A method is described to determine hypersonic flow around a two dimensional flat plate at angle of attack. The existing method of integral relations for asymmetric flow has been combined with the constant density solution, which is valid near the axis of symmetry, Examples are presented for various incidence angles at a Mach number of 6. These are compared with results from standard method of integral relations and with available experimental measurements. It is shown that the stagnation points agree with experimental results closer than the standard method of integral relations.