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Experiments on Shock Induced Laminar-Turbulent Transition on a Flat Plate at Mach 6

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Figure

Figure 2: Experimental set-up As shown in figure 2a the model consists of the following main parts:
Figure 3: Shock generator and shock impingement positions
Figure 4: Positions and numbering of the sensors
Figure 5: Temperature increase on the PEEK insert due to free transition for various nose radii and angles of attack at Re u,∞ = 16 · 10 6 1 m
+6

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