The development of a self-streamlining flexible walled transonic test section

Goodyer, M. J.; Wolf, Stephen

doi:10.2514/6.1980-440

Cited by 6 publications

(6 citation statements)

References 3 publications

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“…10. The Reynolds number of the experiments reported here was only 0-3xl0 6 , based on wing chord, so it is probable that the separation was laminar.…”

Section: 4mentioning

confidence: 68%

“…Calculations by Srinivasan and his colleagues are in qualitative agreement with Spivey's* 11 -' 2 ) data. They also report computations of the flow for a half body of revolution tip on a Naca 0015 profile wing of rectangular planform and AR = 5, but at a = 11-8° and Re = 2xl0 6 . However, they do not give any pressure distributions for the tip cap itself.…”

Section: 4mentioning

confidence: 99%

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A new approach to adaptive-wall windtunnel testing

Fakas

Bernstein

1994

Aeronaut. j.

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Summary A technique is described whereby experiments may be conducted on models which are geometrically similar to only part of the full scale configuration with the windtunnel walls being contoured to simulate the flow over that part. In this way, higher spatial resolutions can be achieved in a windtunnel of moderate size. The method is demonstrated by studying the effects of tip geometry on the flow over a wing of aspect ratio 15 using a half wing model of chord 500 mm projecting 1031 mm into a test section of width 1200 mm.

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“…10. The Reynolds number of the experiments reported here was only 0-3xl0 6 , based on wing chord, so it is probable that the separation was laminar.…”

Section: 4mentioning

confidence: 68%

Section: 4mentioning

confidence: 99%

A new approach to adaptive-wall windtunnel testing

Fakas

Bernstein

1994

Aeronaut. j.

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“…The same seems to be true of the procedures used at Southampton (Goodyer & Wolf 1982). There the shock waves extended to the wall and, again, were not properly accounted for in the outer-fl ow computation.…”

Section: Tunnels With Deformable Impermeable Wallsmentioning

confidence: 91%

Adaptive Wind Tunnels

Sears¹,

Erickson²

1988

Annu. Rev. Fluid Mech.

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“…14 for the plain-wing configuration. For both configurations, wall pressure coefficient far downstream is given by the expression, derived in Appendix B C Px --(CD -CDV)S/C (9) where CDV is vortex drag coefficient. This coefficient is determined in a way suggested by Maskell (2) and is discussed in more detail below.…”

Section: Combat-aircraft Half-modelmentioning

confidence: 99%

Calculation of tunnel wall interference from wall-pressure measurements

Ashill¹,

Keating²

1988

Aeronaut. j.

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Summary A method is described for calculating wall interference in solid-wall wind tunnels from measurements of static pressures at the walls. Since it does not require a simulation of the model flow, the technique is particularly suited to determining wall interference for complex flows such as those over VSTOL aircraft, helicopters and bluff shapes (e.g. cars and trucks). An experimental evaluation shows that the method gives wall-induced velocities which are in good agreement with those of existing methods in cases where these techniques are valid, and illustrates its effectiveness for inclined jets which are not readily modelled.

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The development of a self-streamlining flexible walled transonic test section

Cited by 6 publications

References 3 publications

A new approach to adaptive-wall windtunnel testing

A new approach to adaptive-wall windtunnel testing

Adaptive Wind Tunnels

Calculation of tunnel wall interference from wall-pressure measurements

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