Transition Prediction in Low Reynolds Airfoil Flows Using Finite Element/Difference Solvers Coupled with the e^n Method: a Comparative Study

Mamou, Mahmoud; Yuan, Weixing; Khalid, M.; Wokoeck, Ralf; Radespiel, Rolf

doi:10.2514/6.2006-3176

Cited by 2 publications

(2 citation statements)

References 14 publications

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“…Practically, even if no general transition theory exists, as of yet, there are a number of methods that can be used to numerically determine the transition position with very good accuracy (48)(49)(50)(51) .…”

Section: Second Derivative Analysis Of the Pressure Data For Transitimentioning

confidence: 99%

Numerical and experimental validation of a morphed wing geometry using Price-Païdoussis wind-tunnel testing

2016

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An experimental validation of an optimised wing geometry in the Price-Païdoussis subsonic wind tunnel is presented. Two wing models were manufactured using optimised glass fibre composite and tested at three speeds and various angle-of-attack. These wing models were constructed based on the original aerofoil shape of the ATR 42 aircraft and an optimised version of the same aerofoil for a flight condition of Mach number equal to 0.1 and angle-of-attack of 0°. The aerofoil's optimisation was realised using an ‘in-house’ genetic algorithm coupled with a cubic spline reconstruction routine, and was analysed using XFoil aerodynamic solver. The optimisation was concentrated on improving the laminar flow on the upper surface of the wing, between 10% and 70% of the chord. XFoil-predicted pressure distributions were compared with experimental data obtained in the wind tunnel. The transition position was estimated from the experimental pressure data using a second derivative methodology and was compared with the transition predicted by XFoil code. The results have shown the agreement between numerical and experimental data. The wind-tunnel tests have shown that the improvement of the laminar flow of the optimised wing is higher than the value predicted numerically.

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Section: Second Derivative Analysis Of the Pressure Data For Transitimentioning

confidence: 99%

Numerical and experimental validation of a morphed wing geometry using Price-Païdoussis wind-tunnel testing

2016

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“…Once large enough, higher frequencies occur and the shear layer disintegrates into structures of different size [11]. For a detailed study of transition prediction using numerical computational methods and simulations of the laminar separation bubble in low Reynolds number flows, please refer to the paper of Mamou et al [12].…”

Section: Theoretical Considerationsmentioning

confidence: 99%

Transition Point Detection from the Surface Pressure Distribution for Controller Design

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Labib

2008

Journal of Aircraft

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Transition Prediction in Low Reynolds Airfoil Flows Using Finite Element/Difference Solvers Coupled with the e^n Method: a Comparative Study

Cited by 2 publications

References 14 publications

Numerical and experimental validation of a morphed wing geometry using Price-Païdoussis wind-tunnel testing

Numerical and experimental validation of a morphed wing geometry using Price-Païdoussis wind-tunnel testing

Transition Point Detection from the Surface Pressure Distribution for Controller Design

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