GB714169A - A method of and device for producing a flow of compressible fluid - Google Patents

A method of and device for producing a flow of compressible fluid

Info

Publication number
GB714169A
GB714169A GB2349751A GB2349751A GB714169A GB 714169 A GB714169 A GB 714169A GB 2349751 A GB2349751 A GB 2349751A GB 2349751 A GB2349751 A GB 2349751A GB 714169 A GB714169 A GB 714169A
Authority
GB
United Kingdom
Prior art keywords
duct
slots
fluid
slotted
flow
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
GB2349751A
Inventor
Raymond Frederick Sargent
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.)
Bristol Aeroplane Co Ltd
Original Assignee
Bristol Aeroplane Co Ltd
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 Bristol Aeroplane Co Ltd filed Critical Bristol Aeroplane Co Ltd
Priority to GB2349751A priority Critical patent/GB714169A/en
Publication of GB714169A publication Critical patent/GB714169A/en
Expired legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels
    • G01M9/04—Details

Abstract

714,169. Wind tunnels. BRISTOL AEROPLANE CO., Ltd. Oct. 8, 1952 [Oct. 9, 1951], No. 23497/51. Class 4. A wind tunnel for producing flow at a Mach number greater than unity comprises a duct, the first part of which is connected to a source of fluid under pressure, and is convergent, and the second part is of substantially constant crosssection and is provided with longitudinal slots adapted to bleed off fluid to an ambient atmosphere of reduced static pressure relatively to that of the stream at entry to the duct. Fig. 3 shows an embodiment on the closed circulation system. The duct 6 conveys high pressure fluid from the compressor 5 to the convergent section 7 terminating in the slotted part 8. The slots are preferably provided uniformly, and their aggregate width amounts to only a small part of the total periphery. If a rectangular duct is used, the slots may be in two opposite sides only. The test object is placed at 17 on any convenient mounting. The slotted duct is supported by radial diaphragms 18, Figs. 3 and 4. The end of the duct 8 may be unslotted to enable the outflow to become uniform after bleeding. The gap between the ducts 8 and 15 is closed, as at 19, and by suitably selecting the size of the gap between them, pressure drop along the slots may be adjusted so that the bleeding is substantially uniform along the length of a slot. The duct may be slightly divergent, to the extent of 1 per cent of its internal diameter. An open circulation system is described, a draught shield being provided for the model, and in this, the slotted duct 8 is made rigid by arches interconnecting the sections between two slots, and one or more circular frames joined to these section externally. It is recommended that the slots should diverge outwards at an angle of not less than 60 degrees, and that the flow of bled fluid should be as free as possible.
GB2349751A 1951-10-09 1951-10-09 A method of and device for producing a flow of compressible fluid Expired GB714169A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2349751A GB714169A (en) 1951-10-09 1951-10-09 A method of and device for producing a flow of compressible fluid

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2349751A GB714169A (en) 1951-10-09 1951-10-09 A method of and device for producing a flow of compressible fluid

Publications (1)

Publication Number Publication Date
GB714169A true GB714169A (en) 1954-08-25

Family

ID=10196574

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2349751A Expired GB714169A (en) 1951-10-09 1951-10-09 A method of and device for producing a flow of compressible fluid

Country Status (1)

Country Link
GB (1) GB714169A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2975632A (en) * 1957-06-04 1961-03-21 North American Aviation Inc Ducted nozzle testing apparatus
US4308748A (en) * 1979-11-30 1982-01-05 Aro, Inc. Adaptive automatic wall wind tunnel
GB2142290A (en) * 1983-06-28 1985-01-16 Secr Defence Wind tunnels

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2975632A (en) * 1957-06-04 1961-03-21 North American Aviation Inc Ducted nozzle testing apparatus
US4308748A (en) * 1979-11-30 1982-01-05 Aro, Inc. Adaptive automatic wall wind tunnel
GB2142290A (en) * 1983-06-28 1985-01-16 Secr Defence Wind tunnels

Similar Documents

Publication Publication Date Title
SE414811B (en) TURBOFLEKTMOTOR
CH326300A (en) Axial flow turbine, in particular gas turbine
US2696110A (en) Variable-constriction nozzle
GB714169A (en) A method of and device for producing a flow of compressible fluid
GB697708A (en) Improvements in and relating to supersonic wind tunnels
Takehira et al. An experimental study of the annular diffusers in axial-flow compressors and turbines
GB1073470A (en) Fluid ducts
GB664055A (en) Improvements in apparatus for wind-tunnel testing of scale models of aerothermodynamic ducts
CH298592A (en) Blading on turbomachines with axial flow.
SU109542A1 (en) The method of blowing aircraft generators during their tests in a thermal pressure chamber in high-altitude flight conditions
US3035439A (en) Hypersonic wind tunnel test section
BLANGIER Performance tests of the adaptation of the C 4 wind tunnel to transonic flow. 1 st and 2 nd test campaigns
Goddard Supersonic tunnels
KUREN Design of an axisymmetric wind tunnel nozzle to produce continuous, uniform, parallel air flow of nominal mach 4 at 600 psia stagnation pressure and 4000 degrees stagnation temperature
SU290199A1 (en) Apparatus for testing air-feed jet engine under flignt coditions
MAEDER Progress Report 1 October-30 November 1952. Contract No. N7 ONR-35805 (Brown Univ.)
FR1070561A (en) High frequency, concentric and flexible piping with air insulation
SMELTZER et al. Investigation of a nearly isentropic mixed compression axisymmetric inlet system at Mach numbers 0. 6 to 3. 2(Wind tunnel tests of mixed-compression axisymmetric inlet system to determine bleed mass flow ratio, pressure recovery and pressure distortion)
AT178501B (en) Blading on turbomachines with axial flow
CA644808A (en) Gas turbine compressor driven air conditioning system
CA471995A (en) Guide vanes for axial-flow compressors and turbines
GB909284A (en) Improvements in or relating to the ventilation of tunnels
GREGOREK et al. Non-equilibrium effects in leading edge simulation(Leading edge pressure distributions measured on circular cylinders in normal cross flow, obtaining data from tests in arc-heated perfect gas and variable atmosphere wind tunnels)
PAULON Study of the coexistence of a supersonic jet and of a subsonic jet in a constant section duct(Supersonic and subsonic jets coexistence in rectilinear constant section duct, characterizing flow boundaries by pressure readings and Schlieren flow visualization)
LEYNAERT Problems of interaction between the air intake and the airframe