises a two dimensionally bounded area and the two-dimensional elements comprise stripes having ends at edges of the two dimensionally bounded area.

17. The method of claim 15 , wherein the exterior surface section comprises a three dimensional surface and the two-dimensional elements comprise rings such that each cross sectional area is swept along the line that closes on itself.

18. The method of claim 2 , wherein the one or more surface roughness elements comprise three-dimensional elements each formed by surface bumps spaced along a line substantially perpendicular to a direction of the flow along the exterior surface section.

19. The method of claim 18 , wherein the exterior surface section comprises a two dimensionally bounded area and each line of surface bumps ends at edges of the two dimensionally bounded area.

20. The method of claim 18 , wherein the exterior surface section comprises a three dimensional surface and each line of surface bumps are disposed along the line that closes on itself.

Assignees

• Univ California

Inventors

• Zhong Xiaolin
• Fong Kahei Danny
• Wang Xiaowen

Classifications

• F15D1/08

  of jets leaving an orifice · CPC title

• B64C2230/26

  by using rib lets or hydrophobic surfaces · CPC title

• B64C30/00 Primary

  Supersonic type aircraft · CPC title

• Y02T50/166

  Cross-Sectional Technologies · mapped topic

• B64C21/10 Primary

  using other surface properties, e.g. roughness · CPC title