One method of solving the problem of burning or combustion at supersonic speed is by combusting in a stationary detonation wave. Stabilization of a detonation wave has been recently accomplished and is reproducible, but only in laboratory type apparatus. Using two-dimensional steady flow, perfect gas theory, this paper provides solutions for the changes in properties that may be expected across any oblique detonation wave. Equations are established and solved using the Control Data Corporation 1604 digital computer of the U. S. Naval Postgraduate School, Monterey, California, for different values of specific heat ratio, initial Mach number, a function of the flow deflection angle, and the amount of heat added in the detonation. The results appear in tabular form and for several specific values of Mach number and heat addition in graphical form. An example of use of the data is shown with reference to a ramjet engine operating with a stationary detonation wave for the combustion process.