Subsonic-transonic submerged intake design for a cruise missile

Akman, Oral
In this thesis, aerodynamic design and optimization of subsonic-transonic submerged intake is done for specified cruise conditions. A gradient-based optimization algorithm is developed for intake design studies. Subsonic intake geometric parameterization is conducted and a generic submerged intake for a cruise missile is constructed by using CATIA V5 generative shape design module. Computational Fluid Dynamics (CFD) solver FloEFD v12 is used for computational analyses. Two NASA test cases are used for CFD tool validation. Developed optimization algorithm is validated using random initial intake geometry by setting all design parameters free and not using any geometric limits. Application of subsonic intake design optimization is done after validation of optimization algorithm. Intake geometries are compared to each other which are obtained from optimization iterations. CFD analyses are conducted at engine corrected mass flow rate about 4.43 kg/s. All geometries, obtained from optimization algorithm, are compared to each other. Optimized geometry reached 0.945 Pressure Recovery (PR) coefficient and 0.0262 Distortion Coefficient (DCDPCP). An inferior intake geometry chosen as starting point for the optimization algorithm and after five optimization iterations 6.4% improvement in PR and about 45% enhancement in DC coefficients are achieved. On the other hand total axial force coefficient of cruise missile (CAbody) is reduced about 13% as intake design improved.
Citation Formats
O. Akman, “Subsonic-transonic submerged intake design for a cruise missile,” M.S. - Master of Science, Middle East Technical University, 2014.