NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: NACA 64(1)-212 MOD A (n64212ma-il) Reynolds number: 500,000 Max Cl/Cd: 68.49 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212ma-il-500000.txt Download as CSV file: xf-n64212ma-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3892 0.10533 0.10287 -0.0252 1.0000 0.0259
-10.250 -0.3865 0.10169 0.09926 -0.0268 1.0000 0.0265
-10.000 -0.4133 0.09111 0.08870 -0.0369 1.0000 0.0278
-9.750 -0.4040 0.08929 0.08691 -0.0355 1.0000 0.0280
-9.500 -0.3974 0.08684 0.08448 -0.0356 1.0000 0.0282
-9.250 -0.3930 0.08402 0.08169 -0.0363 1.0000 0.0284
-9.000 -0.3893 0.08121 0.07891 -0.0372 1.0000 0.0288
-8.750 -0.3910 0.07738 0.07512 -0.0394 1.0000 0.0293
-8.500 -0.4017 0.07208 0.06985 -0.0440 1.0000 0.0295
-8.250 -0.4200 0.06739 0.06518 -0.0477 0.9919 0.0297
-8.000 -0.4262 0.05477 0.05197 -0.0625 0.9563 0.0319
-7.750 -0.4066 0.05210 0.04926 -0.0643 0.9387 0.0321
-7.500 -0.3938 0.04996 0.04704 -0.0643 0.9192 0.0323
-7.250 -0.3832 0.04791 0.04487 -0.0635 0.9017 0.0326
-7.000 -0.3720 0.04579 0.04262 -0.0627 0.8866 0.0332
-6.750 -0.3696 0.04065 0.03685 -0.0609 0.8725 0.0362
-6.500 -0.3526 0.03879 0.03496 -0.0604 0.8598 0.0364
-6.250 -0.3350 0.03710 0.03319 -0.0599 0.8479 0.0368
-6.000 -0.3166 0.03547 0.03144 -0.0593 0.8363 0.0374
-5.750 -0.3004 0.03229 0.02761 -0.0575 0.8260 0.0408
-5.500 -0.2792 0.03042 0.02574 -0.0572 0.8144 0.0411
-5.250 -0.2572 0.02899 0.02425 -0.0569 0.8030 0.0416
-5.000 -0.2348 0.02768 0.02281 -0.0564 0.7905 0.0425
-4.750 -0.2121 0.02570 0.02033 -0.0552 0.7794 0.0460
-4.500 -0.1883 0.02435 0.01895 -0.0549 0.7658 0.0467
-4.250 -0.1621 0.02491 0.01900 -0.0537 0.7523 0.0509
-4.000 -0.1388 0.02196 0.01608 -0.0537 0.7382 0.0518
-3.750 -0.1135 0.02081 0.01489 -0.0535 0.7227 0.0527
-3.500 -0.0874 0.01999 0.01393 -0.0530 0.7058 0.0551
-3.250 -0.0585 0.01630 0.00947 -0.0511 0.6935 0.0402
-3.000 -0.0318 0.01528 0.00834 -0.0506 0.6774 0.0400
-2.750 -0.0048 0.01453 0.00745 -0.0502 0.6604 0.0402
-2.500 0.0217 0.01376 0.00657 -0.0497 0.6398 0.0401
-2.250 0.0478 0.01324 0.00589 -0.0490 0.6118 0.0402
-2.000 0.0741 0.01288 0.00538 -0.0485 0.5831 0.0405
-1.750 0.0993 0.01232 0.00472 -0.0479 0.5505 0.0409
-1.500 0.1241 0.01208 0.00432 -0.0473 0.5019 0.0415
-1.250 0.1437 0.01272 0.00427 -0.0462 0.3189 0.0423
-1.000 0.1669 0.01306 0.00423 -0.0456 0.2198 0.0436
-0.750 0.1930 0.01303 0.00405 -0.0452 0.1887 0.0448
-0.500 0.2195 0.01293 0.00384 -0.0449 0.1678 0.0457
-0.250 0.2452 0.01287 0.00364 -0.0447 0.1283 0.0471
0.000 0.2723 0.01282 0.00353 -0.0445 0.1209 0.0490
0.250 0.2997 0.01278 0.00344 -0.0443 0.1180 0.0511
0.500 0.3271 0.01268 0.00335 -0.0442 0.1166 0.0548
0.750 0.3546 0.01263 0.00330 -0.0441 0.1154 0.0605
1.000 0.3822 0.01256 0.00325 -0.0439 0.1145 0.0739
1.250 0.4060 0.01080 0.00326 -0.0443 0.1139 0.6744
1.500 0.4319 0.01084 0.00344 -0.0437 0.1133 0.7290
1.750 0.4583 0.01097 0.00360 -0.0432 0.1128 0.7580
2.000 0.4843 0.01112 0.00379 -0.0427 0.1122 0.7794
2.250 0.5101 0.01126 0.00396 -0.0421 0.1114 0.7988
2.500 0.5352 0.01142 0.00417 -0.0413 0.1102 0.8201
2.750 0.5599 0.01159 0.00437 -0.0404 0.1090 0.8378
3.000 0.5854 0.01178 0.00456 -0.0399 0.1082 0.8504
3.250 0.6102 0.01197 0.00475 -0.0392 0.1075 0.8602
3.500 0.6353 0.01220 0.00497 -0.0386 0.1068 0.8703
3.750 0.6587 0.01246 0.00523 -0.0377 0.1060 0.8810
4.000 0.6824 0.01269 0.00546 -0.0369 0.1053 0.8918
4.250 0.7063 0.01286 0.00565 -0.0360 0.1047 0.9038
4.500 0.7286 0.01301 0.00584 -0.0348 0.1040 0.9162
4.750 0.7500 0.01317 0.00603 -0.0334 0.1032 0.9310
5.000 0.7706 0.01333 0.00621 -0.0319 0.1026 0.9500
5.250 0.7985 0.01355 0.00644 -0.0320 0.1018 0.9725
5.500 0.8306 0.01389 0.00675 -0.0332 0.1008 1.0000
5.750 0.8564 0.01433 0.00713 -0.0332 0.1000 1.0000
6.000 0.8824 0.01468 0.00746 -0.0332 0.0990 1.0000
6.250 0.9091 0.01492 0.00771 -0.0332 0.0982 1.0000
6.500 0.9350 0.01519 0.00800 -0.0331 0.0971 1.0000
6.750 0.9602 0.01551 0.00831 -0.0328 0.0960 1.0000
7.000 0.9844 0.01589 0.00866 -0.0325 0.0948 1.0000
7.250 1.0074 0.01641 0.00914 -0.0320 0.0937 1.0000
7.500 1.0334 0.01653 0.00933 -0.0318 0.0924 1.0000
7.750 1.0583 0.01675 0.00958 -0.0314 0.0906 1.0000
8.000 1.0817 0.01707 0.00988 -0.0309 0.0890 1.0000
8.250 1.1068 0.01724 0.01012 -0.0306 0.0872 1.0000
8.500 1.1327 0.01730 0.01023 -0.0304 0.0846 1.0000
8.750 1.1598 0.01729 0.01028 -0.0303 0.0810 1.0000
9.000 1.1864 0.01733 0.01042 -0.0301 0.0615 1.0000
9.250 1.2096 0.01766 0.01045 -0.0297 0.0534 1.0000
9.500 1.2265 0.01840 0.01123 -0.0283 0.0508 1.0000
9.750 1.2417 0.01911 0.01198 -0.0266 0.0490 1.0000
10.000 1.2560 0.01979 0.01269 -0.0247 0.0475 1.0000
10.250 1.2681 0.02058 0.01350 -0.0227 0.0465 1.0000
10.500 1.2835 0.02117 0.01415 -0.0212 0.0454 1.0000
10.750 1.2970 0.02189 0.01491 -0.0195 0.0445 1.0000
11.000 1.3091 0.02271 0.01577 -0.0178 0.0438 1.0000
11.250 1.3223 0.02350 0.01661 -0.0163 0.0430 1.0000
11.500 1.3360 0.02428 0.01745 -0.0150 0.0423 1.0000
11.750 1.3492 0.02512 0.01835 -0.0137 0.0415 1.0000
12.000 1.3618 0.02603 0.01930 -0.0125 0.0409 1.0000
12.250 1.3732 0.02705 0.02036 -0.0113 0.0403 1.0000
12.500 1.3849 0.02807 0.02146 -0.0102 0.0398 1.0000
12.750 1.3949 0.02925 0.02270 -0.0090 0.0394 1.0000
13.000 1.4052 0.03045 0.02396 -0.0080 0.0389 1.0000
13.250 1.4158 0.03165 0.02523 -0.0072 0.0384 1.0000
13.500 1.4255 0.03296 0.02659 -0.0063 0.0379 1.0000
13.750 1.4326 0.03453 0.02822 -0.0056 0.0375 1.0000
14.000 1.4380 0.03631 0.03007 -0.0048 0.0372 1.0000
14.250 1.4435 0.03814 0.03199 -0.0042 0.0369 1.0000
14.500 1.4480 0.04013 0.03406 -0.0037 0.0366 1.0000
14.750 1.4517 0.04226 0.03627 -0.0034 0.0363 1.0000
15.000 1.4547 0.04453 0.03863 -0.0032 0.0360 1.0000
15.250 1.4567 0.04699 0.04117 -0.0032 0.0358 1.0000
15.500 1.4577 0.04962 0.04389 -0.0034 0.0355 1.0000
15.750 1.4579 0.05247 0.04682 -0.0037 0.0352 1.0000
16.000 1.4568 0.05558 0.05001 -0.0043 0.0350 1.0000
16.250 1.4544 0.05896 0.05347 -0.0050 0.0348 1.0000
16.500 1.4509 0.06260 0.05717 -0.0060 0.0346 1.0000
16.750 1.4473 0.06639 0.06105 -0.0072 0.0344 1.0000
17.000 1.4444 0.07024 0.06501 -0.0086 0.0342 1.0000
17.250 1.4404 0.07438 0.06927 -0.0102 0.0340 1.0000
17.500 1.4360 0.07874 0.07375 -0.0121 0.0338 1.0000
17.750 1.4310 0.08329 0.07841 -0.0141 0.0336 1.0000
18.000 1.4255 0.08806 0.08330 -0.0164 0.0333 1.0000
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