This numerical study explains the supersonic wave interaction for a slender cone-cylinder body, at a constant acceleration magnitude of 400g with results reported at 10 \(^\circ \) angle of attack. ANSYS Fluent \(^{\text{\textregistered} }\) V.19.0 with a Moving Reference Frame (MRF) acceleration technique was used to model the acceleration motion. Results were compared to constant velocity flight Mach numbers 1.00, 1.07 and 1.10. The asymmetric bow shock wave, in comparison to steady state, was shown to be fully developed at a flight Mach number \(\approx \) 1.10. The transonic lambda shock that developed aft of the cone-cylinder shoulder during transonic acceleration had a rear foot that propagated downstream on the cylinder surface during acceleration above flight Mach number 1.00 until approximately 1.10. This rear foot propagates both in the axial and radial direction and decays in strength as the projectile accelerates. This rear foot was identified as a shock wave for supersonic flight Mach numbers near 1.00.