Numerical investigation of hypersonic flow and heating over two models of an interplanetary probe was carried out at Mach numbers from 6 to 20 and Reynolds numbers Re ∞,D from 0.7×10 5 to 16×10 5 . The models differ mainly by the shape of the back surface simulating the payload container. The Reynolds number, at which laminar-turbulent transition takes place in the near wake, was defined at Mach numbers M = 6–8. It was shown that at turbulent base flow, the heat flux to the back surface of a blunted body can be comparable with the heat flux at the forward stagnation point. The results of numerical flow within the framework of Navier-Stokes and Reynolds equations simulation were compared with the experimental data.