A numerical analysis of the inlet-combustor interaction and flow structure through a scramjet engine at a flight Mach number M = 6 with parallel injection (Strut with circular inlet) is presented in the present research article. Three different angles of attack (α=-4°. α=0°. α=4°) have been studied for parallel injection. https://hollandscountryclothinges.shop/product-category/hip-flasks/