NACA 2418 (naca2418-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2418 (naca2418-il) Reynolds number: 200,000 Max Cl/Cd: 60.78 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2418-il-200000.txt Download as CSV file: xf-naca2418-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9287 0.07528 0.06988 -0.0740 1.0000 0.0698
-16.250 -0.9766 0.06602 0.06030 -0.0793 1.0000 0.0698
-16.000 -1.0030 0.06020 0.05425 -0.0820 1.0000 0.0702
-15.750 -1.0225 0.05559 0.04941 -0.0836 1.0000 0.0707
-15.500 -1.0393 0.05167 0.04526 -0.0843 1.0000 0.0714
-15.250 -1.0550 0.04827 0.04161 -0.0843 1.0000 0.0720
-15.000 -1.0705 0.04537 0.03845 -0.0833 1.0000 0.0726
-14.750 -1.0639 0.04350 0.03656 -0.0825 1.0000 0.0737
-14.500 -1.0510 0.04235 0.03547 -0.0816 1.0000 0.0748
-14.250 -1.0468 0.04095 0.03403 -0.0802 1.0000 0.0759
-14.000 -1.0474 0.03946 0.03244 -0.0782 1.0000 0.0769
-13.750 -1.0510 0.03802 0.03088 -0.0755 1.0000 0.0780
-13.500 -1.0576 0.03674 0.02944 -0.0719 1.0000 0.0791
-13.250 -1.0689 0.03570 0.02822 -0.0670 1.0000 0.0800
-13.000 -1.0628 0.03457 0.02711 -0.0643 1.0000 0.0813
-12.750 -1.0591 0.03390 0.02650 -0.0609 1.0000 0.0825
-12.500 -1.0617 0.03331 0.02591 -0.0565 1.0000 0.0838
-12.250 -1.0631 0.03262 0.02516 -0.0523 1.0000 0.0853
-12.000 -1.0657 0.03188 0.02428 -0.0479 1.0000 0.0870
-11.750 -1.0669 0.03111 0.02333 -0.0436 1.0000 0.0886
-11.500 -1.0554 0.03027 0.02263 -0.0414 1.0000 0.0905
-11.250 -1.0485 0.02969 0.02206 -0.0383 1.0000 0.0925
-11.000 -1.0426 0.02908 0.02137 -0.0350 1.0000 0.0947
-10.750 -1.0377 0.02848 0.02058 -0.0316 1.0000 0.0970
-10.500 -1.0259 0.02766 0.01986 -0.0294 1.0000 0.0995
-10.250 -1.0157 0.02717 0.01940 -0.0269 1.0000 0.1022
-10.000 -1.0058 0.02669 0.01881 -0.0243 1.0000 0.1054
-9.750 -0.9936 0.02600 0.01809 -0.0221 0.9999 0.1085
-9.500 -0.9571 0.02540 0.01754 -0.0245 0.9960 0.1133
-9.250 -0.9193 0.02476 0.01678 -0.0271 0.9924 0.1187
-9.000 -0.8850 0.02412 0.01624 -0.0291 0.9871 0.1240
-8.750 -0.8464 0.02356 0.01557 -0.0317 0.9824 0.1302
-8.500 -0.8090 0.02297 0.01508 -0.0341 0.9781 0.1364
-8.250 -0.7751 0.02244 0.01446 -0.0357 0.9718 0.1429
-8.000 -0.7363 0.02189 0.01400 -0.0383 0.9680 0.1500
-7.750 -0.7033 0.02138 0.01347 -0.0396 0.9623 0.1572
-7.500 -0.6691 0.02091 0.01305 -0.0412 0.9565 0.1648
-7.250 -0.6293 0.02036 0.01254 -0.0439 0.9531 0.1736
-7.000 -0.5975 0.02001 0.01216 -0.0448 0.9467 0.1824
-6.750 -0.5635 0.01949 0.01174 -0.0463 0.9409 0.1918
-6.500 -0.5226 0.01899 0.01127 -0.0490 0.9375 0.2037
-6.250 -0.4786 0.01853 0.01083 -0.0523 0.9353 0.2178
-6.000 -0.4556 0.01821 0.01058 -0.0514 0.9254 0.2295
-5.750 -0.4157 0.01772 0.01016 -0.0538 0.9216 0.2454
-5.500 -0.3751 0.01722 0.00973 -0.0563 0.9187 0.2625
-5.250 -0.3514 0.01691 0.00947 -0.0554 0.9089 0.2765
-5.000 -0.3159 0.01648 0.00907 -0.0567 0.9038 0.2932
-4.750 -0.2780 0.01603 0.00864 -0.0585 0.9000 0.3103
-4.500 -0.2556 0.01577 0.00844 -0.0572 0.8891 0.3242
-4.250 -0.2221 0.01532 0.00805 -0.0580 0.8834 0.3402
-4.000 -0.1951 0.01501 0.00779 -0.0576 0.8744 0.3553
-3.750 -0.1657 0.01466 0.00747 -0.0576 0.8660 0.3718
-3.500 -0.1361 0.01435 0.00718 -0.0576 0.8581 0.3894
-3.250 -0.1101 0.01405 0.00695 -0.0569 0.8475 0.4075
-3.000 -0.0814 0.01373 0.00669 -0.0567 0.8388 0.4278
-2.750 -0.0557 0.01347 0.00650 -0.0559 0.8275 0.4497
-2.500 -0.0290 0.01319 0.00632 -0.0554 0.8172 0.4737
-2.250 -0.0026 0.01294 0.00616 -0.0547 0.8060 0.5007
-2.000 0.0228 0.01278 0.00607 -0.0539 0.7941 0.5306
-1.750 0.0503 0.01256 0.00593 -0.0533 0.7837 0.5613
-1.500 0.0743 0.01246 0.00591 -0.0522 0.7703 0.5915
-1.250 0.1011 0.01234 0.00582 -0.0515 0.7591 0.6204
-1.000 0.1266 0.01224 0.00579 -0.0506 0.7466 0.6475
-0.750 0.1521 0.01219 0.00580 -0.0497 0.7341 0.6742
-0.500 0.1795 0.01214 0.00574 -0.0491 0.7232 0.7005
-0.250 0.2039 0.01214 0.00581 -0.0480 0.7101 0.7255
0.000 0.2306 0.01214 0.00583 -0.0473 0.6991 0.7493
0.250 0.2560 0.01217 0.00590 -0.0463 0.6869 0.7728
0.500 0.2820 0.01224 0.00600 -0.0454 0.6756 0.7958
0.750 0.3084 0.01232 0.00607 -0.0446 0.6646 0.8177
1.000 0.3339 0.01243 0.00621 -0.0435 0.6528 0.8390
1.250 0.3616 0.01257 0.00627 -0.0429 0.6421 0.8592
1.500 0.3869 0.01269 0.00642 -0.0418 0.6289 0.8785
1.750 0.4150 0.01287 0.00653 -0.0413 0.6176 0.8963
2.000 0.4436 0.01305 0.00667 -0.0409 0.6063 0.9134
2.250 0.4791 0.01329 0.00688 -0.0420 0.5951 0.9256
2.500 0.5165 0.01353 0.00702 -0.0435 0.5842 0.9371
2.750 0.5525 0.01376 0.00723 -0.0450 0.5726 0.9498
3.000 0.6027 0.01404 0.00739 -0.0493 0.5616 0.9560
3.250 0.6467 0.01425 0.00760 -0.0524 0.5490 0.9666
3.500 0.6962 0.01448 0.00776 -0.0568 0.5370 0.9743
3.750 0.7416 0.01465 0.00786 -0.0604 0.5253 0.9823
4.000 0.7867 0.01480 0.00799 -0.0641 0.5126 0.9901
4.250 0.8328 0.01495 0.00804 -0.0680 0.5007 0.9963
4.500 0.8657 0.01502 0.00812 -0.0695 0.4882 1.0000
4.750 0.8825 0.01513 0.00818 -0.0677 0.4772 1.0000
5.000 0.8987 0.01523 0.00821 -0.0657 0.4660 1.0000
5.250 0.9140 0.01535 0.00834 -0.0636 0.4547 1.0000
5.500 0.9304 0.01552 0.00841 -0.0616 0.4445 1.0000
5.750 0.9446 0.01566 0.00859 -0.0591 0.4333 1.0000
6.000 0.9604 0.01588 0.00872 -0.0569 0.4233 1.0000
6.250 0.9740 0.01604 0.00890 -0.0543 0.4119 1.0000
6.500 0.9886 0.01627 0.00909 -0.0519 0.4014 1.0000
6.750 1.0023 0.01649 0.00927 -0.0492 0.3903 1.0000
7.000 1.0160 0.01674 0.00952 -0.0466 0.3791 1.0000
7.500 1.0428 0.01730 0.01000 -0.0413 0.3567 1.0000
7.750 1.0561 0.01763 0.01028 -0.0387 0.3458 1.0000
8.000 1.0689 0.01797 0.01056 -0.0360 0.3345 1.0000
8.250 1.0822 0.01831 0.01091 -0.0334 0.3231 1.0000
8.500 1.0951 0.01875 0.01125 -0.0309 0.3125 1.0000
8.750 1.1063 0.01911 0.01164 -0.0280 0.3013 1.0000
9.000 1.1174 0.01956 0.01206 -0.0252 0.2910 1.0000
9.250 1.1280 0.02006 0.01250 -0.0225 0.2806 1.0000
9.500 1.1400 0.02057 0.01304 -0.0201 0.2698 1.0000
9.750 1.1508 0.02121 0.01360 -0.0176 0.2598 1.0000
10.000 1.1621 0.02182 0.01424 -0.0154 0.2490 1.0000
10.250 1.1732 0.02254 0.01495 -0.0133 0.2389 1.0000
10.500 1.1825 0.02340 0.01572 -0.0110 0.2291 1.0000
10.750 1.1935 0.02419 0.01658 -0.0091 0.2189 1.0000
11.000 1.2024 0.02518 0.01751 -0.0071 0.2098 1.0000
11.250 1.2117 0.02616 0.01851 -0.0053 0.2003 1.0000
11.500 1.2206 0.02725 0.01961 -0.0035 0.1915 1.0000
11.750 1.2277 0.02847 0.02079 -0.0018 0.1832 1.0000
12.000 1.2365 0.02966 0.02204 -0.0003 0.1748 1.0000
12.250 1.2417 0.03112 0.02342 0.0013 0.1677 1.0000
12.500 1.2499 0.03246 0.02486 0.0026 0.1598 1.0000
12.750 1.2541 0.03412 0.02644 0.0040 0.1534 1.0000
13.000 1.2610 0.03568 0.02810 0.0050 0.1465 1.0000
13.250 1.2641 0.03754 0.02987 0.0062 0.1409 1.0000
13.500 1.2697 0.03931 0.03175 0.0071 0.1348 1.0000
13.750 1.2722 0.04132 0.03369 0.0081 0.1297 1.0000
14.000 1.2765 0.04331 0.03578 0.0088 0.1244 1.0000
14.250 1.2794 0.04543 0.03789 0.0094 0.1198 1.0000
14.500 1.2829 0.04756 0.04004 0.0101 0.1154 1.0000
14.750 1.2859 0.04981 0.04236 0.0105 0.1112 1.0000
15.000 1.2906 0.05181 0.04424 0.0112 0.1075 1.0000
15.250 1.2931 0.05423 0.04682 0.0114 0.1040 1.0000
15.500 1.2966 0.05656 0.04919 0.0116 0.1007 1.0000
15.750 1.3036 0.05838 0.05090 0.0121 0.0978 1.0000
16.000 1.3054 0.06099 0.05365 0.0122 0.0951 1.0000
16.250 1.3080 0.06352 0.05627 0.0121 0.0924 1.0000
16.500 1.3133 0.06570 0.05845 0.0122 0.0901 1.0000
16.750 1.3219 0.06743 0.06012 0.0126 0.0878 1.0000
17.000 1.3208 0.07053 0.06340 0.0122 0.0858 1.0000
17.250 1.3234 0.07317 0.06613 0.0120 0.0839 1.0000
17.500 1.3292 0.07537 0.06834 0.0119 0.0822 1.0000
17.750 1.3425 0.07650 0.06938 0.0124 0.0805 1.0000
18.000 1.3426 0.07951 0.07253 0.0120 0.0791 1.0000
18.250 1.3385 0.08315 0.07635 0.0112 0.0778 1.0000
18.500 1.3372 0.08644 0.07977 0.0104 0.0764 1.0000
18.750 1.3393 0.08925 0.08263 0.0098 0.0751 1.0000
19.000 1.3480 0.09108 0.08445 0.0096 0.0738 1.0000
19.250 1.3662 0.09148 0.08475 0.0106 0.0725 1.0000
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