scholarly journals Ice accretion formations on a NACA 0012 swept wing tip in natural icing conditions

2002 ◽  
Author(s):  
M. Vargas ◽  
T. Ratvasky ◽  
J. Giriunas
Keyword(s):  
Ice Accretion ◽  
Swept Wing ◽  
Naca 0012 ◽  
Wing Tip

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

2016 ◽  
Author(s):  
Andy P. Broeren ◽  
Mark G. Potapczuk ◽  
Sam Lee ◽  
Adam M. Malone ◽  
Bernard P. Paul ◽  
...  
Keyword(s):  
Large Scale ◽  
Ice Accretion ◽  
Test Results ◽  
Swept Wing

scholarly journals Aerodynamic Classification of Swept-Wing Ice Accretion

2013 ◽  
Author(s):  
Jeffrey M. Diebold ◽  
Andy P. Broeren ◽  
Michael Bragg
Keyword(s):  
Ice Accretion ◽  
Swept Wing

Effect of Geometric Fidelity on the Aerodynamics of a Swept Wing with Scalloped Ice Accretion

2020 ◽  
Author(s):  
Sam Lee ◽  
Andy P. Broeren ◽  
Brian S. Woodard ◽  
Michael B. Bragg
Keyword(s):  
Ice Accretion ◽  
Swept Wing

scholarly journals Numerical Simulation of the Anti-Icing Performance of Electric Heaters for Icing on the NACA 0012 Airfoil

Aerospace ◽  
2020 ◽  
Vol 7 (9) ◽  
pp. 123
Author(s):  
Sho Uranai ◽  
Koji Fukudome ◽  
Hiroya Mamori ◽  
Naoya Fukushima ◽  
Makoto Yamamoto
Keyword(s):  
Numerical Simulation ◽  
Lift Coefficient ◽  
Heating Surface ◽  
Leading Edge ◽  
Simulation Method ◽  
Chord Length ◽  
Ice Accretion ◽  
Suction Surface ◽  
Edge Surface ◽  
Naca 0012

Ice accretion is a phenomenon whereby super-cooled water droplets impinge and accrete on wall surfaces. It is well known that the icing may cause severe accidents via the deformation of airfoil shape and the shedding of the growing adhered ice. To prevent ice accretion, electro-thermal heaters have recently been implemented as a de- and anti-icing device for aircraft wings. In this study, an icing simulation method for a two-dimensional airfoil with a heating surface was developed by modifying the extended Messinger model. The main modification is the computation of heat transfer from the airfoil wall and the run-back water temperature achieved by the heater. A numerical simulation is conducted based on an Euler–Lagrange method: a flow field around the airfoil is computed by an Eulerian method and droplet trajectories are computed by a Lagrangian method. The wall temperature distribution was validated by experiment. The results of the numerical and practical experiments were in reasonable agreement. The ice shape and aerodynamic performance of a NACA 0012 airfoil with a heater on the leading-edge surface were computed. The heating area changed from 1% to 10% of the chord length with a four-degree angle of attack. The simulation results reveal that the lift coefficient varies significantly with the heating area: when the heating area was 1.0% of the chord length, the lift coefficient was improved by up to 15%, owing to the flow separation instigated by the ice edge; increasing the heating area, the lift coefficient deteriorated, because the suction peak on the suction surface was attenuated by the ice formed. When the heating area exceeded 4.0% of the chord length, the lift coefficient recovered by up to 4%, because the large ice near the heater vanished. In contrast, the drag coefficient gradually decreased as the heating area increased. The present simulation method using the modified extended Messinger model is more suitable for de-icing simulations of both rime and glaze ice conditions, because it reproduces the thin ice layer formed behind the heater due to the runback phenomenon.

Ice Accretion Prediction for Single Airfoil and Multi-Element Airfoil

2011 ◽  
Vol 138-139 ◽  
pp. 140-145
Author(s):  
Zhi Guo Sun ◽  
Cheng Xiang Zhu ◽  
Chun Ling Zhu
Keyword(s):  
Leading Edge ◽  
Ice Accretion ◽  
Runge Kutta Method ◽  
Wide Range ◽  
Ice Accretions ◽  
Airflow Field ◽  
Grid Technique ◽  
Droplet Trajectory ◽  
Naca 0012 ◽  
Methods Numerical

Ice accretion on aircraft components is an enormous threat to flight safety. In this paper, ice accretions on the leading edge of the NACA 0012 airfoil and the NLR 7301 multi-element airfoil with flap are predicted using the icing code developed by us. This code mainly contains five modules which are grid module, airflow module, droplet module, heat module, and boundary reconstruction module. The effectiveness and robustness of this code are tested by executing the five modules orderly and repeatedly. The Spalart-Allmaras one-equation turbulence model is adopt to calculate the viscous airflow field and the four-order Runge-Kutta method is used to solve the droplet trajectory equations. In order to enhance the efficiency of the icing calculations, the multi-block grid technique is integrated into the grid module. Based on the above methods, numerical results in both two cases are presented and the necessary comparisons with the experimental data are given in corresponding chapters. The computational results show that performance of the icing code is very good for the wide range of icing conditions.

scholarly journals Swept wing ice accretion modeling

1990 ◽  
Author(s):  
M. POTAPCZUK ◽  
C. BIDWELL
Keyword(s):  
Ice Accretion ◽  
Swept Wing
Sign in / Sign up

Export Citation Format

Share Document