The accuracy of a single-sweep parabolized Navier-Stokes(SSPNS) algorithm for aeroforce and aeroheating prediction in hypersonic flow fields has been tested through three typical cases.The results suggest: 1) It is feasible for the SSPNS algorithm to predict hypersonic laminar compression corner flows with wedge angle smaller than 15°

when there is no obvious streamwise flow separation.2) According to the numerical results of cone flows(biggest attack angle 24°)

the simulation of transverse separations with the SSPNS algorithm are reliable.3) For the flows over a two-dimensional wing with attack angle smaller than 12°

the accuracy of the SSPNS algorithm corresponds to that of time-iterative algorithm.4) As compared to the traditional time-iterative full Navier-Stokes

the SSPNS algorithm's computational speed is faster by 1～2 order of magnitude and presents a considerable storage saving.