Abstract
PurposeTo improve inviscid compressible flow solution.Design/methodology/approachA local element‐size calculation procedure in the streamline direction and a local variable smoothing approach are employed to improve inviscid compressible flow solution. The characteristic based split approach is used as basic solution procedure to demonstrate the employed improvements.FindingsResults show that employing the element size in the streamline direction improves the solution accuracy in the transonic flow region. The nodal variable smoothing is very effective below a Mach number of 0.85 and produces results without any spatial oscillations.Originality/valueThis paper fills the gap by suggesting novel procedures to study Mach number range between zero and supersonic flow.
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