1. I. Introduction he idea of Mars exploration by a Mars airplane with fixed wing1-4has been considered as a new and attractive approach to obtain academically interesting data about the Martian surface and atmosphere. Mars airplanes can
2. To assure the accuracy in flow measurement over the wide range of pressure, a baratron pressure sensor (627-12T, MKS) and a piezo transducer (Series902, MKS) are used as a pressure calibrator for pressure ranges of 0-13.3 kPa and0.133-133kPa, respectively.
3. The setup for PSP measurement is shown in Fig. 6. The optical equipment was placed outside the vacuum chamber and measurements were made through an optical window on the top of the vacuum chamber and a transparent ceiling of the test section made of acrylic. Two UV-LED arrays with 395 nm wavelength were used as an excitation light source. A Iuminescent image was captured by a thermoelectrically cooled 12-bit CCD camera (Hamamatsu, C4742-95-12ER) with an optical band-pass filter (transmission wavelength 670-20 nm). F1.4 camera lens (Nikon, 50mm) was attached to the camera. In this study, calibration is made in the test section and using the model during the evacuation process of the vacuum chamber. A change in model temperature during the calibration is small and negligible. In this method, the calibration coefficients are obtained on each pixel of the image of the modelsothatthenon-uniformity in pressure sensitivity can be corrected.
4. On the other hand, for TSP measurements, two BLUE-LED arrays and an optical band-pass filter with transmission wavelength 620-10 nm were used as an excitation light source. The other setup is the same as that for PSP measurement. (a) Side View ofthe MWT Setup for PSPMeasurement (b) Optical Setup
5. Fig.6 PSP measurement in the MWT D. Data Acquisition and Processing