Boundary Interference at Subsonic Speeds in Wind Tunnels With Ventilated Walls

Pindzola, M. S.; Lo, C. F.

doi:10.21236/ad0687440

Cited by 39 publications

(5 citation statements)

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“…In this connection, the solution for a subsonic compressible vortex between porous walls is given in Ref. 7. Although the doublet-vortex assumption is plausible, it is not made in the approach herein.…”

Section: Tunnel Far Fieldsmentioning

confidence: 99%

Transonic flow calculations over two-dimensional canard-wing systems

Shankar

Malmuth

Cole

1981

Journal of Aircraft

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As a prototype for the three-dimensional interaction problem, the transonic interference flowfields over twodimensional canard-wing systems are computed using transonic small disturbance theory. In the calculation, the two airfoils comprising the lifting "biplane" system are placed in separate computational planes with an overlapped region across which information from one airfoil to the other is transferred at the end of each relaxation cycle. Results showing the favorable interference in overall lift are presented and compared with linear theory calculations. Far field expressions for solid, slotted, and free jet wind tunnel wall cases that correspond to the canard-wing arrangement are also described.

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Section: Tunnel Far Fieldsmentioning

confidence: 99%

Transonic flow calculations over two-dimensional canard-wing systems

Shankar

Malmuth

Cole

1981

Journal of Aircraft

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“…These methods were early achievements of Prandtl's vortex theory of wings, and they served well for decades (Millikan 1932, Lotz 1935, Silverstein & White 1936. More recent work is summarized by Garner et al (1966) and by Pindzola & Lo (1969).…”

Section: Introductionmentioning

confidence: 99%

Adaptive Wind Tunnels

Sears¹,

Erickson²

1988

Annu. Rev. Fluid Mech.

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“…Accounts of these are given in Garner et al (1966), Pindzola & Lo (1979) and Mokry, Chan & Jones (1 983).…”

Section: Introductionmentioning

confidence: 99%

An asymptotic theory of wind-tunnel-wall interference on subsonic slender bodies

Malmuth

1987

J. Fluid Mech.

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An asymptotic theory of solid cylindrical wind-tunnel-wall interference about subsonic slender bodies has been developed. The basic approximation used is one of large wall-radius to body-length ratio. Matched asymptotic expansions show that in contrast to the analogous two-dimensional problem of a confined airfoil, three regions exist. Besides the incompressible crossflow and nearly axisymmetric zones, a wall layer exists where reflection in the wall of the line source representing the body becomes of dominant importance. From the theory, the interference pressures are shown to be approximately constant for closed bodies. Also demonstrated is that D'Alembert's paradox holds for interference drag of such shapes. Numerical studies comparing the exact theory to the asymptotic model which provides drastic simplifications, show that the latter can be used with reasonable accuracy to describe flows, even where the characteristic tunnel-radius to body-length ratio is as low as 1.5.

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Boundary Interference at Subsonic Speeds in Wind Tunnels With Ventilated Walls

Cited by 39 publications

References 0 publications

Transonic flow calculations over two-dimensional canard-wing systems

Transonic flow calculations over two-dimensional canard-wing systems

Adaptive Wind Tunnels

An asymptotic theory of wind-tunnel-wall interference on subsonic slender bodies

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