Extended Nonlinear Lifting-Line Method for Aerodynamic Modeling of Reconfigurable Aircraft

Cl = section lift coefficient c = local chord length D = fading-memory constant G = nondimensional circulation l = section lift force/length m = number of points used in sine series expansion of circulation function N = consecutive iterations convergence parameter r = perpendicular distance from vortex tol = iteration relative tolerance of conversion U1 = freestream velocity magnitude w = downwash velocity y0 = wing semispan, y coordinate of wingtip = wind incidence angle, wing angle of attack eff = effective angle of attack 2D = 2-D vortex-induced wind incidence angle 3D = 3-D wake-induced wind incidence angle = circulation magnitude = nondimensional spanwise coordinate = local wing twist angle = local wing sweep angle = nondimensional chordwise coordinate = air density = trigonometric spanwise coordinate

[1]  Ephrahim Garcia,et al.  Evaluation of bio-inspired morphing concepts with regard to aircraft dynamics and performance , 2004, SPIE Smart Structures and Materials + Nondestructive Evaluation and Health Monitoring.

[2]  Daniela Tordella,et al.  The Lifting Line Equation for a Curved Wing in Oscillatory Motion , 1997 .

[3]  D. Owens.  Weissinger's model of the nonlinear lifting-line method for aircraft design , 1998 .

[4]  Armando R. Rodriguez.  Morphing Aircraft Technology Survey , 2007 .

[5]  E. S. Levinsky,et al.  Nonlinear Lifting Line Theory for Predicting Stalling Instabilities on Wings of Moderate Aspect Ratio , 1976 .

[6]  John Flanagan,et al.  Development and Flight Testing of a Morphing Aircraft, the NextGen MFX-1 , 2007 .

[7]  J. Weissinger,et al.  The Lift Distribution of Swept-Back Wings , 1947 .

[8]  Dan M. Somers,et al.  A computer program for the design and analysis of low-speed airfoils, supplement , 1980 .

[9]  C. P. van Dam,et al.  Experimental investigation on the effect of crescent planform on lift and drag , 1991 .

[10]  D. Snyder,et al.  Modern Adaptation of Prandtl's Classic Lifting-Line Theory , 2000 .

[11]  W. Gander,et al.  Adaptive Quadrature—Revisited , 2000 .

[12]  J. Anderson,et al.  Numerical lifting line theory applied to drooped leading-edge wings below and above stall , 1980 .

[13]  Daniela Tordella,et al.  On an extension of Prandti's lifting line theory to curved wings , 1991, IMPACT Comput. Sci. Eng..

[14]  James C. Sivells,et al.  Method for calculating wing characteristics by lifting-line theory using nonlinear section lift data , 1947 .

[15]  Ephrahim Garcia,et al.  Aerodynamic Modeling of Morphing Wings Using an Extended Lifting-Line Analysis , 2007 .

[16]  Ephrahim Garcia,et al.  Optimization of Perching Maneuvers Through Vehicle Morphing , 2008 .

[17]  William A. Crossley,et al.  Comparison of Morphing Wing Strategies Based Upon Aircraft Performance Impacts , 2004 .

[18]  Terrence A. Weisshaar,et al.  Evaluating the Impact of Morphing Technologies on Aircraft Performance , 2002 .

[19]  C. W. Harper,et al.  Theoretical symmetric span loading at subsonic speeds for wings having arbitrary plan form , 1948 .