Unsteady pressures on a NACA 64A010 airfoil experimental and theoretical results
Unsteady pressures on a NACA 64A010 airfoil experimental and theoretical results
- New search for: Davis, J.A.
- New search for: Petrie, S.L.
- New search for: Davis, J.A.
- New search for: Petrie, S.L.
Transonic testing of an NACA 64A010 airfoil has been conducted at The Ohio Oetate University Aero-Astro Research Laboratory. This paper reports the results of both fixed angle of attack and pitch oscillation experiments conducted in the OSU-AARL 6' x 22' Transonic Airfoil Wind Tunnel. The model was equipped with both steady-state static pressure taps and unsteady pressure sensors. Theoretical and experimental comparisons are made with both steady state and oscillating pressure data. (DePo)
Document information
Unsteady pressures on a NACA 64A010 airfoil experimental and theoretical results
Versuche mit instabilem Druck auf NACA 64A010 Tragfluegel: Experimentelle und theoretische Ergebnisse
AIAA-Papers ; 1-10
1979
10 Seiten, 18 Bilder, 13 Quellen
Conference paper
English
Similar titles
Boundary-layer and stalling characteristics of NACA 64a010 airfoil section
| Engineering Index Backfile | 1950
| Engineering Index Backfile | 1949