Experimental and Numerical Investigations of Boundary Layer Transition on Blunted Cones at Supersonic Flow

Laminar–turbulent transition reversal on blunt ogive body of revolution at hypersonic speeds

“…Afterwards, a reverse tendency is observed with the transition point moving to the nose. The phenomenon was further confirmed by subsequent wind tunnel experiments [2][3][4][5][6][7][8] on blunt cones and plates.…”

“…Figure 4(a) shows reversal data from various experiments and correlation using the parameter K (figure taken from Brazhko et al 4 ). Figure 4(b) shows the present data and the data from Marineau et al 5 in a similar manner.…”

“…4 Data taken from literature. 3,4,12,33–38 M ∞ = 5–12, θ = 5–10°, R = 0.064–63 mm. K = (Re ∞,R ) 0.5 × M ∞ 2 × Sin(θ) (θ – cone half angle).…”

“…However, data obtained in Brazhko et al. 4 clearly indicate that reversal can be observed at fixed Re ∞,1 (therefore fixed flow disturbances level) and increased R. In this case, reversal still could be triggered by a bypass scenario due to the possible increase of boundary layer sensitivity to bypass with increasing radius. Unfortunately, no flight 23 or ballistic range 24 data on smooth-body reversal are available.…”

“…A parameter that generalizes Re ∞,R : K = (Re ∞,R ) 0.5 × M∞ 2× Sin(θ), (θ – cone half angle) was suggested in Brazhko et al. 4 Experimental data in the range M ∞ = 5–12, θ = 5–10°, R = 0.064–63 mm are described by a universal dependency Re ∞,t (K) reasonably well (Figure 4(a)). Similar to Re ∞,t (Re ∞,R ) dependency, Re ∞,t (K) dependency consists of increasing and decreasing parts.…”