Naddźwiękowy przepływ w obszarze wylotowym dośrodkowego wieńca kierującego

In the papera model of supersonic outlet flow in centripetal blade cascade has been presented. It has been proved that on the trailing edges under all working conditions of the blade cascade oblique curves shock waves should arise. Moreover, the character of a change of flow parameters on the slip line close to the trailing edge has been determined. The results have been illustrated on a photograph of supersonic flow through the model section of the centripetal biade cascade.