Numerical Analysis of Effects of Leading-Edge Protuberances on Aircraft Wing Performance

Malipeddi, Anil Kumar; Mahmoudnejad, Niloufar; Hoffmann, Klaus A.

doi:10.2514/1.c031670

Cited by 50 publications

(44 citation statements)

References 10 publications

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“…Subsequent numerical simulations also confirmed the finding through higher-fidelity numerical methods [16,17,18,19,20]. These were accompanied by experiments on both full-and semi-span rectangular planforms in either wind [21,8,22] or water tunnels [23].…”

Section: Introductionsupporting

confidence: 62%

Effects of leading-edge tubercles on wing flutter speeds

Ng¹,

New²,

Palacios³

2016

Bioinspir. Biomim.

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Abstract. The dynamic aeroelastic effects on wings modified with bio-inspired leading-edge (LE) tubercles are examined in this study. We adopt a state-space aeroelastic model via the coupling of unsteady vortex-lattice method and a composite beam to evaluate stability margins as a result of LE tubercles on a generic wing.The unsteady aerodynamics and spanwise mass variations due to LE tubercles have counteracting effects on stability margins with the former having dominant influence.When coupled, flutter speed is observed to be 5% higher, and this is accompanied by close to 6% decrease in reduced frequencies as an indication of lower structural stiffness requirements for wings with LE tubercles. Both tubercle amplitude and wavelength have similar influences over the change in flutter speeds, and such modifications to the leading-edge would have minimal effect on stability margins when concentrated inboard of the wing. Lastly, when used in sweptback wings, LE tubercles are observed to have smaller impacts on stability margins as the sweep angle is increased.

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Section: Introductionsupporting

confidence: 62%

Effects of leading-edge tubercles on wing flutter speeds

Ng¹,

New²,

Palacios³

2016

Bioinspir. Biomim.

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“…CFD simulations were performed using ANSYS Fluent 17.0, which has been extensively used in various studies [17][18][19][20][21]. The 3D Reynolds-averaged Navier-Stokes (RANS) equations for the mean flow quantities were solved.…”

Section: Boundary Condition and Simulation Setupmentioning

confidence: 99%

Numerical Investigation of Effect of Parameters on Hovering Efficiency of an Annular Lift Fan Aircraft

Jiang

Zhang

2016

Aerospace

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Abstract:The effects of various parameters on the hovering performance of an annular lift fan aircraft are investigated by using numerical scheme. The pitch angle, thickness, aspect ratio (chord length), number of blades, and radius of duct inlet lip are explored to optimize the figure of merit. The annular lift fan is also compared with a conventional circular lift fan of the same features with the same disc loading and similar geometry. The simulation results show that the pitch angle of 27 • , the thickness of 4% chord length, the aspect ratio of 3.5~4.0, 32 blades, and the radius of inlet lip of 4.7% generate the maximum figure of merit of 0.733. The optimized configuration can be used for further studies of the annular lift fan aircraft.

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“…CFD simulations were performed using ANSYS Fluent 17.0 (ANSYS, Inc., Canonsburg, PA, USA), which has been extensively used in various studies [9][10][11][12][13]. Steady and unsteady Reynolds-averaged Navier-Stokes (RANS) equations for the mean flow quantities were solved.…”

Section: Boundary Condition and Simulation Setupmentioning

confidence: 99%

Numerical Study of Transition of an Annular Lift Fan Aircraft

Jiang

Zhang

2016

Aerospace

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The present study aimed at studying the transition of annular lift fan aircraft through computational fluid dynamics (CFD) simulations. The oscillations of lift and drag, the optimization for the figure of merit, and the characteristics of drag, yawing, rolling and pitching moments in transition are studied. The results show that a two-stage upper and lower fan lift system can generate oscillations of lift and drag in transition, while a single-stage inner and outer fan lift system can eliminate the oscillations. The characteristics of momentum drag of the single-stage fans in transition are similar to that of the two-stage fans, but with the peak of drag lowered from 0.63 to 0.4 of the aircraft weight. The strategy to start transition from a negative angle of attack −21 • further reduces the peak of drag to 0.29 of the weight. The strategy also reduces the peak of pitching torque, which needs upward extra thrusts of 0.39 of the weight to eliminate. The peak of rolling moment in transition needs differential upward thrusts of 0.04 of the weight to eliminate. The requirements for extra thrusts in transition lead to a total thrust-weight ratio of 0.7, which makes the aircraft more efficient for high speed cruise flight (higher than 0.7 Ma).

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Numerical Analysis of Effects of Leading-Edge Protuberances on Aircraft Wing Performance

Cited by 50 publications

References 10 publications

Effects of leading-edge tubercles on wing flutter speeds

Effects of leading-edge tubercles on wing flutter speeds

Numerical Investigation of Effect of Parameters on Hovering Efficiency of an Annular Lift Fan Aircraft

Numerical Study of Transition of an Annular Lift Fan Aircraft

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