Comparisons of calculated and experimental transonic unsteady pressures and airloads for four of the AGARD Two Dimensional Aeroelastic Configurations and for a rectangular supercritical wing are presented. The two dimensional computer code, XTRAN2L, implementing the transonic small perturbation equation was used to obtain results for: (1) pitching oscillations of the NACA 64A010A; NLR 7301 and NACA 0012 airfoils; (2) flap oscillations for the NACA 64A006 and NRL 7301 airfoils; and (3) transient ramping motions for the NACA 0012 airfoils. Results from the three dimensional code XTRAN3S are compared with data from a rectangular supercritical wing oscillating in pitch. These cases illustrate the conditions under which the transonic inviscid small perturbation equation provides reasonable predictions.
Experience with Transonic Unsteady Aerodynamic Calculations
1984
23 pages
Report
No indication
English
Aerodynamics , Aerodynamic configurations , Aeroelasticity , Airfoils , Dynamic structural analysis , Flutter analysis , Supercritical wings , Sweptback wings , Transonic flutter , Unsteady flow , Loads (Forces) , Nonstabilized oscillation , Pitching moments , Pressure , Subcritical flow , Wing flaps , Wing oscillations