Numerical Approach to the Analysis of Internal Pressure of M–V Rocket Fairing

Navier-Stokes simulations are performed for time variation of the pressure inside the nose-fairing of M–V rocket. As the altitude increases during the launch of the rocket, flight Mach number and ambient conditions change with time. The numerical method to treat such an unsteady phenomenon is described in detail. The external pressure around the venting hole rapidly drops due to the passage of the local shock-wave over the rocket surface at transonic speed. The pressure inside the nose-fairing changes, because the external pressure is weakened through the venting hole. The effect of the time-accuracy is investigated.