Numerical Investigation of the Effect of Aircraft Nose Wall Waviness on the Hole Pressure of the Static Pressure Probe

The existence of the aircraft nose skin waviness will affect the static pressure measurement, and then affect the altitude indication of aircraft. So it is of great significance to study the effect of waviness on the flow field around the probe. In this paper, the k-ω SST model is used to carry out numerical simulation research on the influence of the aircraft nose skin waviness on the hole pressure of the total static pressure probe. The results show that the numerical simulation method can meet the requirements of the numerical simulation of the flow field around the total static pressure probe on the nose surface. For the single aircraft nose configuration, the influence of skin waviness on the pressure in the spatial area near the pre-installation position of the probe increases with the increase of Mach number, while the influence of angle of attack can be ignored. For the nose-probe combination configuration, the influence of skin waviness on the pressure coefficient at the measuring hole of the probe increases with the increase of Mach number. The influence of skin waviness on the first group of pressure holes S1 is greater than that on the second group of pressure holes S2. At the same time, it is found that the presence of the total static pressure probe does not change the influence of waviness on pressure coefficient obviously.