As a classical configuration, double-cone has been widely used in studies on shock/shock and shock/boundary-layer interactions. For the complexity of flow over a double-cone model, it is difficult to get the detailed aerodynamic heating data with traditional point measurement techniques. Temperature sensitive paint (TSP) technique, a global heating measurement technique makes acquiring such data possible. In this paper, surface heat flux distribution on the 25°/35° and 25°/55° double-cone models are measured in shock tunnel at free stream condition of Mach number 12, Reynolds number ranging from 8.14×105 to 2.83×106/m. Both thin film gauges and TSP are used in the measurement. Also, Schlieren has been taken as an auxiliary approach. Although the test time for the shock tunnel is less than 10ms, the fast response TSP technique could still get quantified results that show clearly change of the aeroheating on the double-cone model with different cone angles and in the different test conditions caused by shock/boundary-layer interaction, shock/shock interaction and flow separation etc.. The temperature distribution is calculated from the pre-calibrated relation between luminescent intensity and temperature. One dimensional heat transfer theory is applied to calculate the heat flux distribution from temperature results with assumption that the aeroheating is step rised to a constant value during the test time. TSP results are qualitatively agreed with the schlieren images. Of the first cone, the thin film gauge results also well agree with the TSP results. But on the second cone, the thin film gauge results are much higher than the TSP results in almost all test conditions. Several possible factors may induce such phenomena. For example, on the location of the shock wave reattachment on the second cone, the model surface temperature may be higher than the measurement limit of the TSP technique. This would make the TSP results incorrect. Also, the TSP model surface is always smoother than the thin film gauge model surface. This may develop two different boundary layer states on the two kinds of models, especially in the complicated flow field, and then cause the different heat transfer rate.
