Integrating CFD and Experiment in Aerodynamics - CFD4Aircraft

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Oscillating model α 0 U ∞ Optical head t u v Measuring volume n y min = 0,2 mm Optical fibres Beamexpander turntable y max = 145 mm 45deg mirror Figure 2: ELDV measurements linked with the oscillating frame model
000000000 MEASUREM ENT S MEASUREM ENTS CH 1 CH 2 465 B OSCIL LOSCOP VOLT E S:DIV VOLT S:DIV SETU P SETU P A and B TIME/D IV and D EL AY TIM E SETT INGS BSA enhan ced SETT ING S BSA enhan ced TRIGGER POW ER A TR IGGER SHIFT ENTER SHIFT ENTER Laser source 000000000 Transmitin g block Optical head U V positio nsensor PM1 Optical fibers PM2 Oscillosco p 1 3.95 3.00 4.00 64 10.67 7 8 9 4 5 6 1 2 3 0 . +/- Color separator DANTEC 9.318 1.00 1560 8 0 1 3.9 5 3.00 4.00 10.6 7 64 7 8 9 4 5 6 1 2 3 0 . +/- Postprocessing: Macintos hLabview IEE E DANTE C 9.31 8 1.0 0 1560 8 0 BSA (Burst Spectrum Analyser) Figure 3: ELDV Acquisition chain
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Integrating CFD and Experiment in A
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Experimentalist’s requirements fo
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persistent discrepancy may be due t
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numbers significantly lower than th
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Heat flux measurements. Over the pa
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The measurements are made on select
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advantage that the signal is emitte
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12. Mébarki, Y. and Mérienne, M.
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castellated nozzles entrained more
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Axisymmetric Regular Convergent Div
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Figure 5: Typical instantaneous PIV
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Figure 8: Streamwise Velocity Profi
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1.25 CFD (SKW PRESTO) Experimental
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5 Conclusions In this paper we have
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2 which include boundary layer and
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4 not received much attention in th
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6 Although a great deal of effort h
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8 Computational simulations can con
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10 separation location over rounded
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12 3.7 Vortex / flexible wing inter
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14 [8] Mitchell, A.M. and Molton, P
Page 43 and 44: 16 [31] Gursul, I., Proposed Mechan
Page 45 and 46: 18 Figure 3: Spectrum of unsteady f
Page 47 and 48: 20 Figure 7: Flow visualisation of
Page 49 and 50: Figure 11: Upper surface pressure d
Page 51 and 52: While the information presented in
Page 53 and 54: Figure 3 : DFR against Flap angle f
Page 55 and 56: Figure 7 shows a series of plots of
Page 57 and 58: Figure 9 : Contours of Mach number,
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Page 71 and 72: yaw angle. Also, extreme value coef
Page 73 and 74: 0.9 Cs vs yaw angle Side force coef
Page 75 and 76: Fig. 5. Grid block structure around
Page 77 and 78: Cs comparison at V=0.6 m/s Fig. 10.
Page 79 and 80: Investigation of Flow Turning in a
Page 81 and 82: duct as it approaches the blocker c
Page 83 and 84: Figure 1. Natural Blockage Thrust R
Page 85 and 86: Figure 7. Post-Exit rake Total Span
Page 87 and 88: Figure 11. Comparison of Static Pre
Page 89 and 90: 2.2 Data Aquired The Embedded Laser
Page 91 and 92: First, plots of the turbulent Reyno
Page 93: Particles seeding tube 3 m 1 m mode
Page 97 and 98: Figure 5: Influence of the pseudo t
Page 99 and 100: Figure 7: Turbulent Reynolds' numbe
Page 101 and 102: Figure 9: Turbulent Reynolds' numbe
Page 103 and 104: Figure 11: Vortex Shedding cycle fo
Page 105 and 106: Figure 13: Comparison with experime
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