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 surface

Info

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
Application number
GB11198/46A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to GB11198/46A priority Critical patent/GB610623A/en
Publication of GB610623A publication Critical patent/GB610623A/en
Expired legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C21/00Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/025Influencing 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
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C21/00Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/04Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2230/00Boundary layer controls
    • B64C2230/04Boundary layer controls by actively generating fluid flow
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/10Drag 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.
GB11198/46A 1946-04-11 1946-04-11 Improvements in and relating to the control of fluid flow along a solid boundary surface Expired GB610623A (en)

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)

* Cited by examiner, † Cited by third party
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

Cited By (2)

* Cited by examiner, † Cited by third party
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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