The Advection Upstream Splitting Method (AUSM) is used to compute 2D inviscid hypersonic flow over a semi-cylinder on a finite volume framework. Solution reconstruction to achieve higher order accuracy is done using the MUSCL-type reconstruction technique with the Van Albada and Hemker-Koren limiter functions. The gas models under consideration are the perfect gas model and the high temperature equilibrium chemically reacting air model of Tannehill and Mugge. The performance of these limiters in computing hypersonic flows is analyzed and compared with the first order accurate method. Keywords:Hypersonic, shock, reconstruction, limiter