Numerical Investigation of Co-Flow Jet 3D Transonic Wings

This paper numerically investigates CoFlow Jet (CFJ) 3D transonic wings formed with the 10% thickness NASA SC(2)-1010 and the 12% thickness RAE-2822 airfoils. The present research is based on validated CFD simulation, which employs 3D RANS solver with Spalart-Allmaras (S-A) turbulence model, 3rd order WENO scheme for the inviscid fluxes, and 2nd order central differencing for the viscous terms. For zero sweep and aspect ratio of 10, the CFJ-NASA SC(2)-1010 wing is shown to increase cruise-efficiency C_L/C_Dc by 10% and lift coefficient by 10% simultaneously over the baseline wing. When the sweep angle is increased to 10^◦, the improvement is decreased. Similarly, wings formed by CFJ-RAE-2822 are able to increase aerodynamic efficiency at zero sweep and aspect ratio of 10. Decreasing the CFJ jet strength from root to tip is beneficial to reduce drag and power consumption while maintaining lift enhancement due to decreased tip loading. Applying the CoFlow Jet to only the inner span of the CFJ-RAE-2822 wing sees a CFJ power reduction benefit over having injection and suction extend to the wing tip. This method also provides a lift and cruise efficiency benefit over the baseline wing. The outer 30% span shows a diminished supersonic region. Applying the CFJ to the innjer 70% results in reduced power consumption while increasing performance including a 1.2% increase in aerodynamic efficiency over baseline and a 5.7% improvement in lift coefficient in case CFJ-3D-14. Productivity efficiency is similarly increased by 7.1%.