Results are presented of unsteady separated flow computations using the LTRAN2-NLR code (low-frequency transonic small perturbation theory) coupled in strong interaction with Green's lag-entrainment method for a steady turbulent boundary layer. Computations of shock-induced separation have been carried out for a supercritical airfoil oscillating in pitch and for the NACA 0012 airfoil at a transient change of angle of attack.
Computations of Separated Subsonic and Transonic Flow about Airfoils in Unsteady Motion
1984
15 pages
Report
No indication
English