Magnetic Hypersonic Flow Near the Stagnation Point at Low Reynolds Number
An investigation of the effects of wall temperature and of a magnetic field on the flow field at the stagnation point of blunt-nosed bodies in low-Reynolds-number hypersonic flow, with the intent of determining the possibility of using small magnetic fields to reduce heat transfer and skin friction in that region. Results indicate that a small magnetic field of the order of 1000 Gauss or less reduces both heat transfer and skin friction in high-altitude flight, but increases shock standoff distance. The strength of magnetic field required is attainable by a permanent magnet. Increasing the wall temperature tends to produce higher values of both the heat-transfer and skin-friction parameters, although the magnitude of the effect is less on the heat-transfer parameter. All of these effects diminish rapidly as the flow approaches the free-molecular-flow limit.