A Low Fidelity Method for Flap Aerodynamic Design of a Cranked-Arrow Wing

A low fidelity method to calculate aerodynamic characteristics of wings is presented. This method is intended to be used in design of high lift devices in preliminary design stages of a supersonic transport to improve aerodynamic performance at take-off and landing conditions. A quasi-vortex-lattice method coupled with the leading-edge suction analogy was applied to calculate aerodynamic forces of a flapped cranked-arrow wing planform. Calculation results of lift and drag agreed well with the corresponding experiment data, and effects on the aerodynamic forces due to flaps were well estimated. Results show that the present method is capable of estimating the aerodynamic characteristics of flaps at take-off and landing conditions.