Thin airfoils flying at nearly sonic velocities display a distinct shock pattern commonly referred to in the literature as the“fishtail” shock structure. Specifically, this pattern comprises two oblique shock waves originating at the trailing edge of the airfoil, which interact with a detached, nearly normal shock wave at two triple points situated along the oblique shocks. In the context of a NACA0012 airfoil, the utilization of both shock-fitting and shock-capturing CFD simulations in this work, alongside classical shock-polar analysis, make evident that these interaction points cannot be adequately modeled using von Neumann’s three-shock theory, originally formulated during World War II for triple points arising in Mach reflection. Our analysis indicates that the four-wave interaction model proposed by Guderley offers a more suitable framework for modeling this phenomenon.
On the Nature of the Fishtail Shock-Shock Interaction in the Transonic Flow Past A NACA0012 Profile
Bonfiglioli, A.;
2025-01-01
Abstract
Thin airfoils flying at nearly sonic velocities display a distinct shock pattern commonly referred to in the literature as the“fishtail” shock structure. Specifically, this pattern comprises two oblique shock waves originating at the trailing edge of the airfoil, which interact with a detached, nearly normal shock wave at two triple points situated along the oblique shocks. In the context of a NACA0012 airfoil, the utilization of both shock-fitting and shock-capturing CFD simulations in this work, alongside classical shock-polar analysis, make evident that these interaction points cannot be adequately modeled using von Neumann’s three-shock theory, originally formulated during World War II for triple points arising in Mach reflection. Our analysis indicates that the four-wave interaction model proposed by Guderley offers a more suitable framework for modeling this phenomenon.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
