Water Tunnel Investigation of Forebody Characteristics at High Angles of Attack

Jouannet, Christopher; Munro, Cameron; Muller, S.; Krus, Petter

doi:10.2514/6.2003-3414

Cited by 3 publications

(4 citation statements)

References 11 publications

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“…Thus, the separation lines are always symmetric, and the leeward vortices are also symmetric because the vortex flow is mainly controlled by the fixed separation. The results obtained by previous researches [5,6,12,17] and present experiment all show that there is no obvious asymmetry in leeward vortex structure over chined fuselage, as shown in Figure 8(a). Therefore, the separation lines and leeward vortex flow would not change with the variation of nose tip perturbation.…”

Section: Influence Of Nose Tip Perturbation On Flow Behaviors Over Chsupporting

confidence: 71%

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Study on flow behavior and structure over chined fuselage at high angle of attack

Tian

Xueying

Wang

et al. 2010

Sci. China Technol. Sci.

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A study of leeward vortex structure over chined fuselage and the effects of micro tip perturbation on its vortex flow have been carried out in wind tunnel experiments at Reynolds numbers from 1.26×10 5 to 5.04×10 5 with PIV and pressure measurement techniques. Firstly, the experiment results have proved that micro tip perturbation has no effects on the vortex flow and its aerodynamic characteristics over chined fuselage at high angle of attack, in which there are not any non-deterministic flow behaviors. Secondly, the evolution of leeward vortex structure over chined fuselage along the axis of model can be divided into four flow regimes: linear conical developed regime, decay regime of leeward vortex intensity, asymmetric leeward vortex break down regime and completely break down regime. And a correlation between leeward vortex structure and sectional aerodynamic force was also revealed in the present paper. Thirdly, the experiment results show the behavior of leeward vortex core trajectories and zonal characteristics of leeward vortex structure with angles of attack. Finally, the experiment results of Reynolds number effect on the leeward vortex flow have further confirmed research conclusions from previous studies: the flows over chined fuselage at high angles of attack are insensitive to variation of Reynolds number, and there is a little effect on the secondary boundary layer separation and the suction peak induced by leeward vortex.high angle of attack aerodynamics, chined fuselage, tip perturbation, leeward vortex structure, zonal characteristics Citation:Tian W, Deng X Y, Wang Y K, et al. Study on flow behaviors and structure over chined fuselage at high angle of attack.

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Section: Influence Of Nose Tip Perturbation On Flow Behaviors Over Chsupporting

confidence: 71%

“…Therefore, it seems that the flow behaviors over chined fuselage are completely insensitive to Reynolds number. Based on this conclusion, Jouannet, Munro, and Muller [17] have investigated the flow structure and aerodynamic characteristic over chined fuselage through water tunnel tests in which the Reynolds number is very low.…”

Section: Introductionmentioning

confidence: 91%

Study on flow behavior and structure over chined fuselage at high angle of attack

Tian

Xueying

Wang

et al. 2010

Sci. China Technol. Sci.

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show abstract

“…This is especially so at high angles of attack where the vortex formed is stronger and hence less sensitive to viscous effects. For instance, the water tunnel studies of Jouannet et al 28 of chined forebodies show agreement with high Reynolds number wind tunnel data. In the case of smooth-shaped conical bodies, the transition and separation location on the body will invariably be influential and sensitive to Reynolds number.…”

Section: Introductionmentioning

confidence: 50%

“…Studies [25][26][27][28] have shown that at relatively high Reynolds numbers, vortex-dominated flow such as separated vortex flow on the leeward side of sharp-edged slender bodies is insensitive to Reynolds number effects. This is especially so at high angles of attack where the vortex formed is stronger and hence less sensitive to viscous effects.…”

Section: Introductionmentioning

confidence: 99%

A combined experimental and analytical investigation of the vortex stability over sharp-edged slender bodies

2007

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A combined experimental and analytical investigation is conducted to assess the stability of the symmetric vortex pair over three different sharp-edged slender bodies at high angles of attack. The analysis is based on a previously developed eigenvalue stability method. Corresponding experimental studies involving flow visualization in the water tunnel, force and pressure measurement in the wind tunnel are carried out. The angles of attack tested range from 15°to 40°. Overall, the experiments confirm the stability behaviors as determined from the analysis. The analytical solutions indicate that an absolute type of instability is the mechanism for the breakdown of symmetry of the vortex flow over slender conical bodies at high angles of attack. Both the experiments and the analysis reveal that a sharp-edged slender body with a smaller volume on the leeward side and a bigger volume on the windward side increases the overall stability of the symmetric vortex pair. A shape with extended sharp edges in the outboard direction on its sides further enhances the stability of the vortex pair. The analytical method can be a useful tool for exploring shapes that favor stability or instability.

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Influence of artificial tip perturbation on asymmetric vortices flow over a chined fuselage

Shi

Xueying

Tian

et al. 2015

Chinese Journal of Aeronautics

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Water Tunnel Investigation of Forebody Characteristics at High Angles of Attack

Cited by 3 publications

References 11 publications

Study on flow behavior and structure over chined fuselage at high angle of attack

Study on flow behavior and structure over chined fuselage at high angle of attack

A combined experimental and analytical investigation of the vortex stability over sharp-edged slender bodies

Influence of artificial tip perturbation on asymmetric vortices flow over a chined fuselage

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