Spike root oblique jet effect on drag and heat load reduction performance for hypersonic vehicles

How to effectively reduce aeroheating load and drag is an important issue in the engineering application of the hypersonic vehicles. In this paper, a novel combined aerodisk-spike root oblique jet strategy has been proposed for drag and heat reduction. The Reynolds-averaged Navier Stokes equations are solved based on the finite volume method, and the shear stress transport turbulence model is used. The reliability of the developed in-house codes has been verified systematically. The results demonstrate that the introduction of aemdisk and oblique jet makes the flow field change obviously, and this novel strategy gets an excellent effect on drag and heat reduction. Then the laws of pressure and Stanton number distributions have been studied in deep. Furthermore, the influences of spike length, oblique jet pressure ratio, and aerodisk diameter on the flow field, drag and heat reduction performance are investigated. Increasing the spike length-to-diameter and jet pressure ratio can enhance the performance of drag and heat reduction. The drag coefficient decreases by about 26% when the spike length-to-diameter increases from 0.5 to 3.0, and the total heat load can be decreased by 38.6% as the jet pressure ratio increases from 0.4 to 0.7. The larger aerodisk diameter can also get a better heat reduction performance. However, the increasing of aerodisk diameter makes the total drag rise sharply. The total drag coefficient increases by about 43% as the aerodisk diameter ratio varies from 0.18 to 0.48.