Non Linear Induced Drag Study of Generically Cambered Closely Coupled Dual Wings
A non-linear thin vortex lattice method, BSAERO, with wake rollup has been used to analyze closely coupled generic dual wings. These induced drag studies involved using generic mean camber line wings created using two parabolas. Using this parabola method the location of maximum camber and the magnitude of the maximum camber were varied independently of one another. CL/CDi was used as the success parameter for a particular wing system configuration. The best dual wing geometry configuration had a CL/CDi 18% greater than the comparable dual baseline with symmetric wings. The worst dual wing configuration had a CL/CDi which was 63% below the dual wing baseline. Systematic result are presented which will demonstrate trends as well as magnitudes for the best types of dual wing configurations for minimum induced drag.