Numerical lifting line theory applied to drooped leading-edge wings below and above stall

Anderson, J. D.; Corda, Stephen

doi:10.2514/3.44690

Cited by 96 publications

(62 citation statements)

References 8 publications

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“…Moreover, a more rigorous and more rapidly converging method using Fourier series expansion was developed by Rasmussen and Smith [12]. Meanwhile, McCormick [13] proposed a purely numerical method to solve the liftingline equation for a single-lifting surface with a straight lifting line, and Anderson and Corda [14] improved the numerical method by relaxing the linear assumption of the relationship between section lift and section angle of attack. However, all the aforementioned methods, to obtain the solution to the classical lifting-line equation, only applied for the particular configuration with a single-lifting surface with no sweep and no dihedral.…”

Section: Introductionmentioning

confidence: 99%

Prediction of Lift Coefficient for Tandem Wing Configuration or Multiple-Lifting-Surface System Using Prandtl’s Lifting-Line Theory

Cheng

Wang

2018

International Journal of Aerospace Engineering

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In tandem airfoil configuration or multiple-lifting-surface layouts, due to the flow interaction among their lifting surfaces, the aerodynamic characteristics can be affected by each other. In accordance with Prandtl's classical lifting-line theory, a method to calculate the section lift coefficient for the tandem wing configuration or multiple-lifting-surface system is presented. In that method, the form of Fourier sine series is used to express the variation of the section circulation which changes continuously along the wingspan. The accuracy of the numerical solutions obtained by the method has been validated by the data obtained from computational fluid dynamics and tunnel experiment. By varying the design parameters, such as the gap, the stagger, the incidence angle, the wingspan, the taper ratio as well as the aspect ratio, a series of tandem wing configurations are tested to analyze the lift coefficient and the induced drag of each lifting surface. From the results, it can be seen that the bigger negative gap and stagger can produce better lift characteristic for tandem wing configuration. Besides, it will also be beneficial for the lift characteristic when the incidence angle and the wingspan of fore wing are appropriately declined or if the incidence angle and the wingspan of hind wing are appropriately increased.

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Section: Introductionmentioning

confidence: 99%

Prediction of Lift Coefficient for Tandem Wing Configuration or Multiple-Lifting-Surface System Using Prandtl’s Lifting-Line Theory

Cheng

Wang

2018

International Journal of Aerospace Engineering

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“…6,10 The wing prototypes are described in Table 1. Wing twist and aerodynamic computations were performed using spanwise n station intervals of 0.01 m. 20 Computation of wing aerodynamics Baseline wings. For the baseline straight wings, an elliptical distribution of G y ð Þ was computed using a numerical iterative method based on Prandtl's Lifting-line Theory, 2,20 according to the following four stages.…”

Section: Wing Twistmentioning

confidence: 99%

Design of the Grand Touring sports car wing: geometric and aerodynamic twist

Marques-Bruna

2012

Proceedings of the Institution of Mechanical Engineers, Part P:

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Wing twist gives the Grand Touring sports car an eye-catching 'aerodynamic shape'. From the functional viewpoint, wing twist may improve downforce, provide stall control and enhance aerodynamic efficiency if the twist is optimised. This study aims, first, to explore the influence of linear geometric and aerodynamic twist upon spanwise upwash velocity, downforce and induced drag distributions and, second, to evaluate the use of optimum twist in achieving minimum induced drag while preserving high downforce, in wings with linear taper for the Grand Touring car. Baseline wing prototypes were designed and fitted, subsequently, with a Gurney flap and endplates to obtain complete wings. Aerodynamics for straight wings and wings with geometric, aerodynamic and optimised twist were computed using modified versions of the Prandtl's Lifting-line Theory. Straight and geometrically-twisted wings with constituent NACA 65 1 -412 airfoils present superior aerodynamic efficiency at angles of attack 4 1°and may be used as stabilisers on high-speed circuits. Geometric twisting elicits a partial, rather than complete, wing stall that contributes to safety in motor racing. A geometrically-twisted wing constructed with a NASA LS(1)-0413 airfoil yields high downforce at the expense of large induced drag via a double-peaked induced drag distribution, and it is suitable for high-downforce racing circuits. Nonetheless, the analysis suggests that a twist-optimised wing for the Grand Touring car very nearly duplicates the ideal aerodynamic performance of an elliptic wing and yields high downforce and minimum possible induced drag. The findings support the implementation of optimum wing twist at the conceptual stages of Grand Touring sports car design.

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“…For this objective we have developed a decambering approach for multiple lifting surfaces that uses known two-dimensional airfoil characteristics as input. Earlier approaches for prediction of wing aerodynamics using nonlinear airfoil lift curves can be broadly classified into two kinds: (a) iterative Γ-distribution approaches [1][2][3][4][5][6][7][8] and (b) α-reduction approaches.…”

Section: Introductionmentioning

confidence: 99%

“…4) and has since been discussed by several researchers. [3][4][5][6][7][8]15 However, the approach in scheme 2 is novel because this scheme is believed to be the first one in which the possibility of multiple solutions for high angles of attack is brought to light right during the iteration process. Earlier approaches including scheme 1 were able to identify the existence of multiple solutions only as a result of obtaining multiple final converged solutions with different initial conditions for the iteration procedure.…”

Section: 10mentioning

confidence: 99%

Post-Stall Aerodynamic Modeling and Gain-Scheduled Control Design

Gopalarathnam

Kim

2005

AIAA Guidance, Navigation, and Control Conference and Exhibit

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A multidisciplinary research effort that combines aerodynamic modeling and gain-scheduled control design for aircraft flight at post-stall conditions is described. The aerodynamic modeling uses a decambering approach for rapid prediction of post-stall aerodynamic characteristics of multiple-wing configurations using known section data. The approach is successful in bringing to light multiple solutions at post-stall angles of attack right during the iteration process. The predictions agree fairly well with experimental results from wind tunnel tests. The control research was focused on actuator saturation and flight transition between low and high angles of attack regions for near-and post-stall aircraft using advanced LPV control techniques. The new control approaches maintain adequate control capability to handle high angle of attack aircraft control with stability and performance guarantee.

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Numerical lifting line theory applied to drooped leading-edge wings below and above stall

Cited by 96 publications

References 8 publications

Prediction of Lift Coefficient for Tandem Wing Configuration or Multiple-Lifting-Surface System Using Prandtl’s Lifting-Line Theory

Prediction of Lift Coefficient for Tandem Wing Configuration or Multiple-Lifting-Surface System Using Prandtl’s Lifting-Line Theory

Design of the Grand Touring sports car wing: geometric and aerodynamic twist

Post-Stall Aerodynamic Modeling and Gain-Scheduled Control Design

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