Aerodynamic interaction of heat transfer with steady transonic flow

This thesis is concerned with the effect of heat transfer on steady transonic flow in a two-dimensional, convergent-divergent duct. The problem was studied by means of experiments in a combustion tunnel.

An experimental investigation to determine the shock position and sonic line was carried out at total pressures ranging between 4 and 20 psig, total temperatures between 40 and 1000°F and wall temperatures between 50 and 900°F. Detailed duct wall pressures and shock positions were obtained for various expansion ratios and wall-to-fluid temperature ratios. The two-dimensionality of the duct flow was verified by wall pressure measurements. In addition, the fact that the flow was turbulent was verified.

For the experimental conditions investigated, it was confirmed that the change of the sonic line due to the effect of the heat transfer was small. However, the displacement thickness downstream of the shock became markedly thinner as the duct walls were cooled. Thus the position of the shock was shifted by wall cooling. The extent of the shock movement in the present experiment was of the same order as the throat height for the expansion ratio p_e/p_t of about 0.5 and wall-to-fluid temperature ratio T_w/T_t of approximately 0.5.