Low-Speed Flow Studies Using the Pressure Sensitive Paint TechniqueOptical pressure measurements have been made on a NACA 0012 airfoil coated with Pressure Sensitive Paint (PSP) at very low flow speeds (less than 50 m/s). Angle of attack was limited to 5 deg. for most measurements. Effects of temperature gradients and mis-registration errors on PSP response have been established and minimized. By reducing measurement error caused by these effects. PSP sensitivity has been enhanced. Acceptable aerodynamic data at flow speeds down to 20 m/s have been obtained and valid pressure paint response was observed down to 10 m/s. Measurement errors (in terms of pressure and pressure coefficient) using PSP with pressure taps as a reference are provided for the range of flow speeds from 50 m/s to 10 m/s.
Document ID
19980204016
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Brown, O. C. (Stanford Univ. Menlo Park, CA United States)
Mehta, R. D. (NASA Ames Research Center Moffett Field, CA United States)
Cantwell, B. J. (Stanford Univ. Menlo Park, CA United States)