What is the formula for the calculation?
Article Impact of parameterized lee wave drag on the energy budget o...
please see aerodynamics by John Anderson, pages 714-716
One option to estimate wave drag except for other drag components in CFD is "drag decomposition". (http://arc.aiaa.org/doi/abs/10.2514/2.7300?journalCode=aiaaj) In this method, whole domain is decomposed by using some sensors such as shock sensor or viscosity sensor.
The formula can be obtained from linearised supersonic flow theory, available in Anderson (Fundamentals of Aerodynamics), as has previously been posted:
For flat plate aerofoil: cd_w = 4*(alpha)^2 / (M^2 - 1)^0.5
For double-wedge aerofoil: cd_w = 4*[(alpha)^2 + (t/c)^2] / (M^2 - 1)^0.5
Where: alpha is angle of attack; M is freestream Mach number; t/c is thickness-to-chord ratio. These equations are applicable at low alpha (generally
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