Scramjet engine combustion chamber performance pre-evaluation method

The invention provides a scramjet engine combustion chamber performance pre-evaluation method. By taking a thermal throat as a starting point, parameter distribution from the starting point to a combustion chamber inlet and from the starting point to a combustion chamber outlet is calculated, and the problem that a singular value is apt to occur in the thermal throat during solution due to a reason that the traditional one-dimension calculation is performed from the combustion chamber inlet is avoided. The scramjet engine combustion chamber performance pre-evaluation method fully considers the different working modes of the combustion chamber and provides a reference basis for the design of the combustion chamber within a wide flight Ma range.