NACA 2418 (naca2418-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 2418 (naca2418-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.52 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2418-il-1000000-n5.txt Download as CSV file: xf-naca2418-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.1926 0.08389 0.07986 -0.0564 1.0000 0.0294
-19.500 -1.2161 0.07721 0.07306 -0.0596 1.0000 0.0296
-19.250 -1.2364 0.07108 0.06681 -0.0625 1.0000 0.0297
-19.000 -1.2559 0.06515 0.06076 -0.0653 1.0000 0.0299
-18.750 -1.2715 0.05981 0.05531 -0.0678 1.0000 0.0301
-18.500 -1.2843 0.05498 0.05037 -0.0699 1.0000 0.0302
-18.250 -1.2942 0.05060 0.04588 -0.0718 1.0000 0.0304
-18.000 -1.3005 0.04678 0.04195 -0.0734 1.0000 0.0306
-17.750 -1.3043 0.04334 0.03842 -0.0747 1.0000 0.0308
-17.500 -1.3052 0.04031 0.03531 -0.0758 1.0000 0.0310
-17.250 -1.3039 0.03761 0.03252 -0.0766 1.0000 0.0312
-17.000 -1.3036 0.03491 0.02975 -0.0772 1.0000 0.0314
-16.750 -1.3013 0.03254 0.02731 -0.0776 1.0000 0.0318
-16.500 -1.2972 0.03049 0.02519 -0.0777 1.0000 0.0321
-16.250 -1.2914 0.02872 0.02337 -0.0774 1.0000 0.0325
-16.000 -1.2843 0.02718 0.02178 -0.0769 1.0000 0.0329
-15.750 -1.2764 0.02584 0.02039 -0.0762 1.0000 0.0334
-15.500 -1.2681 0.02467 0.01917 -0.0751 1.0000 0.0338
-15.250 -1.2599 0.02365 0.01810 -0.0736 1.0000 0.0343
-15.000 -1.2531 0.02277 0.01717 -0.0716 1.0000 0.0346
-14.750 -1.2487 0.02202 0.01638 -0.0689 1.0000 0.0349
-14.500 -1.2480 0.02135 0.01566 -0.0654 0.9999 0.0353
-14.250 -1.2265 0.02050 0.01479 -0.0657 0.9976 0.0360
-14.000 -1.2041 0.01976 0.01403 -0.0660 0.9953 0.0368
-13.750 -1.1798 0.01910 0.01334 -0.0664 0.9934 0.0376
-13.500 -1.1555 0.01851 0.01272 -0.0667 0.9913 0.0384
-13.250 -1.1330 0.01799 0.01216 -0.0664 0.9874 0.0392
-13.000 -1.1100 0.01742 0.01158 -0.0663 0.9837 0.0402
-12.750 -1.0850 0.01689 0.01104 -0.0664 0.9807 0.0415
-12.500 -1.0637 0.01646 0.01059 -0.0657 0.9756 0.0428
-12.250 -1.0401 0.01605 0.01016 -0.0653 0.9708 0.0439
-12.000 -1.0157 0.01559 0.00968 -0.0651 0.9669 0.0455
-11.750 -0.9941 0.01520 0.00929 -0.0642 0.9609 0.0470
-11.500 -0.9706 0.01486 0.00892 -0.0636 0.9552 0.0485
-11.250 -0.9473 0.01448 0.00852 -0.0629 0.9501 0.0502
-11.000 -0.9249 0.01414 0.00818 -0.0621 0.9432 0.0522
-10.750 -0.9011 0.01383 0.00784 -0.0614 0.9358 0.0540
-10.500 -0.8783 0.01350 0.00749 -0.0606 0.9262 0.0562
-10.250 -0.8547 0.01321 0.00717 -0.0598 0.9162 0.0588
-10.000 -0.8307 0.01292 0.00687 -0.0592 0.9065 0.0614
-9.750 -0.8062 0.01264 0.00657 -0.0586 0.8986 0.0643
-9.500 -0.7811 0.01239 0.00631 -0.0581 0.8902 0.0669
-9.250 -0.7563 0.01214 0.00604 -0.0576 0.8815 0.0700
-9.000 -0.7304 0.01193 0.00580 -0.0572 0.8730 0.0728
-8.750 -0.7052 0.01169 0.00555 -0.0567 0.8633 0.0760
-8.500 -0.6791 0.01149 0.00533 -0.0564 0.8544 0.0792
-8.250 -0.6532 0.01129 0.00510 -0.0560 0.8444 0.0824
-8.000 -0.6270 0.01110 0.00490 -0.0556 0.8345 0.0862
-7.750 -0.6007 0.01095 0.00470 -0.0553 0.8234 0.0892
-7.500 -0.5743 0.01075 0.00450 -0.0550 0.8133 0.0927
-7.250 -0.5478 0.01062 0.00432 -0.0546 0.8022 0.0959
-7.000 -0.5210 0.01047 0.00415 -0.0544 0.7907 0.0991
-6.750 -0.4946 0.01031 0.00397 -0.0541 0.7796 0.1032
-6.500 -0.4675 0.01019 0.00382 -0.0538 0.7684 0.1069
-6.250 -0.4411 0.01003 0.00365 -0.0535 0.7575 0.1124
-6.000 -0.4142 0.00991 0.00350 -0.0532 0.7454 0.1175
-5.750 -0.3874 0.00976 0.00335 -0.0530 0.7348 0.1236
-5.250 -0.3335 0.00951 0.00308 -0.0525 0.7122 0.1366
-5.000 -0.3066 0.00941 0.00296 -0.0522 0.7010 0.1439
-4.750 -0.2795 0.00928 0.00284 -0.0520 0.6894 0.1532
-4.500 -0.2527 0.00916 0.00273 -0.0518 0.6779 0.1637
-4.250 -0.2257 0.00904 0.00262 -0.0515 0.6654 0.1750
-4.000 -0.1986 0.00895 0.00253 -0.0513 0.6530 0.1864
-3.750 -0.1716 0.00887 0.00245 -0.0511 0.6398 0.1985
-3.500 -0.1445 0.00879 0.00237 -0.0509 0.6263 0.2101
-3.250 -0.1171 0.00873 0.00231 -0.0507 0.6135 0.2204
-3.000 -0.0898 0.00870 0.00225 -0.0505 0.6000 0.2305
-2.750 -0.0623 0.00865 0.00220 -0.0503 0.5872 0.2395
-2.500 -0.0346 0.00862 0.00216 -0.0502 0.5765 0.2490
-2.250 -0.0071 0.00860 0.00212 -0.0500 0.5648 0.2574
-2.000 0.0207 0.00858 0.00209 -0.0499 0.5544 0.2663
-1.500 0.0763 0.00853 0.00204 -0.0497 0.5358 0.2857
-1.250 0.1040 0.00851 0.00202 -0.0496 0.5268 0.2952
-1.000 0.1318 0.00849 0.00201 -0.0495 0.5183 0.3071
-0.750 0.1592 0.00847 0.00201 -0.0493 0.5078 0.3201
-0.500 0.1867 0.00846 0.00200 -0.0492 0.4973 0.3338
-0.250 0.2135 0.00842 0.00200 -0.0489 0.4856 0.3579
0.000 0.2407 0.00835 0.00201 -0.0487 0.4767 0.3864
0.250 0.2679 0.00831 0.00202 -0.0485 0.4677 0.4101
0.500 0.2952 0.00828 0.00204 -0.0484 0.4602 0.4329
0.750 0.3228 0.00823 0.00206 -0.0483 0.4530 0.4572
1.000 0.3499 0.00823 0.00209 -0.0480 0.4449 0.4799
1.250 0.3776 0.00821 0.00213 -0.0479 0.4374 0.5020
1.500 0.4047 0.00823 0.00217 -0.0477 0.4280 0.5242
1.750 0.4322 0.00824 0.00222 -0.0476 0.4205 0.5435
2.000 0.4597 0.00826 0.00228 -0.0474 0.4124 0.5619
2.250 0.4867 0.00831 0.00234 -0.0472 0.4043 0.5813
2.500 0.5142 0.00834 0.00241 -0.0471 0.3954 0.5988
2.750 0.5409 0.00842 0.00249 -0.0468 0.3857 0.6153
3.000 0.5682 0.00846 0.00257 -0.0466 0.3772 0.6329
3.250 0.5945 0.00854 0.00266 -0.0463 0.3670 0.6529
3.500 0.6204 0.00865 0.00277 -0.0459 0.3527 0.6731
3.750 0.6462 0.00877 0.00289 -0.0454 0.3377 0.6921
4.000 0.6719 0.00888 0.00301 -0.0450 0.3254 0.7131
4.250 0.6972 0.00899 0.00315 -0.0445 0.3142 0.7378
4.500 0.7232 0.00907 0.00328 -0.0440 0.3048 0.7621
4.750 0.7481 0.00920 0.00343 -0.0435 0.2941 0.7872
5.000 0.7723 0.00929 0.00360 -0.0427 0.2829 0.8226
5.250 0.7959 0.00940 0.00379 -0.0417 0.2729 0.8590
5.500 0.8189 0.00958 0.00399 -0.0407 0.2610 0.8868
5.750 0.8426 0.00976 0.00418 -0.0398 0.2499 0.9058
6.000 0.8658 0.00998 0.00438 -0.0388 0.2393 0.9225
6.250 0.8885 0.01024 0.00461 -0.0378 0.2277 0.9379
6.500 0.9125 0.01048 0.00482 -0.0370 0.2175 0.9517
6.750 0.9374 0.01074 0.00506 -0.0365 0.2085 0.9640
7.000 0.9651 0.01104 0.00531 -0.0366 0.1989 0.9730
7.250 0.9925 0.01134 0.00556 -0.0368 0.1884 0.9810
7.500 1.0213 0.01170 0.00585 -0.0373 0.1763 0.9875
7.750 1.0487 0.01208 0.00616 -0.0376 0.1650 0.9932
8.000 1.0779 0.01248 0.00649 -0.0383 0.1533 0.9972
8.250 1.0979 0.01284 0.00679 -0.0371 0.1428 1.0000
8.500 1.1098 0.01313 0.00704 -0.0341 0.1355 1.0000
8.750 1.1243 0.01349 0.00736 -0.0318 0.1281 1.0000
9.000 1.1411 0.01385 0.00769 -0.0299 0.1214 1.0000
9.250 1.1582 0.01425 0.00806 -0.0283 0.1156 1.0000
9.500 1.1756 0.01467 0.00845 -0.0267 0.1099 1.0000
9.750 1.1932 0.01510 0.00887 -0.0252 0.1048 1.0000
10.000 1.2104 0.01558 0.00932 -0.0237 0.0996 1.0000
10.250 1.2279 0.01605 0.00979 -0.0223 0.0953 1.0000
10.500 1.2452 0.01656 0.01028 -0.0210 0.0909 1.0000
10.750 1.2619 0.01711 0.01082 -0.0196 0.0870 1.0000
11.000 1.2787 0.01767 0.01138 -0.0183 0.0829 1.0000
11.250 1.2942 0.01832 0.01201 -0.0170 0.0791 1.0000
11.500 1.3104 0.01895 0.01264 -0.0157 0.0753 1.0000
11.750 1.3249 0.01969 0.01338 -0.0143 0.0718 1.0000
12.000 1.3398 0.02043 0.01412 -0.0131 0.0682 1.0000
12.250 1.3532 0.02129 0.01497 -0.0118 0.0649 1.0000
12.500 1.3670 0.02214 0.01584 -0.0106 0.0619 1.0000
12.750 1.3793 0.02313 0.01682 -0.0093 0.0590 1.0000
13.000 1.3926 0.02407 0.01778 -0.0082 0.0569 1.0000
13.250 1.4043 0.02515 0.01888 -0.0071 0.0546 1.0000
13.500 1.4158 0.02628 0.02003 -0.0060 0.0528 1.0000
13.750 1.4274 0.02744 0.02121 -0.0051 0.0511 1.0000
14.000 1.4374 0.02874 0.02255 -0.0041 0.0494 1.0000
14.250 1.4462 0.03018 0.02401 -0.0032 0.0479 1.0000
14.500 1.4565 0.03154 0.02541 -0.0024 0.0467 1.0000
14.750 1.4654 0.03306 0.02697 -0.0017 0.0455 1.0000
15.000 1.4726 0.03476 0.02870 -0.0010 0.0442 1.0000
15.250 1.4783 0.03665 0.03063 -0.0004 0.0430 1.0000
15.500 1.4860 0.03841 0.03244 0.0001 0.0422 1.0000
15.750 1.4925 0.04033 0.03441 0.0005 0.0412 1.0000
16.000 1.4974 0.04244 0.03657 0.0009 0.0404 1.0000
16.250 1.5009 0.04473 0.03891 0.0011 0.0396 1.0000
16.500 1.5032 0.04721 0.04144 0.0013 0.0389 1.0000
16.750 1.5053 0.04977 0.04406 0.0014 0.0383 1.0000
17.000 1.5084 0.05227 0.04662 0.0013 0.0378 1.0000
17.250 1.5101 0.05493 0.04935 0.0012 0.0373 1.0000
17.500 1.5104 0.05782 0.05231 0.0010 0.0368 1.0000
17.750 1.5096 0.06087 0.05543 0.0007 0.0363 1.0000
18.000 1.5077 0.06410 0.05873 0.0003 0.0358 1.0000
18.250 1.5045 0.06749 0.06219 -0.0001 0.0353 1.0000
18.500 1.5003 0.07105 0.06581 -0.0007 0.0349 1.0000
18.750 1.4944 0.07489 0.06972 -0.0014 0.0344 1.0000
19.000 1.4884 0.07880 0.07371 -0.0023 0.0341 1.0000
19.250 1.4838 0.08253 0.07753 -0.0031 0.0338 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 2418 (naca2418-il)