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Boundary Layer and Heat Transfer Characterization on a Flat Plate with Realistic Ice Roughness
ISSN: 0148-7191, e-ISSN: 2688-3627
Published June 15, 2015 by SAE International in United States
Annotation ability available
Numerical simulation of ice accretion on aircraft surfaces necessitates a good prediction of wall friction coefficient and wall heat transfer coefficient. After the icing process begins, surface roughness induces a high increase of friction and heat transfer, but simple Reynolds analogy is no longer valid. An experimental campaign is conducted to provide a database for numerical model development in the simple configuration of a heated flat plate under turbulent cold airflow conditions.
The flat plate model is placed in the centre of the test section of a wind tunnel. The test model is designed according to constraints for the identification of friction and heat transfer coefficients. It includes three identical resin plates which are moulded to obtain a specified roughness on the upper surface exposed to the flow. Only the 3rd resin plate is heated on its lower face by an electrical heater connected to a temperature regulator. The evaluation of the friction coefficient is based on velocity profile measurements by laser Doppler Velocimetry. A methodology for heat transfer coefficient identification is defined. It is based on the surface temperature measurement by infrared thermography during thermal transient conditions. The heat flux at the wall is calculated by a thermal numerical model of the resin plate.
The experimental campaign begins with validation of the experimental methodologies with the smooth flat plate. The experimental results are compared to reference numerical results and exhibit very good agreement in terms of friction and heat transfer coefficients. From the three test models with roughness, two models are tested under zero pressure gradient flow. In these test conditions, the measurements show an increase of the friction coefficient by a factor 2.0 and 1.9 respectively for models nr. 2 and nr. 3. On the other hand the heat transfer is identical for these 2 models and increases by a factor 1.8.
CitationReulet, P., Aupoix, B., Donjat, D., and Micheli, F., "Boundary Layer and Heat Transfer Characterization on a Flat Plate with Realistic Ice Roughness," SAE Technical Paper 2015-01-2096, 2015, https://doi.org/10.4271/2015-01-2096.
- Ligrani P.M., Moffat. R.J., “Structure of Transitionally Rough and Fully Rough Turbulent Boundary Layers”, Journal of Fluid Mechanics, vol. 162, pp. 69-98, 1986.
- Hosni M.H., Coleman H.W., Taylor R.P., “Measurements and Calculation of Rough-Wall Heat Transfer in the Turbulent Boundary Layer”, International Journal of Heat and Mass Transfer, vol. 34, n°4/5, pp. 1067-1082, 1991.
- Hosni M.H., Coleman H.W., Gardner J.W., Taylor R.P., “Roughness Element Shape Effects on Heat Transfer and Skin Friction in Rough-Wall Turbulent Boundary Layer”, International Journal of Heat and Mass Transfer, vol. 36, n°1, pp. 147-153, 1993.
- Grabow R.M., White C.O., “Surface roughness effects on nosetip ablation characteritics”, AIAA Journal, vol. 13, n°5, pp. 605-609, 1975.
- Anderson D.N., Hentschel D.B., Ruff G.A., “Measurement and Correlation of Ice Accretion Roughness”, NASA CR-2003-211823, 1998.
- Tecson L., McClain S.T., “Modeling of Realistic Ice Roughness Element Distributions to Characterize Convective Heat Transfer”, AIAA 2013-3059, 5th AIAA Atmospheric and Space Environments Conference, 24-27 Juin 2013, San Diego, CA.
- Flack K.A., Schultz M.P., “Review of Hydraulic Roughness Scales in the Fully Rough Regime”, Journal of Fluid Engineering, vol. 132, 2010.
- Lee S., Broeren A.P., Kreeger R.E., Potapczuk M., “Implementation and Validation of 3-D Ice Accretion Measurement Methodology”, AIAA 2014-2613, 6th AIAA Atmospheric and Space Environments Conference, 16-20 Juin 2014, Atlanta, GA.
- Broeren A.P., Addy H.E., Lee S., Monastero M.C., “Validation of 3-D Ice Accretion Measurement Methodology for Experimental Aerodynamic Simulation”, AIAA 2014-2614, 6th AIAA Atmospheric and Space Environments Conference, 16-20 Juin 2014, Atlanta, GA.
- Aupoix B., “Couches Limites Bidimensionnelles Compressibles. Descriptif et mode d'emploi du code CLICET - Version 2010”, Rapport Technique Onera RT-1/17015 DMAE, Oct. 2010.
- Coleman H., Hodge B., Taylor R., “Generalized roughness effects on turbulent boundary layer heat transfer - A discrete element predictive approach for turbulent flow over rough surfaces”, Air Force Armament Laboratory AFATL-TR-83-90, Mississippi State University, 1983.
- Bons J., “St and Cf augmentation for real turbine roughness with elevated freestream turbulence”, Journal of Turbomachinery, vol. 124, pp. 632-644, 2002.