Page 46 - Computational Fluid Dynamics for Engineers

1.4 Prediction of Aircraft Performance Degradation Due to Icing 31

0.04
0.04

0.02 k
0.02
y / c o.oo h y/c o.oo

-0.02 -0.02

-0.04 _i . i_
-0.04 -0.04 -0.02 0.00 0.02 0.04
-0.04 -0.02 0.00 0.02 0.04
x/c
(a) x/c (b)
0.04 r 0.04

0.02

y/c o.oo

-0.02

-0.04 -0.04
-0.04 -0.02 0.00 0.02 0.04 -0.04 -0.02 0.00 0.02 0.04
x/c x/c

y/c o.oo y/c o.ooo

-0.02 -0.020

-0.04 -0.040
-0.04 -0.02 0.00 0.02 0.04 -0.040 -0.020 0.000 0.020 0.040
(e) x/c (f) * G
Fig. 1.31. Comparison of computed ice (solid lines) and experimental ice (dashed lines)
shapes for mixed ice: (a) wing, flight 85-24a, (b) tail, flight 84-24a, (c) wing, flight 85-24b,
(d) tail, flight 85-24b, (e) wing, flight 84-34, and (f) wing, flight 84-29.