Japan Aerospace Exploration Agency (JAXA) has constructed the JAXA practical pressure-sensitive paint (PSP) measurement system for their large industrial wind tunnels. Its system and application tests were introduced. Contents of the system which included PSP paint, pressure calculation method and apparatus were described. A high accuracy pressure calculation method, a priori/in situ hybrid method, was also introduced and applied to the data processing. For validating this PSP system, an experiment using an ONERA M5 standard model was conducted in a transonic wind tunnel. PSP results represented global quantitative pressure distribution. The PSP data accuracy, 2σ, of the system compared with pressure taps was 1.9 kPa (Cp = 0.06 at M = 0.84). Then, the JAXA practical PSP measurement system was applied to the Japanese regional jet development test. Its results also represented a detailed and global flow structure on the test model. 2σ of PSP data was Cp = 0.06 at cruising condition. It was proved that the present PSP system could be applied to practical tests at a large industrial transonic wind tunnel.

The main purpose of the present paper is to show that the local homogeneous holonomy group of the conformally flat Riemannian manifold is the full rotation group with some exceptions, 1. Let M be an n dimensional conformally flat Riemannian manifold (n ^ 3), the metric being given by ds 2 = cf'Σdx} in a coordinates neighborhood U with a function a-aixi, . . . , x n ) of class 2. We take rectangular frames in the tangent spaces at each point of U and put according to the frames When we puty,7r/ is a flat metric, and if we take πij such thatthen we have by the flatness of "Σπ)Next we putand we getThus (Oij are the parameters of the Riemannian connection of M in U. Now we calculate the curvature forms of M. Putting

No abstract

Pressure-sensitive paint measurement can obtain a much more detailed surface pressure distribution than can be obtained using conventional pressure taps. However, the pressure-sensitive paint is sensitive not only to pressure but also to temperature, and where high accuracy is required, it is essential to compensate for this temperature dependency. This paper discusses data processing methods for pressure-sensitive paint measurement in transonic industrial wind tunnel testing, and proposes three methods to compensate for temperature dependency of the pressure-sensitive paint: an in situ method, an a priori method, and a hybrid of a priori and in situ methods. The pressure distributions from the pressure-sensitive paint data obtained by these proposed methods are compared with pressure tap data measured by conventional pressure transducers, and it is confirmed that the proposed methods are effective in compensating the temperature dependency of pressure-sensitive paint and improve the accuracy of the obtained data. It is also found that the hybrid of a priori and in situ methods is widely applicable to the industrial wind tunnel testing even if the pressure range of the pressure tap data is limited. Nomenclature C p = pressure coefficient C PSP = compensation constant for PSP data C TSP = compensation constant for TSP data f, g = functions of pressure ratio and temperature ratio I = luminescence intensity M = Mach number p = pressure T = temperature x=c = airfoil chordwise coordinate measured from leading edge, normalized by chord = angle of attack = standard deviation Subscripts PT = pressure tap location ref = reference condition in wind tunnel testing refc = reference condition at calibration TM = thermometer location 0 = stagnation condition 1 = freestream conditions