Fig. 7From: Experimental study of bluntness effects on hypersonic boundary-layer transition over a slender cone using surface mounted pressure sensorsPSD of wall pressure fluctuations at different cone bluntness. The wall temperature of the cone model is 300 K, the stagnation pressure of the wind tunnel is 4E+ 5 Pa, the stagnation temperature of the wind tunnel is 454 K, and the corresponding Reynolds number is 4E+ 6/mBack to article page