Ice-Accretion Test Results for Three Large-Scale Swept-Wing Models in the NASA Icing Research Tunnel

Icing simulation tools and computational fluid dynamics codes are reaching levels of maturity such that they are being proposed by manufacturers for use in certification of aircraft for flight in icing conditions with increasingly less reliance on natural-icing flight testing and icing-wind-tunnel testing. Sufficient high-quality data to evaluate the performance of these tools is not currently available. The objective of this work was to generate a database of ice-accretion geometry that can be used for development and validation of icing simulation tools as well as for aerodynamic testing. Three large-scale swept wing models were built and tested at the NASA Glenn Icing Research Tunnel (IRT). The models represented the Inboard (20 percent semispan), Midspan (64 percent semispan) and Outboard stations (83 percent semispan) of a wing based upon a 65 percent scale version of the Common Research Model (CRM). The IRT models utilized a hybrid design that maintained the full-scale leading-edge geometry with a truncated afterbody and flap. The models were instrumented with surface pressure taps in order to acquire sufficient aerodynamic data to verify the hybrid model design capability to simulate the full-scale wing section. A series of ice-accretion tests were conducted over a range of total temperatures from -23.8 to -1.4 C with all other conditions held constant. The results showed the changing ice-accretion morphology from rime ice at the colder temperatures to highly 3-D scallop ice in the range of -11.2 to -6.3 C. Warmer temperatures generated highly 3-D ice accretion with glaze ice characteristics. The results indicated that the general scallop ice morphology was similar for all three models. Icing results were documented for limited parametric variations in angle of attack, drop size and cloud liquid-water content (LWC). The effect of velocity on ice accretion was documented for the Midspan and Outboard models for a limited number of test cases. The data suggest that there are morphological characteristics of glaze and scallop ice accretion on these swept-wing models that are dependent upon the velocity. This work has resulted in a large database of ice-accretion geometry on large-scale, swept-wing models.

[1]  Sam Lee,et al.  Evaluation of Icing Scaling on Swept NACA 0012 Airfoil Models , 2011 .

[2]  Sam Lee,et al.  Development of 3D Ice Accretion Measurement Method , 2012 .

[3]  Philippe Villedieu,et al.  Swept-Wing Ice Accretion Characterization and Aerodynamics , 2013 .

[4]  David N. Anderson,et al.  Manual of Scaling Methods , 2004 .

[5]  Michael B. Bragg,et al.  A Hybrid Airfoil Design Method for Icing Wind Tunnel Tests , 2013 .

[6]  Emmanuel Montreuil,et al.  Experimental and Numerical Study of Scallop Ice on Swept Cylinder , 2009 .

[7]  Michael B. Bragg,et al.  Large-Scale Swept-Wing Icing Simulations in the NASA Glenn Icing Research Tunnel Using LEWICE3D , 2014 .

[8]  E. Lozowski,et al.  Progress towards a 3D Numerical Simulation of Ice Accretion on a Swept Wing using the Morphogenetic Approach , 2015 .

[9]  Mario Vargas,et al.  Parametric Experimental Study of the Formation of Glaze Ice Shapes on Swept Wings , 1999 .

[10]  Farooq Saeed,et al.  Hybrid airfoil design method to simulate full-scale ice accretion throughout a given α range , 1998 .

[11]  Sam Lee,et al.  Validation of 3-D Ice Accretion Measurement Methodology for Experimental Aerodynamic Simulation , 2014 .

[12]  Wagdi G. Habashi,et al.  FENSAP-ICE's Three-Dimensional In-Flight Ice Accretion Module: ICE3D , 2003 .

[13]  Farooq Saeed,et al.  Design of Subscale Airfoils with Full-Scale Leading Edges for Ice Accretion Testing , 1997 .

[14]  Andrew Mortonson.  Use of hybrid airfoil design in icing wind tunnel tests of large scale swept wings , 2012 .

[15]  Mario Vargas,et al.  LEWICE Modeling of Swept Wing Ice Accretions , 2003 .

[16]  S. Mcilwain,et al.  Numerical Simulation of Complex Ice Shapes on Swept Wings , 2006 .

[17]  Judith F. Van Zante,et al.  NASA Glenn Icing Research Tunnel: 2014 and 2015 Cloud Calibration Procedures and Results , 2015 .

[18]  Mario Vargas.  Current Experimental Basis for Modeling Ice Accretions on Swept Wings , 2013 .

[19]  Mario Vargas,et al.  Physical Mechanisms of Glaze Ice Scallop Formations on Swept Wings , 1998 .

[20]  Philippe Villedieu,et al.  SLD Lagrangian modeling and capability assessment in the frame of ONERA 3D icing suite , 2012 .

[21]  Melissa B. Rivers,et al.  Experimental Investigations of the NASA Common Research Model (Invited) , 2010 .

[22]  Melissa B. Rivers,et al.  Experimental Investigation of the NASA Common Research Model , 2014 .

[23]  Edward N. Tinoco,et al.  Summary of the Fourth AIAA CFD Drag Prediction Workshop , 2010 .

[24]  Brock Wiberg.  Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D , 2014 .

[25]  Christopher W. Lum,et al.  Computational and Experimental Ice Accretions of Large Swept Wings in the Icing Research Tunnel , 2016 .

[26]  Michael B. Bragg,et al.  3D swept hybrid wing design method for icing wind tunnel tests , 2013, EMBC 2013.

[27]  Mario Vargas,et al.  Measurement of the Critical Distance Parameter Against Icing Conditions on a NACA 0012 Swept Wing Tip , 2009 .

[28]  Wagdi G. Habashi,et al.  Toward Real-Time Aero-Icing Simulation of Complete Aircraft via FENSAP-ICE , 2010 .

[29]  Thomas P. Ratvasky,et al.  Ice Accretion Formations on a NACA 0012 Swept Wing Tip in Natural Icing Conditions , 2002 .

[30]  T. Hedde,et al.  Improvement of the ONERA 3D icing code, comparison with 3D experimental shapes , 1993 .

[31]  Mario Vargas,et al.  Time-Sequence Observations of the Formation of Ice Accretions on Swept Wings , 2008 .

[32]  C. S. Bidwell,et al.  Numerical simulation of ice growth on a MS-317 swept wing geometry , 1991 .

[33]  Farooq Saeed,et al.  Hybrid Airfoil Design Procedure Validation for Full-Scale Ice Accretion Simulation , 1999 .

[34]  William Gropp,et al.  CFD Vision 2030 Study: A Path to Revolutionary Computational Aerosciences , 2014 .

[35]  Stanley R. Mohler,et al.  COLLECTION EFFICIENCY AND ICE ACCRETION CALCULATIONS FOR A SPHERE, A SWEPT MS(1)-317 WING, A SWEPT NACA-0012 WING TIP, AN AXISYMMETRIC INLET, AND A BOEING 737-300 INLET. , 1995 .

[36]  Gustavo Camarinha Fujiwara.  Design of 3D swept wing hybrid models for icing wind tunnel tests , 2015 .

[37]  Didier Guffond,et al.  Experimental Study of the Scallop Formation on Swept Cylinder , 2007 .

[38]  Mario Vargas,et al.  LWC and Temperature Effects on Ice Accretion Formation on Swept Wings at Glaze Ice Conditions , 2000 .

[39]  Melissa B. Rivers,et al.  Experimental Investigations of the NASA Common Research Model in the NASA Langley National Transonic Facility and NASA Ames 11-Ft Transonic Wind Tunnel (Invited) , 2011 .

[40]  Colin S. Bidwell.  Icing Analysis of a Swept NACA 0012 Wing Using LEWICE3D Version 3.48 , 2014 .

[41]  Mario Vargas,et al.  Ice Accretions on a Swept GLC-305 Airfoil , 2002 .

[42]  John C. Vassberg,et al.  Development of a Common Research Model for Applied CFD Validation Studies , 2008 .

[43]  Jen-Ching Tsao.  Cross Flow Effects on Glaze Ice Roughness Formation , 2013 .

[44]  John C. Vassberg,et al.  Extended OVERFLOW Analysis of the NASA Trap Wing Wind Tunnel Model , 2012 .

[45]  T. Hedde,et al.  Development of a three-dimensional icing code - Comparison with experimental shapes , 1992 .

[46]  Mark G. Potapczuk,et al.  Swept wing ice accretion modeling , 1990 .

[47]  Andy P. Broeren,et al.  Implementation and Validation of 3-D Ice Accretion Measurement Methodology , 2014 .