Pressure-Sensitive Paint measurement of the flow around a simplified car model

Yamashita, Taro; Sugiura, Hideaki; Nagai, Hiroki; Asai, Keisuke; Ishida, Keitaro

doi:10.1007/bf03181696

Cited by 47 publications

(20 citation statements)

References 9 publications

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“…The calibration coefficients were obtained by using a sample plate in a static calibration chamber. Additionally, the temperature correction method using a correction factor (T) 11 was applied. Using this method, the Stern-Volmer equation is expressed in the following form:…”

Section: B Time-series Pressure Distributionmentioning

confidence: 99%

Unsteady PSP Measurement of Transonic Buffet on a Wing

Sugioka

Numata²,

Asai³

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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In this study, unsteady pressure field caused by transonic buffeting phenomena on a generic transport model was analyzed using unsteady PSP. The tests were conducted in the JAXA 2-m Transonic Wind Tunnel at M=0.85 and the model angle of attack was varied between 2.5 and 6.8 degrees. From the obtained unsteady PSP data, the RMS of pressure fluctuation was calculated to detect the areas with strong shock oscillation. Spectral analysis was also conducted in order to find frequencies of shock oscillation and their correlation with pressure fluctuation. As the angle of attack increases, the shock position moves upstream and shock oscillation becomes stronger. At 6.8 degrees, two distinct areas with strong shock oscillation were observed. The spectral analysis shows that, under buffeting conditions, shock oscillation frequencies are distributed around either of 490 Hz or 365 Hz. Noticeable effects from the PSP coating on the measured aerodynamic forces were noticed, indicating that even the small roughness of the unsteady PSP coating has an influence on the transonic buffeting phenomena. Nomenclaturet = time p = pressure M ∞ = Mach number Re = Reynolds number c = chord length c = mean aerodynamic chord length x = model stream wise location  = angle of attack I = PSP emission intensity p RMS = Root-Mean-Square of pressure fluctuation p = difference from time-averaged pressure  = wing spanwise location (non-dimensional) X(f) = Fast Fourier Transform results of  ave /I N FFT = the number of data points for FFT (=2048) f S = frame rate of the high-speed camera Coh 2 = coherence 1 Master's course student, 2 S XX , S YY = auto-spectrum of X and Y S XY = cross-spectrum between X and Y PSD = Power spectrum density Subscripts: ref = refrence condition, 100kPa ave = time-averaged

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Section: B Time-series Pressure Distributionmentioning

confidence: 99%

Unsteady PSP Measurement of Transonic Buffet on a Wing

Sugioka

Numata²,

Asai³

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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“…For PSP measurement, we use Iref after as the reference image, because this method can reduce the influence of temperature, according to [3], when the temperature distribution at the wind-on condition is preserved immediately after the tunnel is shut down. We have confirmed from TSP test results that this is the case for this wind tunnel experiment.…”

Section: Optical Setupmentioning

confidence: 99%

Development of Pressure-Sensitive Paint Technique in a Supersonic Indraft Wind Tunnel and its Application to a Busemann Biplane

Saito¹,

Nagai²,

Ogawa

et al. 2007

2007 22nd International Congress on Instrumentation in Aerospace Simulation Facilities

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Using Pressure Sensitive Paint, the pressure distributions on thin wings of the Busemann biplane model were measured in the small supersonic indraft wind tunnel. The observed phenomenon is so complicated that it is completely different from the prediction of the simple 2-D theory. Referring to Schlieren picture and CFD analysis, it is found that these complex pressure fields are caused by the shock wave generated downstream just behind the wing ridge line. The results of this experiment show that the interference between Busemann biplane wings is sensitive to a small change in flow condition. A care must be taken in a wind tunnel test to realize the design condition of Busemann biplane where the shock waves are completely cancelled with each other.

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“…From the point of view of the measurement procedure, Bell et al 8) , Mitsuo et al 7,9) , Yamashita et al 12) and Asai et al 13) reported the modification of the image acquisition procedure in PSP measurements by means of the intensity method. Especially, it is well known that a significant temperature change between reference (wind-off) -and run (wind-on) data is a major source of error.…”

Section: Introductionmentioning

confidence: 99%

Reduction of Temperature Effect in Pressure-Sensitive Paint Measurements by Model Materials and Coatings

Egami

Fujii

Takagi

et al. 2012

28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference

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Pressure-Sensitive Paint (PSP) generally changes its luminescence intensity not only with pressure but also with temperature. The effect of temperature variations on a model surface decreases the measurement accuracy of PSP. Therefore, it is important to minimize temperature variations on the surface during wind tunnel testing. In this study, we have investigated the effect of model materials and coatings on the temperature variations on a model surface. Plate models made of three different materials: aluminium alloy, stainless steel, and wood with two thicknesses: 2 and 10 mm were prepared and then coated with PSP. Temperature variations on the model surfaces heated with hot air flow was measured by means of an infrared camera. The results revealed that the magnitude of the temperature variations on the model surface strongly depends on the model material and thickness, and applied coatings. The model with a higher heat capacity showed a smaller rate of temperature change on the model surface. Moreover, the models coated with PSP showed 2-3 times higher temperature change rates than those without the coating due to the low thermal conductivity of the applied layer. To resolve this problem, a high thermal conductive PSP has been developed by mixing high thermal conductive particles. This novel PSP successfully reduced the rate of the temperature change to almost the same level as a non-coated metal model surface. omenclature A, B = Stern-Volmer constants AA = aluminum alloy As = surface area, m 2 Bi = Biot number (= hL/ λ) C = heat capacity (C V V ), J/K C V = volumetric heat capacity, kJ/(K⋅m 3 ) Fo = Fourier Number (= ‫ܮ/ݐߙ‬ ଶ ) I = luminescence intensity, counts L = plate thickness, m P = pressure, kPa R = rate of temperature increase/decrease, K/min SS = stainless steel T = temperature, K 2 V = volume, m 3 c = specific heat, J/(kg⋅K) h = convective heat transfer coefficient, W/(m 2 ⋅K) t = time, sec x = distance, m α = heat diffusivity (=λ/(cρ)), m 2 /s δ i = eigenvalue, positive root of ߜ tan ߜ = ‫݅ܤ‬ ε = heat emissivity λ = thermal conductivity, W/(m⋅K) ρ = density, kg/m 3 Subscripts 0 = initial value max = maximum ref = reference ∞ = circumstance

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Pressure-Sensitive Paint measurement of the flow around a simplified car model

Cited by 47 publications

References 9 publications

Unsteady PSP Measurement of Transonic Buffet on a Wing

Unsteady PSP Measurement of Transonic Buffet on a Wing

Development of Pressure-Sensitive Paint Technique in a Supersonic Indraft Wind Tunnel and its Application to a Busemann Biplane

Reduction of Temperature Effect in Pressure-Sensitive Paint Measurements by Model Materials and Coatings

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