title: Towards transition modelling for supersonic laminar flow control based on spanwise periodic roughness elements.
abstract: Laminar flow control (LFC) is one of the key enabling technologies for quiet and efficient supersonic aircraft. Recent work at Arizona State University (ASU) has led to a novel concept for passive LFC, which employs distributed leading edge roughness to limit the growth of naturally dominant crossflow instabilities in a swept-wing boundary layer. Predicated on nonlinear modification of the mean boundary-layer flow via controlled receptivity, the ASU concept requires a holistic prediction approach that accounts for all major stages within transition in an integrated manner. As a first step in developing an engineering methodology for the design and optimization of roughness-based supersonic LFC, this paper reports on canonical findings related to receptivity plus linear and nonlinear development of stationary crossflow instabilities on a Mach 2.4, 73 degrees swept airfoil with a chord Reynolds number of 16.3 million.
authors.affiliation: NASA Langley Research Center, Hampton, VA 23681, USA. meelan.m.choudhari@nasa.gov
authors.forename: Meelan
authors.initials: M
authors.lastname: Choudhari
authors.forename: Chau-Lyan
authors.initials: CL
authors.lastname: Chang
authors.forename: Li
authors.initials: L
authors.lastname: Jiang