This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Further Application of the Mass Loss Model to the GLC-305 and MS(1)-317 Airfoils
Technical Paper
2004-01-1816
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
A model to simulate the mass loss due to splashing by large droplets impinging on an airfoil surface has been developed and successful validated for a single airfoil1: MS(1)-317 at angle of attack (AOA) of 0°. The published results on the comparison between experimental and predicted droplet impingement efficiency values have shown good agreement. Droplet impingement characteristic is essential for simulating ice shapes. Although current icing codes can predict ice buildup for Appendix C droplet sizes with acceptable degree of accuracy, they were less successful with supercooled large droplets (SLD) due to the droplet splashing effects. The proposed mass loss model accounts for this effect by including a splash parameter term into the computation of the droplet impingement efficiency. This parameter is a function of the droplet median volume diameter (MVD) and impact parameter (K), which is related to the droplet impact velocity (and angle). This paper presents further application of this mass loss model to the MS(1)-317 airfoil at AOA of 8°, and the GLC-305 airfoil at AOA of 1.5°.
Topic
Citation
Tan, S., "Further Application of the Mass Loss Model to the GLC-305 and MS(1)-317 Airfoils," SAE Technical Paper 2004-01-1816, 2004, https://doi.org/10.4271/2004-01-1816.Also In
References
- Tan, S.C. A Tentative Mass Loss Model for Simulating Water Droplet Splash Reno January 2004
- Papadakis, M. Yeong, H. Aerodynamic Performance of Swept Wing with Ice Accretions Reno January 2003
- Lu Bioa Bragg, M. Airfoil Drag Measurement with Simulated Leading Edge Ice using the Wake-Survey Method Reno January 2003
- Potapczuk, M.G. Al-Khalil, M.K. Velazquez, M.T. Ice Accretion and Performance Degradation Calculations with LEWICE/NS Reno January 1993
- Papadakis, M. Rachman, A. Wong, S.C. Bidwell, C. Bencic, T. An Experimental Investigation of SLD Impingement On Airfoils And Simulated Ice Shape Chicago June 2003
- Rutkowski, A. Wright, B. Potapczuk, M. Numerical Study of Droplet Splashing and Re-Impingement Reno January 2003
- Potapczuk, M. Ice mass measurements: Implications for the ice accretion process Reno January 2003
- Chr Mundo Sommerfeld, M. Tropea, C. Droplet-Wall Collisions: Experimental Studies of The Deformation And Breakup Process Int. J. Multiphase Flow 21 2 151 173 1995
- Tan, S.C. Bartlett, P.G. An Experimental Study Of Droplet Breakup Using A Wind Tunnel Reno January 2003
- Bai ChengXin Gosman, A.D. Development of Methodology For Spray Impingement Simulation SAE Technical paper series 950283 International Congress and exposition Detroit, Michigan Feb. 27 Mar. 2 1995
- Trujillo, M.F. Matthews, W.S. Lee, C.F. Peters, J.E. Modeling and Experiment of Impingement and Atomization of a Liquid Spray on a Wall Int. J. Engine Research 1 1
- Gent, R.W. Ford, J.M. Moser, R.J. Results From SLD Mass Loss Tests In The ACT Luton Icing Wind Tunnel Reno Jan. 2003
- Wright, B.W. Potapczuk, M. Semi-Empirical Modeling of SLD Physics Reno Jan. 2004
- Mohler, S.R. Bidwell, C. Comparison of Two-dimensional and Three-dimensional Droplet Trajectory Calculations in the Vicinity of Finite Wing Reno Jan. 1992
- Gent, R.W. Calculation of Water Droplet Trajectories about an Airfoil in Steady Two-Dimensional Compressible Flow June 1984
- Bourgault Y. Habashi W. G. Dompierre J. Boutanios Z. Di Bartolomeo W. An Eulerian Approach to Supercooled Droplets Impingement Calculations Reno Jan. 1997
- Wirogo, S. Srirambhatia AN Eulerian Method to calculate the Collection Efficiency on Two and Three-Dimensional Bodies Reno Jan. 2003
- Papadakis, M. Hung, K.E. Vu, G.T. Yeong, H.W. Bidwell, C. Breer, M. Bencic, T.J. Experimental Investigation Of Water Droplet Impingement On Airfoils, Finite Wings, And An S-Duct Engine Inlet Oct. 2002
- Wright, B.W. Users Manual for the Improved NASA Lewis Ice Accretion Code LEWICE 1.6 June 1995