Robust design of an aerodynamic compensation pitot-static tube for supersonic aircraft

We have designed an aerodynamic compensation pitot-static tube that improves upon the traditional ogival pitot-static tube. The proposed design is able to provide the desired compensation in both subsonic (negative value of the pressure coefficient Cp) and supersonic (zero value of Cp) regimes at the same axial location. At this axial location, the local Cp gradient is small in the subsonic regime and is close to zero in the supersonic regime so that in practical application, this pitot-static tube would perform better than an ogival pitot-static tube. The proposed design can be used effectively to compensate for Cp position errors of up to +0.1 in the subsonic regime, by nondimensional stretching of the basic profile, while maintaining zero Cp in the supersonic regime. Computational fluid dynamics is used in the design and analysis of the proposed pitot-static tube. The complete Mach number regime (Mach less than two) has been computationally analyzed for different profiles resulting from stretching of the basic profile, to validate the proposed design's capability. A design methodology is also presented in which a specific pitot-static tube profile can be extracted from the general nondimensional profile to aerodynamically compensate for a known position error in Cp.