NACA 2418 (naca2418-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2418 (naca2418-il) Reynolds number: 100,000 Max Cl/Cd: 44 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2418-il-100000-n5.txt Download as CSV file: xf-naca2418-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8072 0.08487 0.07772 -0.0653 1.0000 0.0726
-15.500 -0.8514 0.07482 0.06740 -0.0712 1.0000 0.0732
-15.250 -0.8526 0.07164 0.06421 -0.0724 1.0000 0.0740
-15.000 -0.8639 0.06715 0.05963 -0.0745 1.0000 0.0749
-14.750 -0.8768 0.06267 0.05501 -0.0765 1.0000 0.0759
-14.500 -0.8898 0.05842 0.05060 -0.0781 1.0000 0.0770
-14.250 -0.9025 0.05449 0.04649 -0.0791 1.0000 0.0782
-14.000 -0.9150 0.05090 0.04266 -0.0796 1.0000 0.0795
-13.750 -0.9202 0.04828 0.03991 -0.0792 1.0000 0.0808
-13.500 -0.9172 0.04661 0.03826 -0.0784 1.0000 0.0820
-13.250 -0.9175 0.04483 0.03643 -0.0773 1.0000 0.0834
-13.000 -0.9203 0.04304 0.03455 -0.0757 1.0000 0.0849
-12.750 -0.9248 0.04134 0.03271 -0.0735 1.0000 0.0866
-12.500 -0.9316 0.03975 0.03092 -0.0706 1.0000 0.0884
-12.250 -0.9313 0.03876 0.02999 -0.0677 1.0000 0.0897
-12.000 -0.9348 0.03784 0.02908 -0.0641 1.0000 0.0912
-11.750 -0.9413 0.03700 0.02820 -0.0598 1.0000 0.0929
-11.500 -0.9485 0.03619 0.02731 -0.0550 1.0000 0.0946
-11.250 -0.9515 0.03529 0.02625 -0.0509 1.0000 0.0968
-11.000 -0.9506 0.03452 0.02551 -0.0472 1.0000 0.0987
-10.750 -0.9487 0.03384 0.02483 -0.0436 1.0000 0.1007
-10.500 -0.9457 0.03313 0.02408 -0.0402 1.0000 0.1033
-10.250 -0.9413 0.03239 0.02319 -0.0369 1.0000 0.1063
-10.000 -0.9354 0.03171 0.02252 -0.0339 1.0000 0.1087
-9.750 -0.9228 0.03105 0.02186 -0.0321 0.9989 0.1119
-9.500 -0.8926 0.03022 0.02087 -0.0335 0.9942 0.1172
-9.250 -0.8634 0.02945 0.02014 -0.0348 0.9894 0.1216
-9.000 -0.8335 0.02874 0.01935 -0.0361 0.9841 0.1273
-8.750 -0.8009 0.02803 0.01863 -0.0378 0.9798 0.1327
-8.500 -0.7734 0.02740 0.01796 -0.0385 0.9731 0.1386
-8.250 -0.7406 0.02674 0.01728 -0.0401 0.9681 0.1448
-8.000 -0.7114 0.02616 0.01667 -0.0409 0.9614 0.1515
-7.750 -0.6795 0.02555 0.01607 -0.0422 0.9552 0.1585
-7.500 -0.6441 0.02499 0.01546 -0.0442 0.9503 0.1669
-7.250 -0.6180 0.02446 0.01497 -0.0442 0.9417 0.1741
-7.000 -0.5818 0.02394 0.01440 -0.0461 0.9369 0.1842
-6.750 -0.5550 0.02347 0.01400 -0.0463 0.9291 0.1929
-6.500 -0.5232 0.02299 0.01353 -0.0473 0.9227 0.2035
-6.250 -0.4862 0.02252 0.01303 -0.0492 0.9184 0.2163
-6.000 -0.4634 0.02215 0.01272 -0.0484 0.9087 0.2267
-5.750 -0.4305 0.02171 0.01230 -0.0495 0.9028 0.2396
-5.500 -0.4002 0.02134 0.01191 -0.0500 0.8960 0.2532
-5.250 -0.3736 0.02100 0.01159 -0.0498 0.8872 0.2661
-5.000 -0.3395 0.02056 0.01119 -0.0509 0.8819 0.2804
-4.750 -0.3158 0.02028 0.01093 -0.0501 0.8716 0.2933
-4.250 -0.2568 0.01960 0.01029 -0.0505 0.8562 0.3226
-4.000 -0.2289 0.01927 0.01002 -0.0504 0.8472 0.3372
-3.750 -0.1971 0.01891 0.00969 -0.0509 0.8403 0.3538
-3.500 -0.1729 0.01869 0.00950 -0.0501 0.8292 0.3701
-3.250 -0.1401 0.01831 0.00917 -0.0507 0.8224 0.3897
-3.000 -0.1173 0.01813 0.00905 -0.0496 0.8103 0.4089
-2.750 -0.0857 0.01777 0.00877 -0.0500 0.8028 0.4318
-2.500 -0.0624 0.01760 0.00870 -0.0489 0.7904 0.4545
-2.250 -0.0316 0.01730 0.00847 -0.0490 0.7823 0.4809
-2.000 -0.0078 0.01716 0.00842 -0.0480 0.7697 0.5062
-1.750 0.0213 0.01695 0.00825 -0.0479 0.7602 0.5334
-1.500 0.0468 0.01682 0.00821 -0.0470 0.7483 0.5591
-1.250 0.0744 0.01668 0.00812 -0.0466 0.7377 0.5855
-1.000 0.1014 0.01658 0.00805 -0.0460 0.7264 0.6113
-0.750 0.1278 0.01651 0.00803 -0.0453 0.7150 0.6370
-0.500 0.1559 0.01643 0.00796 -0.0448 0.7043 0.6620
-0.250 0.1816 0.01642 0.00802 -0.0440 0.6924 0.6861
0.000 0.2108 0.01638 0.00798 -0.0436 0.6824 0.7107
0.250 0.2360 0.01644 0.00810 -0.0427 0.6700 0.7345
0.500 0.2648 0.01646 0.00812 -0.0423 0.6601 0.7583
0.750 0.2911 0.01655 0.00824 -0.0416 0.6482 0.7815
1.000 0.3198 0.01664 0.00832 -0.0412 0.6379 0.8038
1.250 0.3480 0.01676 0.00844 -0.0408 0.6268 0.8256
1.500 0.3775 0.01690 0.00857 -0.0406 0.6162 0.8463
1.750 0.4082 0.01706 0.00869 -0.0407 0.6055 0.8661
2.000 0.4396 0.01724 0.00886 -0.0410 0.5941 0.8852
2.250 0.4741 0.01742 0.00894 -0.0419 0.5831 0.9032
2.500 0.5080 0.01764 0.00916 -0.0428 0.5700 0.9207
2.750 0.5448 0.01784 0.00928 -0.0443 0.5583 0.9363
3.000 0.5815 0.01805 0.00944 -0.0460 0.5464 0.9504
3.250 0.6232 0.01826 0.00961 -0.0488 0.5347 0.9606
3.500 0.6643 0.01845 0.00971 -0.0515 0.5238 0.9701
3.750 0.7027 0.01866 0.00992 -0.0538 0.5118 0.9804
4.000 0.7440 0.01883 0.01002 -0.0567 0.5009 0.9887
4.250 0.7837 0.01902 0.01022 -0.0595 0.4886 0.9970
4.500 0.8090 0.01921 0.01036 -0.0593 0.4786 1.0000
4.750 0.8241 0.01939 0.01053 -0.0572 0.4685 1.0000
5.000 0.8401 0.01959 0.01069 -0.0551 0.4594 1.0000
5.250 0.8549 0.01981 0.01090 -0.0528 0.4491 1.0000
5.500 0.8704 0.02004 0.01109 -0.0507 0.4393 1.0000
5.750 0.8851 0.02028 0.01131 -0.0483 0.4287 1.0000
6.000 0.8995 0.02054 0.01155 -0.0459 0.4177 1.0000
6.250 0.9141 0.02080 0.01174 -0.0435 0.4068 1.0000
6.500 0.9274 0.02109 0.01205 -0.0410 0.3948 1.0000
6.750 0.9416 0.02140 0.01229 -0.0385 0.3841 1.0000
7.000 0.9552 0.02173 0.01261 -0.0360 0.3727 1.0000
7.250 0.9694 0.02209 0.01296 -0.0337 0.3620 1.0000
7.500 0.9834 0.02247 0.01328 -0.0314 0.3515 1.0000
7.750 0.9973 0.02289 0.01372 -0.0291 0.3405 1.0000
8.000 1.0109 0.02333 0.01409 -0.0267 0.3306 1.0000
8.250 1.0236 0.02380 0.01459 -0.0244 0.3196 1.0000
8.500 1.0352 0.02429 0.01506 -0.0218 0.3098 1.0000
8.750 1.0457 0.02483 0.01558 -0.0191 0.2995 1.0000
9.000 1.0569 0.02542 0.01618 -0.0167 0.2895 1.0000
9.250 1.0671 0.02607 0.01679 -0.0142 0.2797 1.0000
9.500 1.0780 0.02677 0.01753 -0.0120 0.2694 1.0000
9.750 1.0877 0.02755 0.01825 -0.0098 0.2600 1.0000
10.000 1.0974 0.02838 0.01913 -0.0077 0.2497 1.0000
10.250 1.1066 0.02930 0.02004 -0.0057 0.2405 1.0000
10.500 1.1148 0.03030 0.02103 -0.0037 0.2311 1.0000
10.750 1.1234 0.03137 0.02213 -0.0019 0.2221 1.0000
11.000 1.1301 0.03256 0.02330 -0.0001 0.2136 1.0000
11.250 1.1378 0.03381 0.02461 0.0014 0.2048 1.0000
11.500 1.1430 0.03521 0.02598 0.0031 0.1971 1.0000
11.750 1.1498 0.03664 0.02750 0.0044 0.1886 1.0000
12.000 1.1535 0.03828 0.02910 0.0058 0.1816 1.0000
12.250 1.1592 0.03993 0.03086 0.0068 0.1736 1.0000
12.500 1.1616 0.04182 0.03271 0.0080 0.1673 1.0000
12.750 1.1661 0.04371 0.03471 0.0088 0.1600 1.0000
13.000 1.1672 0.04585 0.03684 0.0096 0.1543 1.0000
13.250 1.1702 0.04799 0.03908 0.0102 0.1480 1.0000
13.500 1.1705 0.05038 0.04149 0.0107 0.1427 1.0000
13.750 1.1720 0.05279 0.04396 0.0111 0.1375 1.0000
14.000 1.1720 0.05540 0.04663 0.0113 0.1325 1.0000
14.250 1.1717 0.05808 0.04929 0.0114 0.1283 1.0000
14.500 1.1722 0.06085 0.05219 0.0114 0.1236 1.0000
14.750 1.1713 0.06376 0.05512 0.0113 0.1197 1.0000
15.000 1.1709 0.06668 0.05808 0.0111 0.1160 1.0000
15.250 1.1699 0.06980 0.06132 0.0107 0.1121 1.0000
15.500 1.1689 0.07290 0.06444 0.0103 0.1089 1.0000
15.750 1.1686 0.07594 0.06751 0.0099 0.1058 1.0000
16.000 1.1665 0.07939 0.07110 0.0092 0.1025 1.0000
16.250 1.1652 0.08270 0.07446 0.0085 0.0997 1.0000
16.500 1.1672 0.08547 0.07720 0.0080 0.0973 1.0000
16.750 1.1622 0.08952 0.08143 0.0069 0.0945 1.0000
17.000 1.1594 0.09323 0.08525 0.0058 0.0920 1.0000
17.250 1.1597 0.09643 0.08848 0.0050 0.0898 1.0000
17.500 1.1614 0.09940 0.09145 0.0042 0.0878 1.0000
17.750 1.1529 0.10426 0.09650 0.0023 0.0857 1.0000
18.000 1.1472 0.10865 0.10102 0.0006 0.0837 1.0000
18.250 1.1465 0.11219 0.10462 -0.0007 0.0818 1.0000
18.500 1.1536 0.11430 0.10668 -0.0013 0.0802 1.0000
18.750 1.1385 0.12060 0.11321 -0.0043 0.0786 1.0000
19.000 1.1210 0.12751 0.12033 -0.0079 0.0770 1.0000
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