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The structural integrity of a store and its attachments to a fighter aircraft has to be verified at various aircraft maneuvering conditions in its flight envelope for the clearance of the store to integrate with aircraft. The captive loads of a flight vehicle mounted on a fighter aircraft have been estimated at various Mach numbers, angles of attack, and sideslip angles using an indigenously developed 3-D grid-free Euler solver. The point distributions required to apply grid-free solver are obtained using chimera cloud technique, and the connectivity required for the solver is obtained using gradient search method. Forces and moments acting on the fighter aircraft with launchers and flight vehicles have been estimated using computational fluid dynamics simulations at different flow conditions, and load distributions on flight vehicle have been obtained. The aerodynamic loads obtained from computational fluid dynamics calculations form the basis of the flight testing.

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