NACA 2418 (naca2418-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2418 (naca2418-il) Reynolds number: 50,000 Max Cl/Cd: 8.55 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2418-il-50000.txt Download as CSV file: xf-naca2418-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2418
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3154 0.11237 0.10410 -0.0195 1.0000 0.4102
-9.250 -0.5654 0.07956 0.07157 -0.0393 1.0000 0.2507
-9.000 -0.6067 0.07477 0.06686 -0.0360 1.0000 0.2494
-8.750 -0.6563 0.06953 0.06165 -0.0321 1.0000 0.2480
-8.500 -0.7067 0.06417 0.05621 -0.0277 1.0000 0.2470
-8.250 -0.7485 0.05916 0.05099 -0.0233 1.0000 0.2475
-8.000 -0.7806 0.05452 0.04597 -0.0192 1.0000 0.2498
-7.750 -0.7682 0.05324 0.04479 -0.0171 1.0000 0.2557
-7.500 -0.7649 0.05145 0.04293 -0.0146 1.0000 0.2618
-7.250 -0.7755 0.04810 0.03914 -0.0118 1.0000 0.2678
-7.000 -0.7648 0.04660 0.03765 -0.0099 1.0000 0.2745
-6.750 -0.7550 0.04522 0.03618 -0.0079 1.0000 0.2827
-6.500 -0.7501 0.04297 0.03360 -0.0061 1.0000 0.2910
-6.250 -0.7338 0.04225 0.03299 -0.0046 1.0000 0.2999
-6.000 -0.7242 0.04044 0.03085 -0.0032 1.0000 0.3102
-5.750 -0.7073 0.03977 0.03029 -0.0018 1.0000 0.3203
-5.500 -0.6935 0.03850 0.02885 -0.0006 1.0000 0.3319
-5.250 -0.6776 0.03768 0.02798 0.0006 1.0000 0.3444
-5.000 -0.6612 0.03697 0.02731 0.0018 1.0000 0.3570
-4.750 -0.6452 0.03611 0.02634 0.0027 1.0000 0.3717
-4.500 -0.6287 0.03545 0.02557 0.0036 1.0000 0.3884
-4.250 -0.6117 0.03511 0.02540 0.0049 1.0000 0.4038
-4.000 -0.5949 0.03473 0.02509 0.0059 1.0000 0.4208
-3.750 -0.5782 0.03442 0.02484 0.0070 1.0000 0.4395
-3.500 -0.5615 0.03419 0.02466 0.0080 1.0000 0.4589
-3.250 -0.5448 0.03406 0.02460 0.0090 1.0000 0.4795
-3.000 -0.5163 0.03422 0.02483 0.0079 0.9957 0.5051
-2.750 -0.4705 0.03475 0.02545 0.0040 0.9835 0.5374
-2.500 -0.4298 0.03525 0.02605 0.0013 0.9712 0.5699
-2.250 -0.3924 0.03568 0.02662 -0.0007 0.9587 0.6024
-2.000 -0.3562 0.03609 0.02708 -0.0025 0.9467 0.6390
-1.750 -0.3175 0.03671 0.02789 -0.0038 0.9352 0.6754
-1.500 -0.2942 0.03698 0.02828 -0.0027 0.9223 0.7103
-1.250 -0.2684 0.03744 0.02885 -0.0018 0.9106 0.7498
-1.000 -0.2312 0.03820 0.02972 -0.0019 0.8998 0.7944
-0.750 -0.2124 0.03871 0.03030 0.0006 0.8872 0.8353
-0.500 -0.1617 0.03989 0.03147 -0.0021 0.8758 0.8811
-0.250 -0.0568 0.04161 0.03305 -0.0149 0.8633 0.9236
0.000 0.0628 0.04302 0.03431 -0.0322 0.8493 0.9552
0.250 0.2010 0.04348 0.03462 -0.0530 0.8369 0.9846
0.500 0.2907 0.04310 0.03416 -0.0660 0.8249 1.0000
0.750 0.2716 0.04344 0.03443 -0.0611 0.8106 1.0000
1.000 0.2894 0.04332 0.03422 -0.0612 0.7999 1.0000
1.250 0.2746 0.04368 0.03451 -0.0565 0.7867 1.0000
1.500 0.2572 0.04422 0.03498 -0.0512 0.7742 1.0000
1.750 0.2915 0.04422 0.03489 -0.0526 0.7642 1.0000
2.000 0.2615 0.04528 0.03585 -0.0455 0.7507 1.0000
2.250 0.2947 0.04556 0.03604 -0.0465 0.7404 1.0000
2.500 0.2893 0.04654 0.03694 -0.0426 0.7275 1.0000
2.750 0.2966 0.04749 0.03780 -0.0404 0.7154 1.0000
3.000 0.3356 0.04769 0.03795 -0.0417 0.7044 1.0000
3.250 0.3254 0.04928 0.03948 -0.0377 0.6908 1.0000
3.500 0.3746 0.04922 0.03938 -0.0398 0.6807 1.0000
3.750 0.3687 0.05089 0.04099 -0.0366 0.6669 1.0000
4.000 0.3784 0.05224 0.04231 -0.0350 0.6546 1.0000
4.250 0.4202 0.05230 0.04235 -0.0360 0.6439 1.0000
4.500 0.4091 0.05465 0.04467 -0.0330 0.6302 1.0000
4.750 0.4556 0.05451 0.04453 -0.0342 0.6204 1.0000
5.000 0.4493 0.05684 0.04684 -0.0318 0.6068 1.0000
5.250 0.4548 0.05880 0.04879 -0.0303 0.5946 1.0000
5.500 0.4972 0.05869 0.04870 -0.0308 0.5842 1.0000
5.750 0.4786 0.06219 0.05218 -0.0284 0.5709 1.0000
6.000 0.5275 0.06167 0.05168 -0.0290 0.5611 1.0000
6.250 0.5078 0.06549 0.05550 -0.0270 0.5481 1.0000
6.500 0.5179 0.06752 0.05754 -0.0261 0.5368 1.0000
6.750 0.5421 0.06855 0.05860 -0.0257 0.5258 1.0000
7.000 0.5288 0.07237 0.06242 -0.0245 0.5145 1.0000
7.250 0.5850 0.07096 0.06105 -0.0244 0.5037 1.0000
7.500 0.5428 0.07720 0.06728 -0.0232 0.4928 1.0000
7.750 0.5920 0.07628 0.06641 -0.0227 0.4813 1.0000
8.000 0.5585 0.08204 0.07217 -0.0221 0.4713 1.0000
8.250 0.5861 0.08287 0.07303 -0.0214 0.4598 1.0000
8.500 0.5758 0.08689 0.07708 -0.0212 0.4500 1.0000
8.750 0.5889 0.08901 0.07923 -0.0206 0.4391 1.0000
9.000 0.5926 0.09197 0.08224 -0.0204 0.4292 1.0000
9.250 0.5944 0.09524 0.08553 -0.0202 0.4195 1.0000
9.500 0.5996 0.09823 0.08856 -0.0201 0.4102 1.0000
9.750 0.6016 0.10165 0.09200 -0.0201 0.4012 1.0000
10.000 0.5897 0.10648 0.09687 -0.0208 0.3953 1.0000
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Polar data table (+)
Polar graphs
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