Hypersonic aircraft surface temperature prediction method based on electronic transpiration cooling

The invention provides a hypersonic flight vehicle surface temperature prediction method based on electronic transpiration cooling, and relates to the technical field of aerospace, and the method comprises the steps: S1, building a geometric model of a target hypersonic flight vehicle, and setting an initial boundary condition; s2, carrying out unbalanced flow field numerical simulation according to the initial boundary condition to obtain spatial flow field parameter distribution; s3, determining the ion number density, the ion velocity and the surface thermal load at the stationary point according to the spatial flow field parameter distribution; s4, inputting the ion number density and the ion velocity into a pre-constructed hot electron emission double-sheath model to obtain electron transpiration cooling heat dissipating capacity; s5, according to the surface thermal load and the electron transpiration cooling heat dissipating capacity, the surface temperature of the stationary point is obtained; judging