Aerodynamic Validation of Vortex Lattice Methods for Forward-Swept Wing Analysis

This paper investigates the aerodynamic accuracy of simulating forward-swept wing (FSW) configurations using the Vortex Lattice Method (VLM). The solver was calibrated against Grumman X-29 flight test data, yielding a post-processed span efficiency of e_corrected = 0.851 (within 2.53% of the NASA reference value). At cruise for a geometrically mirrored aft-swept baseline, this corresponds to an approximate 3.14% reduction in induced drag. Since induced drag comprises approximately 40% of total cruise drag, this yields a net total drag reduction of roughly 1.24%.