A High Temperature Fiber Optic Sensor (HTFOS) has been developed at NASA GlennResearch Center for aircraft engine applications. After fabrication and preliminary in-house performance evaluation, the HTFOS was tested in an engine environment at NASA Armstrong Flight Research Center. The engine tests enabled the performance of the HTFOS in real engine environments to be evaluated along with the ability of the sensor to respond to changes in the engine's operating condition. Data were collected prior, during, and after each test in order to observe the change in temperature from ambient to each of the various test point levels. An adequate amount of data was collected and analyzed to satisfy the research team that HTFOS operates properly while the engine was running. Temperature measurements made by HTFOS while the engine was running agreed with those anticipated. Nomenclature d 1 = Outer diameter of a smaller diameter ceramic tube d 2 = Outer diameter of a larger diameter ceramic tube dn = infinitesimal change in the refractive index dT = infinitesimal change in temperature 2 N = number of grating line spacings in a grating n = refractive index P i,j = Pockel's coefficient of the stress-optic tensor α = coefficient of thermal expansion of the fiber material Δn = longitudinal periodic variation of the refractive index of the optical fiber core in a grating ΔT = temperature change Δλ = full-width-half-maximum bandwidth of a grating = shift in the Bragg wavelength due to temperature and pressure ε = applied strain G = grating period λ G = Bragg wavelength ν = Poisson's ratio