C. Strangfeld, H.F. Müller-Vahl, D. Greenblatt, B.G. van der Wall, C.N. Nayeri, C.O. Paschereit

An experimental investigation was carried out to quantify the aerodynamic lift acting on a NACA 0018 airfoil subjected to combined pitching and surging and to compare the results to established theories. A dedicated unsteady wind tunnel was employed that produces large surge amplitudes, and airfoil loads were estimated by means of unsteady surface mounted pressure measurements. In-phase and out-of-phase pre-stall pitching and surging cases were considered for different velocity amplitudes. When the flow was fully attached, satisfactory correspondence was observed between experiments and theory. However, differences were observed when trailing-edge separation was present; in particular the shedding of a trailing-edge vortex corresponded with discrepancies between the experiments and theory.

41th European Rotorcraft Forum 2015

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

DGLR-Bericht, 2016, 2016-01, 41st European Rotorcraft Forum 2015; S.-; 2016; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

airfoils;trailing edges;lift;wind tunnels;surges;loads (forces);estimating;pressure;pressure measurement;vortices

Bestellbar

2016