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A pressure measurement technique based on a photoluminescent coating is being developed and used for aerodynamic applications. Visible light excites probe molecules in the paint and their luminescence is related to the static pressure. Details of the illumination, luminescence detection, and data reduction for this technique are presented. These include key issues such as temperature effects, camera calibration, and model movement. Results from this technique in a variety of flowfields are given. Comparisons with pressures measured using standard wall taps show good agreement. Nomenclature b = intercept of the calibration function / = luminous intensity K q -Stern-Volmer constant M -Mach number m = slope of the calibration function P = pressure Po 2 = partial pressure of oxygen R = fitted slope of the calibration function S = fitted intercept of the calibration function T = temperature X = wavelength Subscripts cal = calibration condition ex = excitation ref = reference condition run = test condition 0 = zero oxygen partial pressure

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