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An Iterative Decambering Approach for Post-Stall Prediction of Wing Characteristics using known Section Data
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An iterative decambering approach for the post stall prediction of wings using known section data as inputs is presented in this article, which can currently be used for incompressible.ow and can be extended to compressible subsonic.ow using Mach number correction schemes.Abstract:
An iterative decambering approach for the post stall prediction of wings using known section data as inputs is presented. The method can currently be used for incompressible .ow and can be extended to compressible subsonic .ow using Mach number correction schemes. A detailed discussion of past work on this topic is presented first. Next, an overview of the decambering approach is presented and is illustrated by applying the approach to the prediction of the two-dimensional C(sub l) and C(sub m) curves for an airfoil. The implementation of the approach for iterative decambering of wing sections is then discussed. A novel feature of the current e.ort is the use of a multidimensional Newton iteration for taking into consideration the coupling between the di.erent sections of the wing. The approach lends itself to implementation in a variety of finite-wing analysis methods such as lifting-line theory, discrete-vortex Weissinger's method, and vortex lattice codes. Results are presented for a rectangular wing for a from 0 to 25 deg. The results are compared for both increasing and decreasing directions of a, and they show that a hysteresis loop can be predicted for post-stall angles of attack.read more
Citations
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Journal ArticleDOI
Nonlinear-Aerodynamics/Nonlinear-Structure Interaction Methodology for a High-Altitude Long-Endurance Wing
TL;DR: In this article, a nonlinear time-domain aeroelastic methodology has been integrated via tightly coupling a geometrically exact nonlinear intrinsic beam model and the generalized unsteady vortex-lattice aerodynamic model with vortex roll-up and free wake.
Journal ArticleDOI
Poststall prediction of multiple-lifting-surface configurations using a decambering approach
TL;DR: In this article, a novel scheme is presented for an iterative decambering approach to predict the post-stall characteristics of wings using known section data as inputs, which differs from earlier ones in the details of how the residual is computed.
Journal ArticleDOI
Nonlinear Generalized Lifting-Line Coupling Algorithms for Pre/Poststall Flows
S. Gallay,Eric Laurendeau +1 more
TL;DR: In this paper, a thorough analysis on the circulation-based and angle-of-attack-based correction methods (Γ and α) highlights their respective numerical poststall characteristics, and a strongly coupled algorithm is presented, allowing to bypass the interpolation phase via the use of Legendre polynomials.
Journal ArticleDOI
Preliminary-Design Aerodynamic Model for Complex Configurations Using Lifting-Line Coupling Algorithm
S. Gallay,Eric Laurendeau +1 more
TL;DR: In this paper, a nonlinear lifting-line-theory algorithm for the prediction of aerodynamic coefficients and lifting-surface-pressure distribution for multiple aircraft configurations is presented, which is applied to isolated wing, high-lift systems (slat/main/flap), and multisurface configurations.
Proceedings ArticleDOI
Design Optimization of a Variable-Span Morphing Wing for a Small UAV
TL;DR: An in-house aerodynamic shape optimization code is used to solve a drag minimization problem to determine the optimal values of wing span for the whole vehicle’s flight speed envelope while subject to geometric constraints.
References
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DissertationDOI
Unsymmetrical lift distributions on a stalled monoplane wing
TL;DR: In this article, it is shown that it is possible to have an unsymmetrical lift distribution at the stall if a certain shape is assumed for the curve of section lift coefficient vs. effective angle of attack.
Journal ArticleDOI
Effect of Airfoil Characteristics on Aircraft Performance
TL;DR: In this article, a two-pronged approach is presented to tailor an airfoil for an aircraft: 1) an approach in which aircraft performance simulations are used to study the effects of aerodynamic changes, and 2) an analytical approach to determine expressions that provide guidance in sizing and locating the low-drag range.
Proceedings ArticleDOI
Aerodynamic Modeling for Global Stability Analysis
TL;DR: A nonlinear lifting-line method is used to generate compact aerodynamic models of complete aircraft configurations of moderate fidelity that can be used for fundamental studies of aircraft stability and control.
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