Thermal effect of the slanted surface around the central hole of a miniature delta wing on the leading-edge Vortices

The main feature of a delta wing is in the generation of vortices on the leading edge of its wings to provide additional stable lift at high angle of attack. The main purpose of this study is to analyze the impact of lee side central holes under thermal condition to the development of vortex flow field at the tip of a miniature delta wing and find the region with the most significant changes in the velocity and pressure gradient to serve as the thermal control location of a future delta wing. The study chooses near wing surface heat flux of Q=100W/m² and 10W/m², representing the high and the low heat flux, at Reynolds number, Re=2.64×10³ and 8.84×10³, to perform flow field analysis. The study finds: the temperature effect under the high heat flux produces a significant impact on the angle of attack (AOA) and the angle of sideslip (AOS) of the delta wing and can easily cause the occurrence of asymmetric flow field of vortices at the downstream tip of the delta wing. Additionally, because a significant velocity and pressure gradient exist around the corner on the bottom slanted surface of the lee side central hole in the delta wing, the temperature impact on the change of AOA is most pronounced and it is also the region of which the development of vortex flow field is most affected. These findings could provide information on realizing the thermal effect on the leading-edge vortices over the miniature delta wing for future optimal flow control.