NACA 2412 (naca2412-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2412 (naca2412-il) Reynolds number: 200,000 Max Cl/Cd: 62.62 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2412-il-200000-n5.txt Download as CSV file: xf-naca2412-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2412
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8240 0.07577 0.07147 -0.0436 1.0000 0.0283
-13.500 -0.8677 0.06288 0.05833 -0.0542 1.0000 0.0281
-13.250 -0.8961 0.05413 0.04931 -0.0618 1.0000 0.0281
-13.000 -0.9170 0.04815 0.04305 -0.0662 1.0000 0.0282
-12.750 -0.9337 0.04398 0.03858 -0.0676 1.0000 0.0285
-12.500 -0.9470 0.04105 0.03537 -0.0664 1.0000 0.0288
-12.250 -0.9475 0.03932 0.03360 -0.0645 1.0000 0.0293
-12.000 -0.9414 0.03798 0.03222 -0.0630 1.0000 0.0298
-11.750 -0.9340 0.03669 0.03084 -0.0614 1.0000 0.0304
-11.500 -0.9264 0.03534 0.02936 -0.0597 1.0000 0.0311
-11.250 -0.9188 0.03388 0.02773 -0.0578 1.0000 0.0319
-11.000 -0.9106 0.03240 0.02603 -0.0558 1.0000 0.0327
-10.750 -0.9011 0.03098 0.02437 -0.0537 1.0000 0.0336
-10.500 -0.8900 0.02972 0.02284 -0.0517 1.0000 0.0344
-10.250 -0.8770 0.02850 0.02159 -0.0500 1.0000 0.0353
-10.000 -0.8624 0.02761 0.02065 -0.0483 1.0000 0.0361
-9.750 -0.8473 0.02674 0.01971 -0.0465 1.0000 0.0369
-9.500 -0.8319 0.02588 0.01875 -0.0448 1.0000 0.0380
-9.250 -0.8160 0.02502 0.01774 -0.0431 1.0000 0.0391
-9.000 -0.7997 0.02417 0.01672 -0.0414 1.0000 0.0401
-8.750 -0.7826 0.02336 0.01575 -0.0397 1.0000 0.0410
-8.500 -0.7663 0.02242 0.01480 -0.0381 1.0000 0.0420
-8.250 -0.7487 0.02176 0.01412 -0.0366 1.0000 0.0431
-8.000 -0.7266 0.02113 0.01343 -0.0360 0.9992 0.0445
-7.750 -0.6945 0.02039 0.01259 -0.0373 0.9963 0.0461
-7.500 -0.6618 0.01967 0.01175 -0.0387 0.9935 0.0476
-7.250 -0.6308 0.01893 0.01094 -0.0398 0.9898 0.0492
-7.000 -0.5984 0.01828 0.01029 -0.0412 0.9864 0.0514
-6.750 -0.5640 0.01774 0.00970 -0.0428 0.9837 0.0540
-6.500 -0.5333 0.01721 0.00909 -0.0437 0.9787 0.0566
-6.250 -0.4997 0.01661 0.00848 -0.0452 0.9747 0.0598
-6.000 -0.4642 0.01612 0.00797 -0.0470 0.9713 0.0643
-5.750 -0.4327 0.01565 0.00750 -0.0479 0.9650 0.0700
-5.500 -0.3964 0.01523 0.00704 -0.0498 0.9610 0.0781
-5.250 -0.3641 0.01479 0.00665 -0.0508 0.9555 0.0873
-5.000 -0.3324 0.01440 0.00628 -0.0517 0.9493 0.0972
-4.750 -0.2978 0.01403 0.00590 -0.0531 0.9451 0.1090
-4.500 -0.2696 0.01371 0.00561 -0.0532 0.9369 0.1216
-4.250 -0.2371 0.01335 0.00530 -0.0542 0.9310 0.1370
-4.000 -0.2081 0.01302 0.00504 -0.0545 0.9230 0.1556
-3.750 -0.1774 0.01268 0.00479 -0.0551 0.9157 0.1810
-3.500 -0.1486 0.01235 0.00458 -0.0553 0.9070 0.2122
-3.250 -0.1186 0.01202 0.00437 -0.0557 0.8988 0.2448
-3.000 -0.0906 0.01176 0.00419 -0.0556 0.8887 0.2748
-2.750 -0.0609 0.01148 0.00399 -0.0559 0.8798 0.3040
-2.500 -0.0333 0.01123 0.00383 -0.0557 0.8687 0.3339
-2.250 -0.0057 0.01098 0.00367 -0.0555 0.8575 0.3671
-2.000 0.0220 0.01073 0.00353 -0.0554 0.8464 0.4060
-1.750 0.0490 0.01046 0.00341 -0.0550 0.8343 0.4534
-1.500 0.0751 0.01022 0.00333 -0.0545 0.8212 0.5065
-1.250 0.1012 0.01001 0.00327 -0.0538 0.8080 0.5612
-1.000 0.1269 0.00980 0.00323 -0.0531 0.7944 0.6187
-0.750 0.1518 0.00959 0.00321 -0.0520 0.7806 0.6817
-0.500 0.1764 0.00943 0.00322 -0.0508 0.7662 0.7423
-0.250 0.2018 0.00935 0.00324 -0.0497 0.7517 0.7919
0.000 0.2282 0.00934 0.00327 -0.0488 0.7362 0.8361
0.250 0.2568 0.00937 0.00330 -0.0484 0.7205 0.8743
0.500 0.2884 0.00944 0.00332 -0.0487 0.7042 0.9059
0.750 0.3226 0.00952 0.00334 -0.0496 0.6873 0.9313
1.000 0.3582 0.00962 0.00336 -0.0510 0.6696 0.9518
1.250 0.3941 0.00973 0.00338 -0.0525 0.6513 0.9687
1.500 0.4304 0.00985 0.00341 -0.0542 0.6325 0.9826
1.750 0.4691 0.00998 0.00344 -0.0565 0.6132 0.9930
2.000 0.5051 0.01011 0.00347 -0.0583 0.5940 1.0000
2.250 0.5284 0.01026 0.00352 -0.0574 0.5767 1.0000
2.500 0.5518 0.01041 0.00359 -0.0564 0.5599 1.0000
2.750 0.5752 0.01058 0.00368 -0.0555 0.5436 1.0000
3.000 0.5987 0.01075 0.00378 -0.0546 0.5280 1.0000
3.250 0.6223 0.01093 0.00390 -0.0538 0.5132 1.0000
3.500 0.6460 0.01112 0.00405 -0.0529 0.4987 1.0000
3.750 0.6698 0.01132 0.00420 -0.0521 0.4839 1.0000
4.000 0.6932 0.01153 0.00435 -0.0512 0.4661 1.0000
4.250 0.7161 0.01179 0.00452 -0.0502 0.4446 1.0000
4.500 0.7393 0.01204 0.00470 -0.0493 0.4224 1.0000
4.750 0.7627 0.01229 0.00490 -0.0484 0.4018 1.0000
5.000 0.7857 0.01259 0.00512 -0.0475 0.3799 1.0000
5.250 0.8084 0.01291 0.00536 -0.0466 0.3531 1.0000
5.500 0.8303 0.01331 0.00562 -0.0455 0.3221 1.0000
5.750 0.8518 0.01375 0.00593 -0.0445 0.2903 1.0000
6.000 0.8732 0.01423 0.00628 -0.0434 0.2602 1.0000
6.250 0.8943 0.01475 0.00667 -0.0424 0.2314 1.0000
6.500 0.9152 0.01530 0.00709 -0.0413 0.2040 1.0000
7.000 0.9562 0.01649 0.00806 -0.0392 0.1527 1.0000
7.250 0.9763 0.01712 0.00859 -0.0381 0.1311 1.0000
7.500 0.9963 0.01775 0.00915 -0.0370 0.1127 1.0000
7.750 1.0158 0.01841 0.00976 -0.0358 0.0985 1.0000
8.000 1.0350 0.01908 0.01040 -0.0346 0.0880 1.0000
8.250 1.0532 0.01981 0.01109 -0.0332 0.0798 1.0000
8.500 1.0724 0.02043 0.01175 -0.0320 0.0736 1.0000
8.750 1.0891 0.02122 0.01254 -0.0304 0.0688 1.0000
9.000 1.1073 0.02186 0.01327 -0.0291 0.0651 1.0000
9.250 1.1238 0.02259 0.01404 -0.0275 0.0615 1.0000
9.500 1.1371 0.02348 0.01492 -0.0256 0.0586 1.0000
9.750 1.1513 0.02421 0.01574 -0.0237 0.0563 1.0000
10.000 1.1647 0.02501 0.01663 -0.0218 0.0541 1.0000
10.250 1.1773 0.02589 0.01756 -0.0199 0.0521 1.0000
10.500 1.1879 0.02691 0.01862 -0.0179 0.0503 1.0000
10.750 1.1976 0.02805 0.01980 -0.0159 0.0487 1.0000
11.000 1.2099 0.02905 0.02092 -0.0143 0.0471 1.0000
11.250 1.2210 0.03015 0.02212 -0.0127 0.0455 1.0000
11.500 1.2313 0.03133 0.02338 -0.0112 0.0440 1.0000
11.750 1.2400 0.03266 0.02476 -0.0098 0.0427 1.0000
12.000 1.2456 0.03431 0.02644 -0.0083 0.0414 1.0000
12.250 1.2551 0.03572 0.02798 -0.0071 0.0403 1.0000
12.500 1.2636 0.03724 0.02963 -0.0060 0.0390 1.0000
12.750 1.2711 0.03888 0.03140 -0.0050 0.0378 1.0000
13.000 1.2775 0.04066 0.03327 -0.0042 0.0367 1.0000
13.250 1.2825 0.04263 0.03531 -0.0035 0.0357 1.0000
13.500 1.2851 0.04488 0.03760 -0.0029 0.0348 1.0000
13.750 1.2893 0.04709 0.03997 -0.0024 0.0339 1.0000
14.000 1.2930 0.04943 0.04247 -0.0021 0.0329 1.0000
14.250 1.2954 0.05194 0.04513 -0.0019 0.0320 1.0000
14.500 1.2967 0.05463 0.04795 -0.0020 0.0311 1.0000
14.750 1.2971 0.05750 0.05092 -0.0023 0.0304 1.0000
15.000 1.2963 0.06057 0.05408 -0.0028 0.0297 1.0000
15.250 1.2943 0.06383 0.05741 -0.0033 0.0291 1.0000
15.500 1.2913 0.06742 0.06115 -0.0041 0.0285 1.0000
15.750 1.2872 0.07129 0.06523 -0.0051 0.0278 1.0000
16.000 1.2820 0.07542 0.06953 -0.0064 0.0271 1.0000
16.250 1.2760 0.07978 0.07405 -0.0079 0.0265 1.0000
16.500 1.2695 0.08434 0.07875 -0.0097 0.0260 1.0000
16.750 1.2622 0.08909 0.08364 -0.0116 0.0255 1.0000
17.000 1.2547 0.09400 0.08867 -0.0138 0.0251 1.0000
17.250 1.2472 0.09902 0.09378 -0.0161 0.0247 1.0000
17.500 1.2396 0.10412 0.09899 -0.0185 0.0243 1.0000
17.750 1.2316 0.10928 0.10421 -0.0210 0.0240 1.0000
18.000 1.2155 0.11640 0.11157 -0.0247 0.0237 1.0000
18.250 1.1974 0.12420 0.11958 -0.0291 0.0234 1.0000
18.500 1.1770 0.13276 0.12836 -0.0341 0.0231 1.0000
18.750 1.1520 0.14275 0.13855 -0.0401 0.0230 1.0000
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Polar data table (+)
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