GB610623A - Improvements in and relating to the control of fluid flow along a solid boundary surface - Google Patents
Improvements in and relating to the control of fluid flow along a solid boundary surfaceInfo
- Publication number
- GB610623A GB610623A GB11198/46A GB1119846A GB610623A GB 610623 A GB610623 A GB 610623A GB 11198/46 A GB11198/46 A GB 11198/46A GB 1119846 A GB1119846 A GB 1119846A GB 610623 A GB610623 A GB 610623A
- Authority
- GB
- United Kingdom
- Prior art keywords
- slot
- boundary layer
- velocity
- downstream
- slots
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 239000012530 fluid Substances 0.000 title abstract 4
- 239000007787 solid Substances 0.000 title abstract 2
- 238000011144 upstream manufacturing Methods 0.000 abstract 3
- 230000007423 decrease Effects 0.000 abstract 1
- 230000003247 decreasing effect Effects 0.000 abstract 1
- 238000002347 injection Methods 0.000 abstract 1
- 239000007924 injection Substances 0.000 abstract 1
- 238000000926 separation method Methods 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/025—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for simultaneous blowing and sucking
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/04—Boundary layer controls by actively generating fluid flow
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
610,623. Boundary layer control. GOLDSTEIN, S., RICHARDS, E. J., and PRESTON, J. H. April 11, 1946, No. 11198. [Class 4] A solid surface intended to serve as the boundary of a fluid stream is provided with a transversely-extending slot facing downstream through which fluid may be injected downstream into the boundary layer tangentially of the surface, which is so shaped that the calculated potential flow velocity decreases abruptly in the downstream direction at a position substantially coincident with the slot and not upstream of it, the upstream velocity gradients being such as not to provoke boundary layer separation, means being provided for injecting fluid through the slot into the boundary layer at a velocity not less than that of the outside edge of the boundary layer immediately upstream of the slot. Fig. 4 shows a thick unsymmetrical aerofoil, the section of which is shaped to produce a discontinuity in the velocity distribution over the upper surface at a point 69.1 per cent of the chord from the leading edge, where a spanwise slot S is provided connected to a pump P for injecting air into the boundary layer. The symmetrical aerofoil section shown in Fig. 6 is shaped to produce velocity discontinuities at points on the upper and lower surfaces distant 80 per cent of the chord from the leading edge. Slots S1, S2, in communication with a pump P are located at these points, the upper one S1 being a suction slot and the lower one S2 a discharge slot through which air drawn through the upper slot is injected into the boundary layer on the lower surface. This arrangement may be modified by providing a discharge slot on both the upper and lower surfaces, the air being supplied to the slots through a single branched duct or two separate ducts. Fig. 8 shows the application of the invention to a symmetrical expansion duct with decreasing velocity in the downstream direction, e.g. for a compressor diffuser, in which downstream-facing injection slots S2 are provided in the portions of the wall W where the velocity q changes abruptly. Specification 578,763 is referred to.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB11198/46A GB610623A (en) | 1946-04-11 | 1946-04-11 | Improvements in and relating to the control of fluid flow along a solid boundary surface |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB11198/46A GB610623A (en) | 1946-04-11 | 1946-04-11 | Improvements in and relating to the control of fluid flow along a solid boundary surface |
Publications (1)
Publication Number | Publication Date |
---|---|
GB610623A true GB610623A (en) | 1948-10-19 |
Family
ID=9981820
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB11198/46A Expired GB610623A (en) | 1946-04-11 | 1946-04-11 | Improvements in and relating to the control of fluid flow along a solid boundary surface |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB610623A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2894703A (en) * | 1954-05-27 | 1959-07-14 | Research Corp | Boundary layer control system |
US2915136A (en) * | 1956-05-28 | 1959-12-01 | Friedrich O Ringleb | Apparatus for suppressing noise |
-
1946
- 1946-04-11 GB GB11198/46A patent/GB610623A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2894703A (en) * | 1954-05-27 | 1959-07-14 | Research Corp | Boundary layer control system |
US2915136A (en) * | 1956-05-28 | 1959-12-01 | Friedrich O Ringleb | Apparatus for suppressing noise |
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