Integrating CFD and Experiment in Aerodynamics - CFD4Aircraft

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Conclusion The experiment successfully models the qualitative aspects of the flow through the reverser in terms of efflux deflection angle and pressure distributions. However the nozzle pressure ratio range for the experiments is set too low for quantitative data collection. It is suggested that the tunnel velocity is increased to rectify the problem. The preliminary CFD results highlight the problems of attempting to computationally model in 2D a flow which is highly 3D in nature. Generating a 3D computational model would reduce the need to make artificial alterations to correctly simulate the three-dimensional effects in the thrust reverser. This could potentially offset the inherent added complexity and computation time of such a model. Bibliography 1. Yetter, J.A., Why do airlines want and use thrust reversers? - A compilation of airline industry responses to a survey regarding the use of thrust reversers on commercial transport airplanes, NASA TM-109158, January 1995 2. Short Brothers PLC (GB), Aircraft Propulsive Power Unit Thrust Reverser with Separation Delay Means, UK patent no. GB231481, November 2000. 3. Ower, E. and Pankhurst, R.C., The Measurement of Air Flow, Pergamon Press, Oxford, 1966. 4. Poland, D.T., Aerodynamics of Thrust Reversers for High Bypass Turbofans, AIAA paper 67-418, July 1967. 5. Romine, B.M. and Johnson, W.A., Performance Investigation of a Fan Thrust Reverser for a High Bypass Turbofan Engine, AIAA-84-1178, AIAA/SAE/ASME 20 th Joint Propulsion Conference, Cincinnati, OH., June 11- 13, 1984. 6. Thompson, J.D., Thrust Reverser Effectiveness on High Bypass Ratio Fan Powerplant Installations, SAE Paper, Ref. 660736, October 1966.
Figure 1. Natural Blockage Thrust Reverser Figure 2. The Experimental Model Figure 3. Positions of Static Ports and the Traverse of the External Pressure Rake.
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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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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
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Page 77 and 78: Cs comparison at V=0.6 m/s Fig. 10.
Page 79 and 80: Investigation of Flow Turning in a
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Page 85 and 86: Figure 7. Post-Exit rake Total Span
Page 87 and 88: Figure 11. Comparison of Static Pre
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Page 91 and 92: First, plots of the turbulent Reyno
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Page 99 and 100: Figure 7: Turbulent Reynolds' numbe
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Page 103 and 104: Figure 11: Vortex Shedding cycle fo
Page 105 and 106: Figure 13: Comparison with experime
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