Transonic Wind Tunnel Tests on a NACA 0012 Aerofoil,
AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)
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Transonic wind tunnel tests on three geometrically similar NACA 0012 aerofoil models are reported. The tests which comprised surface pressure distribution and wake traverse measurements covered a Mach number range of 0.50 to 0.82 and an incidence range of 0 to 8 deg. The test Reynolds numbers for the three models were 1,680,000, 840,000 and 420,000 for the large, intermediate and small models respectively. Brief tests on the two larger models at reduced Reynolds number were also included. All tests were conducted with artificial boundary layer transition fixing on both surfaces. The main purpose of this investigation was to provide data to evaluated wall interference effects in the transonic wind tunnel. The data should also be useful for checking the accuracy of interference theories at high subsonic speed.
- Fluid Mechanics