Wind tunnel evaluation and calibration of model rocket nosecone Pitot-static probes

As part of an instrumentation course for third-year Electro-Mechanical Engineering Technology students, model rockets were used as an experimentation platform. The nosecones of several model rockets were modified to form Pitot-static probes to measure the velocity of the rockets in flight. An electronic pressure sensor was used to measure the differential pressure between the static and stagnation ports of the probe. Students evaluated the performance of the nosecone Pitot-static probes in the controlled conditions of a wind tunnel facility. The actual performance data was compared to the theoretical predictions of Bernoulli's theorem. The students used the wind tunnel test data to create a calibration table for each Pitot-static probe that was then used in the analysis of the actual rocket flight data. In this paper, the construction of the modified model rocket nosecones is described in detail. Nosecone geometry and port placement considerations are also presented. The wind tunnel testing data is presented and compared to the theoretical predictions. Actual rocket flight data and its analysis is also presented and discussed. Details of the data acquisition systems used for the wind tunnel testing and in-flight data recording are also provided.