Transonic testing of an NACA 64A010 airfoil at the Ohio State University Aero-Astro Research Laboratory is described, and results of fixed angle of attack and pitch oscillation experiments are discussed. The operating range was Mach 0.20 to 1.07 with available total pressures of 140,000 N/m2 to 620,000 N/m2. The airfoil model was mounted on roller bearings installed in the solid sidewalls of the tunnel test section. The equipment included transducers to measure unsteady pressures, and static pressure taps obtaining steady-state data. The data gathered at Mach 0.8 gave an indication of the influence of the natural shock instability and shock-induced flow separation on the unsteady pressures, with the location of the peak disturbance level shifting forward in the comparison of 0 to 2 deg pitch angle data. The oscillating airfoil data is examined in terms of harmonic content and the in-phase and out-of-phase components. It is concluded that the experimental data has good qualitative comparison with methods accounting for shock interaction.
Unsteady pressures on a NACA 64A010 airfoil - Experimental and theoretical results
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1979 ; New Orleans, LA
1979-01-01
Conference paper
No indication
English
Unsteady pressures on a NACA 64A010 airfoil experimental and theoretical results
Tema Archive | 1979
|Boundary-layer and stalling characteristics of NACA 64a010 airfoil section
Engineering Index Backfile | 1950
|