1. For severalyears MTU and DLR havebeen working on the CRISP*concept in a close cooperation' which has also included numerical and experimental investigations on the first CRISP rotor in the Institutefor Propulsion Technology of the DLR. This rotor has 10blades, adiameter of 400mm, and a hub to tip ratio of 0.25 and is run at approximately 12000rpm and a corrected mass flow of m =23.5kg/s. The data have been carried out at off-design with a blade setting for a max climbcase.The relative inlet Machnumber is high subsonic with transonic regions on the suction side of the blades from about 65%blade height.
2. Investigations on piezoresistive high speed probes with their provided m:tnufacturcr's temperature error compensation haw shown an inaccuracy as high as 10% FS (Full scalc). Thc compcnsation method uscd is based on thc rncthod previously dcscl-ibcd in Chcrrctt', Epstein' and maas^^.^and compensates thetemperature's influence with an inaccuracy of less than 0.1%FS.Theremaining mcasurement error isitshysteresis. A FlT-analysis of the data shows a main frequency bandwidth of 35kHz whereas the high frequency response probe has an eigenfrequency found to be approximately 130kHz. The signal of the pressure probe is sampled at a rate of IMHz by a 12-Bit two channel digital oscilloscope which is triggered by a highly accurate hall transmitter mounted onthedrivingshaft. Thehigh frequency response probes are Kulite types XB-21-062-5D. A flow angle's calibration is necessary and for further tests in preparation.