Modeling supersonic inlet boundary layer bleed roughness

Paynter, Gerald C.; Treiber, David A.; Kneeling, W.

doi:10.2514/6.1992-269

Cited by 7 publications

(2 citation statements)

References 5 publications

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“…4 A summary of roughness and turbulence model adjustments to account for bleed can be found in Paynter, et al 5 who further developed the roughness modeling approach in a distributed bleed patch. This was followed by the works of Slater and Saunders 6 and Slater 7 who developed and extended (respectively) a velocity boundary condition to incorporate bleed effects.…”

Section: B Previous Workmentioning

confidence: 99%

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Oorebeek

Babinsky

Ugolotti

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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A series of experiments have been conducted on an array of bleed holes spanning the width of the CUED supersonic wind tunnel at Mach numbers of 1.8 and 2.5. The wind tunnel was run with varying levels of suction, and the resulting flow structure over the bleed array was subsequently mapped with a Laser Doppler Velocimetry (LDV) system at a resolution of 0.25 hole diameters or better. The same wind tunnel setup was also simulated using the OVERFLOW Navier-Stokes equation solver. Overall good agreement was found in the definition of the expansion fan and barrier shock pattern produced by flow entering the normal holes, with the production of streamwise vorticity noted in both CFD and experimental studies. The proposed mechanism of vorticity generation is an effect of the barrier shock standing off from the rear edge of each bleed hole, and is predicted by CFD to increase in strength as Mach number increases, as well as when the vorticity is produced by a single hole, rather than an array. Both studies found that vorticity decreases as suction strength is reduced, however the experimental study showed the vortices persist farther downstream than predicted by CFD.

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Section: B Previous Workmentioning

confidence: 99%

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Oorebeek

Babinsky

Ugolotti

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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“…Planform geometry is the top-view shape of a wing and effective on wing aerodynamic performance [9] [10]. Therefore, the geometrical parameters of a wing planform geometry are also important for a wing design.…”

Section: Planform Geometry and Aerodynamic Parameters Of An Aircraft Wingmentioning

confidence: 99%

Effects of Taper Ratio on Aircraft Wing Aerodynamic Parameters: A Comperative Study

Güzelbey¹,

Eraslan²,

Doğru³

2019

European Mechanical Science

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Wing design is one of the most important tasks for a designer to overcome during an aircraft design process. Therefore, a designer need to optimize so many wing geometrical parameters with the aim of obtaining an efficient wing geometry complying with requirements of the design. Taper ratio is one of these parameters, which is the ratio of root and tip chord lengths of a wing. In this study, firstly, a high aspect ratio rectangular aircraft wing was numerically investigated in terms of some aerodynamic parameters including induced drag coefficient, Oswald efficiency factor and lift coefficient together with its span-wise distribution by means of XFLR5 computational fluid dynamics program. The assessment of mesh accuracy of the program was done at the beginning of the analyses. Later on, with the aim of observing the effects of taper ratio on aircraft wing aerodynamic parameters, the revised versions of the wing, which have the taper ratios from 0.2 to 1.2 (with the increment of 0.2) were analyzed. In conclusion, depending on the analyses results, the wings having different taper ratios were compared in terms of obtained aerodynamic parameters and span-wise lift distributions. Moreover, tip vortices of each wing, together with their sizes, were obtained and also compared.

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