Abstract:The direct problem of hypersonic flow past a V-shaped wing with a shock wave detached from the leading edges is solved. The reduced normal force coefficient and the lift-drag (L/D) ratio are calculated for a configuration with a lower part in the shape of a V-wing and a streamwise upper part.1. Consider a symmetrical flow past a V-wing with aperture angle "y and apex angle/3 (Fig. 1) 1 (:x -,f) (1.1) b=tg[3cosq',, h=tg~sinT,, T,= Let the function y=y~ z) represent the shape of the shock wave. Using the conserv… Show more
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.