Symmetrical transonic flow with breakaway around cylindro-conical bodies

Bachmanova, N. S.; Kirnasov, B. S.; Kudryavtsev, V. V.; Lipnitskii, Yu. M.

doi:10.1007/bf01023284

Cited by 2 publications

(2 citation statements)

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“…9). With further increase in M ∞ the nature of the flow in the separated free separation zone also changes and subsequently it disappears [20]. This stage of flow variation is as yet poorly understood.…”

Section: Transonic Flow Restructuring With Increase In the Mach Numbementioning

confidence: 99%

“…The pressure difference and the pressure gradient on the body in the region of shock location increase and, at a certain moment, become sufficient for separation of the reattached turbulent boundary layer (curve 9 in Fig. 8 for M ∞ = 0.92); thus, a small free separation zone is formed [6,9,20]. In fact, in this case the pressure difference in the region from the point at which the terminating shock effect starts to manifest itself (∆x/D = 0.6) to the pressure peak behind this shock is in agreement with the critical pressure difference required for turbulent boundary layer separation calculated, for example, from the formula (p 2 /p 1 21]; here, M s and Re x are the flow parameters at the beginning of the influence zone.…”

Section: Transonic Flow Restructuring With Decrease In M ∞mentioning

confidence: 99%

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Distinctive features of the transonic flow past a cone-cylinder body at large angles of the bend in the body generator at the leading corner edge

Dan’kov¹,

Kosenko²,

Куликов³

et al. 2006

Fluid Dyn

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The results of an experimental investigation of the flow past cone-cylinder bodies with small angles of the bend in the body generator at the leading corner edge (θ s ≤ 20 • ) and the available data on the flow past cone-cylinder and segment-cylinder bodies with large angles of the bend in the generator (θ s, c ≥ 30 • ) are generalized. On the basis of these data, the distinctive features of the transonic flow past these bodies and, primarily, the flow restructuring downstream of the leading corner edge at θ s ≥ 30 • are established and the characteristic gasdynamic parameters are determined. Emphasis is placed on the critical stage of flow restructuring, the nature of the stationary aerodynamic hysteresis, and the effect of the Reynolds number and wave disturbances.

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Section: Transonic Flow Restructuring With Increase In the Mach Numbementioning

confidence: 99%

Section: Transonic Flow Restructuring With Decrease In M ∞mentioning

confidence: 99%