In order to combine the advantages

a compact scheme based on finite volume method was developed. A characteristic limiter was used to prevent non-physical oscillations across discontinuity

so the scheme was suited to simulate supersonic flows in aerospace flight. The performance of the scheme was assessed by computing several typical problems. Numerical results reveal that the present scheme can capture discontinuities with few oscillations and simulate various waves sharplybesides

the scheme is able to distinguish small-scale flow structures clearly

and the results solved by the scheme are highly consistent with exact solutions.