An experimental program was generated by the Icing Technology Branch at NASA Lewis Research Center to validate two ice protection simulation codes: LEWICE/Thermal for transient electrothermal de-icing and anti-icing simulations, and ANTICE for steady state hot gas and electrothermal anti-icing simulations. An electrothermal ice protection system was designed and constructed integral to a 36 inch chord NACA0012 airfoil. The model was fully instrumented with thermocouples, RTD's, and heat flux gages. Tests were conducted at several icing environmental conditions during a two week period at the NASA Lewis Icing Research Tunnel. Experimental results of running-wet and evaporative cases were compared to the ANTICE computer code predictions and are presented in this paper. Nomenclature AOA = angle of attack of body with the freestream air (degrees) Cpw = specific heat (Btu/lbm.°F) h = heat transfer coefficient between the dry surface and the ambient air (Btu/hr.ft .°F) h, = film coefficient between the wet surface and the ambient air (Btu/hr.ft.°F) K = thermal conductivity (Btu/hr.ft.°F) LWC = liquid water content in the freestream (g/m) Lv = water latent heat of vaporization (Btu/lbm) MVD = mean volume droplet diameter in cloud *Engineering Scientist, Member AIAA **De-icing Systems Engineer Microspace Engineer, Member AIAA 'Aerospace Engineer, Member AIAA Copyright © 1997 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Hconv Havap (urn) m = surface runback mass flow rate per unit span distance (Ibm/ft.hr) evaP = rate °f surface water evaporation (Ibm/hr.ft) mimp = rate of water droplets impingement (Ibm/hr.ft) q = neater power density (W/in) = convective heat loss (W/in) = evaporative heat loss (W/in) qKE = kinetic heat gain from droplets impact on surface (W/in) Psans sensible heat required to warm the impinging water droplets (W/in ) S = surface distance from stagnation, positive on the upper surface (in) Taw = adiabatic wall temperature (°F) Ts = skin temperature (°F) Ttot = total ambient temperature (°F) T~ = static ambient temperature (°F) V freestream velocity (mph) (3 = droplets collection efficiency p = mass density (Ibm/ft) 1 American Institute of Aeronautics and Astronautics
[1]
T. Keith,et al.
Further development of an anti-icing runback model
,
1991
.
[2]
Robert Henry.
Étude du fonctionnement d'un dégivreur électrique : modélisation et mesure en soufflerie givrante de température pariétale par thermographie infrarouge
,
1989
.
[3]
Theo G. Keith,et al.
Thermal analysis of engine inlet anti-icing systems
,
1989
.
[4]
Theo G. Keith,et al.
Numerical analysis of a thermal deicer
,
1992
.
[5]
Theo G. Keith,et al.
Transient two-dimensional heat transfer through a composite body with application to deicing of aircraft components
,
1988
.
[6]
Kenneth J. Witt,et al.
Development of an improved model for runback water on aircraft surfaces
,
1994
.
[7]
Gary A. Ruff,et al.
Users Manual for the NASA Lewis Ice Accretion Prediction Code (LEWICE)
,
1990
.
[8]
William B. Wright,et al.
Additional improvements to the NASA Lewis ice accretion code LEWICE
,
1995
.
[9]
Kamel Al-Khalil,et al.
Validation of NASA Thermal Ice Protection Computer Codes Part 2 - LEWICE/Thermal
,
1997
.
[10]
Howard Broughton,et al.
Validation of NASA thermal ice protection computer codes. I - Program overview
,
1997
.
[11]
William B. Wright,et al.
Users manual for the improved NASA Lewis ice accretion code LEWICE 1.6
,
1995
.