Effect of Nose Bluntness on Boundary-Layer Transition of a Fin–Cone Configuration at Mach 6
Experiments on hypersonic boundary-layer instability of a fin–cone configuration were conducted in a <i>Φ</i> 0.5 m Mach 6 Ludwieg tube tunnel. Infrared thermography and high-frequency pressure sensors were used to measure the transition front and instability waves under four different nose bluntnes...
Αποθηκεύτηκε σε:
| Κύριοι συγγραφείς: | , , , , , |
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| Μορφή: | Artigo |
| Γλώσσα: | Inglês |
| Έκδοση: |
MDPI AG
2026-01-01
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| Σειρά: | Aerospace |
| Θέματα: | |
| Διαθέσιμο Online: | https://www.mdpi.com/2226-4310/13/1/64 |
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