Natural Rolling Responses of a Delta Wing in Transonic and Subsonic Flows

The unsteady, three-dimensional, full Navier-Stokes (NS) equations and the Euler equations of rigid-body dynamics are sequentially solved to simulate the natural rolling response of slender delta wings of zero thickness at moderate to high angles of attack, to transonic and subsonic flows. The governing equations of fluid flow and dynamics of the present multi-disciplinary problem are solved using the time-accurate solution of the NS equations with the implicit, upwind, Roe flux-difference splitting, finite-volume scheme and a four-stage Runge-Kutta scheme, respectively. The main focus is to analyze the effect of Mach number and angle of attack on the leading edge vortices and their breakdown, the resultant rolling motion, and overall aerodynamic response of the wing. Three cases demonstrate the natural response of a 65 deg swept, cropped delta wing in a transonic flow with breakdown of the leading edge vortices and an 80 deg swept delta wing in a subsonic flow undergoing either damped or self-excited limit-cycle rolling oscillations as a function of angle of attack. Comparisons with an experimental investigation completes this study, validating the analysis and illustrating the complex details afforded by computational investigations

Flapping and Flexible Wing Aerodynamics of Low Reynolds Number Flight Vehicles

Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76905/1/AIAA-2006-503-331.pd

Aeromechanics of membrane and rigid wings in and out of ground-effect at moderate Reynolds numbers

Wind tunnel experiments are conducted using membrane wings and rigid flat-plates in ground-effect at a moderate Reynolds number of Re = 56 000 with ground clearances from 1% to 200% chord length measured from their trailing-edge. A six-axis load-cell captures time-resolved forces and moment while time-resolved stereo digital image correlation (DIC) measurements are performed to capture membrane motions. The lift and drag coefficients of the rigid wing in ground-effect follow well-established trends while the membrane wing appears to exhibit improved coefficients and efficiency (compared to the rigid wing) when in ground-effect. Proper orthogonal decomposition (POD) is applied to study the spatiotemporal structure of membrane vibrations. With increasing angles-of-attack and/or decreasing heights above ground, mode shapes of membrane deformation are dominated by large-scale fluctuations that have a smaller number of local extrema along the chord. Ground-effect induces modifications to the membrane deformation, which appear to be similar to the modifications induced by increasing angles-of-attack in free-flight. At high angles-of-attack in free-flight or at moderate angles in ground-effect, two POD modes of membrane fluctuations are found to be sufficient to capture 90% of all membrane deformations. Under these conditions, a membrane deformation with maximum camber near the trailing edge of the membrane wing is found to correlate with high lift, low drag and a nose down pitching moment. The extrema in membrane deformations and lift and drag forces occur simultaneously, while there is a time-lag between the deformation and the pitching moment

FEDSM2006-98559 HIGH-ORDER COMPUTATIONAL TECHNIQUES FOR UNSTEADY VORTICAL FLOWS OVER DELTA WINGS

ABSTRACT Introduction Delta-like wings are a common design feature of many aircraft including currently proposed unmanned combat air vehicles, micro air vehicles and high-performance fighter aircraft. The complex flows over these types of aircraft when maneuvering involve massive separation and place numerous demands on a computational method. The flowfields are inherently unsteady and three-dimensional. Because of the abrupt nature of the onset of vortex breakdown and the extreme sensitivity of performance coefficients (e.g., pitching moment coefficient, rolling moment coefficient) to the proper representation and location of breakdown, a high degree of accuracy is required to satisfactorily compute these challenging unsteady flowfields. In order to effectively predict these types of highly nonlinear flows a computational approach that solves the unsteady, threedimensional Navier-Stokes equations using a well-validated and robust high-order solve