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Typical derivative aircraft share nose geometry and air data sensors installations and Static Source Error Correction (SSEC). So, those derivative designs are expected to present similar air data calibration residual errors. Although such results are somehow expected, the certification process requires evidence from flight tests and analyses. During the certification of a derivative model of a regional jet, Computational Fluid Dynamics (CFD) analyses have been conducted in order to evaluate the suitability of such tool for this problem. Both the basic and derivative models are assumed to share: (i) nose geometry; (ii) air data sensors positions and installation and (iii) Static Source Error Correction (SSEC). CFD simulations have been performed for different configurations and flight conditions.

In this article, a methodology for flight tests to determine the stall speed is adapted for UAVs (unmanned aerial vehicles). The UAV is equipped with a system of data acquisition to store the variables related to the stall speed during the flight of the aircraft. Next the data is processed to determine the stall characteristics of the aircraft and consequently its stall speed. The results are compared with analytical calculations to validate the proposed methodology.