NACA 66(3)-218 (naca663218-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(3)-218 (naca663218-il) Reynolds number: 100,000 Max Cl/Cd: 22.87 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca663218-il-100000-n5.txt Download as CSV file: xf-naca663218-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(3)-218
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5410 0.10027 0.09489 -0.0799 1.0000 0.0362
-14.500 -0.5828 0.08783 0.08225 -0.0884 0.9884 0.0356
-14.250 -0.6149 0.07927 0.07342 -0.0941 0.9801 0.0353
-14.000 -0.6404 0.07256 0.06642 -0.0980 0.9737 0.0351
-13.750 -0.6586 0.06726 0.06083 -0.1003 0.9671 0.0350
-13.500 -0.6725 0.06255 0.05580 -0.1020 0.9618 0.0350
-13.250 -0.6826 0.05872 0.05165 -0.1026 0.9550 0.0351
-13.000 -0.6885 0.05520 0.04779 -0.1029 0.9495 0.0353
-12.750 -0.6912 0.05233 0.04460 -0.1024 0.9428 0.0354
-12.500 -0.6904 0.04967 0.04162 -0.1018 0.9368 0.0356
-12.250 -0.6869 0.04729 0.03892 -0.1009 0.9311 0.0360
-12.000 -0.6829 0.04526 0.03657 -0.0994 0.9245 0.0366
-11.750 -0.6757 0.04337 0.03430 -0.0982 0.9194 0.0375
-11.500 -0.6631 0.04171 0.03239 -0.0972 0.9142 0.0381
-11.250 -0.6427 0.04025 0.03085 -0.0971 0.9098 0.0389
-11.000 -0.6214 0.03894 0.02943 -0.0970 0.9061 0.0398
-10.750 -0.5961 0.03759 0.02792 -0.0973 0.9033 0.0406
-10.500 -0.5704 0.03638 0.02657 -0.0975 0.9003 0.0417
-10.250 -0.5449 0.03536 0.02541 -0.0974 0.8968 0.0428
-10.000 -0.5199 0.03447 0.02435 -0.0973 0.8935 0.0443
-9.750 -0.4956 0.03357 0.02350 -0.0974 0.8906 0.0459
-9.500 -0.4737 0.03278 0.02269 -0.0971 0.8879 0.0481
-9.250 -0.4509 0.03203 0.02187 -0.0969 0.8856 0.0501
-9.000 -0.4320 0.03140 0.02115 -0.0961 0.8820 0.0520
-8.750 -0.4174 0.03069 0.02046 -0.0949 0.8782 0.0539
-8.500 -0.4028 0.03004 0.01980 -0.0936 0.8746 0.0567
-8.250 -0.3870 0.02943 0.01910 -0.0924 0.8716 0.0606
-8.000 -0.3732 0.02870 0.01838 -0.0910 0.8690 0.0643
-7.750 -0.3602 0.02818 0.01780 -0.0894 0.8660 0.0694
-7.500 -0.3496 0.02769 0.01735 -0.0875 0.8624 0.0760
-7.250 -0.3376 0.02717 0.01687 -0.0857 0.8591 0.0866
-7.000 -0.3258 0.02654 0.01642 -0.0838 0.8563 0.1104
-6.750 -0.3176 0.02567 0.01601 -0.0814 0.8538 0.1780
-6.500 -0.3185 0.02460 0.01552 -0.0778 0.8514 0.2803
-6.250 -0.3288 0.02405 0.01540 -0.0724 0.8468 0.3550
-6.000 -0.2792 0.02574 0.01825 -0.0723 0.8465 0.5421
-5.750 -0.2438 0.02760 0.02014 -0.0713 0.8444 0.5983
-5.500 -0.2536 0.02766 0.02017 -0.0656 0.8400 0.6323
-5.250 -0.2510 0.02851 0.02097 -0.0607 0.8371 0.6621
-5.000 -0.2542 0.02908 0.02147 -0.0549 0.8345 0.6859
-4.750 -0.1967 0.03070 0.02291 -0.0582 0.8344 0.6949
-4.500 -0.2014 0.03111 0.02328 -0.0529 0.8308 0.7065
-4.250 -0.2301 0.03161 0.02379 -0.0434 0.8246 0.7193
-4.000 -0.1866 0.03223 0.02428 -0.0457 0.8236 0.7236
-3.500 -0.1586 0.03277 0.02464 -0.0411 0.8193 0.7394
-3.250 -0.1189 0.03308 0.02484 -0.0432 0.8186 0.7426
-3.000 -0.1009 0.03318 0.02485 -0.0418 0.8171 0.7489
-2.750 -0.1435 0.03392 0.02565 -0.0298 0.8098 0.7585
-2.250 -0.1560 0.03405 0.02570 -0.0188 0.8026 0.7735
-2.000 -0.1220 0.03421 0.02578 -0.0201 0.8014 0.7757
-1.500 -0.1687 0.03440 0.02596 -0.0032 0.7906 0.7912
-1.250 -0.1460 0.03458 0.02609 -0.0026 0.7881 0.7937
-1.000 -0.1239 0.03462 0.02607 -0.0020 0.7858 0.7967
-0.750 -0.1048 0.03449 0.02589 -0.0010 0.7839 0.8005
-0.500 -0.0970 0.03386 0.02518 0.0017 0.7818 0.8067
-0.250 -0.1174 0.03434 0.02569 0.0094 0.7740 0.8106
0.000 -0.0987 0.03438 0.02569 0.0105 0.7708 0.8130
0.250 -0.0759 0.03431 0.02559 0.0109 0.7684 0.8156
0.500 -0.0520 0.03414 0.02538 0.0110 0.7664 0.8184
0.750 -0.0359 0.03391 0.02511 0.0123 0.7636 0.8218
1.000 -0.0487 0.03397 0.02516 0.0182 0.7553 0.8262
1.250 -0.0238 0.03393 0.02511 0.0182 0.7523 0.8276
1.500 0.0048 0.03385 0.02503 0.0176 0.7501 0.8289
1.750 0.0360 0.03377 0.02494 0.0166 0.7483 0.8305
2.000 0.0289 0.03406 0.02525 0.0215 0.7392 0.8342
2.250 0.0533 0.03396 0.02515 0.0215 0.7357 0.8361
2.500 0.0824 0.03381 0.02501 0.0207 0.7333 0.8379
2.750 0.1057 0.03374 0.02494 0.0208 0.7298 0.8400
3.000 0.1106 0.03395 0.02518 0.0235 0.7212 0.8427
3.250 0.1395 0.03391 0.02518 0.0230 0.7180 0.8442
3.500 0.1723 0.03379 0.02510 0.0220 0.7158 0.8456
3.750 0.1758 0.03417 0.02554 0.0250 0.7061 0.8482
4.000 0.2040 0.03407 0.02550 0.0246 0.7022 0.8499
4.250 0.2380 0.03383 0.02532 0.0234 0.6997 0.8514
4.500 0.2438 0.03417 0.02570 0.0259 0.6892 0.8544
4.750 0.2753 0.03391 0.02551 0.0250 0.6853 0.8563
5.000 0.3115 0.03351 0.02519 0.0236 0.6828 0.8579
5.250 0.3172 0.03387 0.02563 0.0262 0.6708 0.8605
5.500 0.3516 0.03344 0.02532 0.0254 0.6675 0.8620
5.750 0.3600 0.03376 0.02573 0.0277 0.6557 0.8651
6.000 0.3949 0.03318 0.02527 0.0269 0.6517 0.8671
6.250 0.4064 0.03336 0.02555 0.0288 0.6391 0.8704
6.500 0.4374 0.03283 0.02515 0.0284 0.6331 0.8727
6.750 0.4560 0.03278 0.02521 0.0292 0.6218 0.8757
7.000 0.4708 0.03285 0.02543 0.0308 0.6092 0.8782
7.500 0.5163 0.03130 0.02411 0.0334 0.5754 0.8838
7.750 0.5411 0.02998 0.02278 0.0350 0.5346 0.8870
8.000 0.5937 0.02729 0.01977 0.0344 0.4636 0.8887
8.250 0.6170 0.02698 0.01895 0.0358 0.3798 0.8919
8.500 0.6207 0.02790 0.01946 0.0387 0.3080 0.8956
8.750 0.6225 0.02912 0.02028 0.0414 0.2365 0.9002
9.000 0.6250 0.03052 0.02118 0.0436 0.1602 0.9051
9.250 0.6313 0.03182 0.02209 0.0454 0.1063 0.9096
9.500 0.6410 0.03294 0.02305 0.0469 0.0829 0.9140
9.750 0.6520 0.03402 0.02408 0.0481 0.0709 0.9189
10.000 0.6633 0.03510 0.02516 0.0492 0.0628 0.9241
10.250 0.6744 0.03623 0.02631 0.0502 0.0579 0.9293
10.500 0.6872 0.03731 0.02747 0.0510 0.0538 0.9353
10.750 0.7006 0.03845 0.02866 0.0515 0.0505 0.9411
11.000 0.7147 0.03965 0.02994 0.0518 0.0478 0.9475
11.250 0.7318 0.04083 0.03122 0.0517 0.0450 0.9541
11.500 0.7498 0.04210 0.03253 0.0513 0.0431 0.9612
11.750 0.7707 0.04336 0.03382 0.0505 0.0415 0.9685
12.000 0.7943 0.04448 0.03509 0.0496 0.0396 0.9782
12.250 0.8134 0.04555 0.03624 0.0492 0.0378 1.0000
12.500 0.8307 0.04675 0.03744 0.0492 0.0365 1.0000
12.750 0.8525 0.04798 0.03862 0.0489 0.0355 1.0000
13.000 0.8740 0.04940 0.04024 0.0488 0.0345 1.0000
13.250 0.8941 0.05099 0.04201 0.0487 0.0337 1.0000
13.500 0.9125 0.05276 0.04395 0.0486 0.0331 1.0000
13.750 0.9276 0.05476 0.04614 0.0487 0.0324 1.0000
14.000 0.9395 0.05687 0.04843 0.0488 0.0320 1.0000
14.250 0.9484 0.05919 0.05092 0.0490 0.0315 1.0000
14.500 0.9546 0.06154 0.05341 0.0492 0.0310 1.0000
14.750 0.9600 0.06398 0.05598 0.0494 0.0305 1.0000
15.000 0.9653 0.06652 0.05857 0.0494 0.0300 1.0000
15.250 0.9601 0.06987 0.06221 0.0497 0.0299 1.0000
15.500 0.9441 0.07398 0.06666 0.0499 0.0295 1.0000
15.750 0.9306 0.07831 0.07126 0.0496 0.0294 1.0000
16.000 0.9162 0.08291 0.07611 0.0488 0.0294 1.0000
16.250 0.8948 0.08857 0.08207 0.0474 0.0292 1.0000
16.500 0.8764 0.09434 0.08807 0.0453 0.0293 1.0000
16.750 0.8532 0.10124 0.09520 0.0422 0.0293 1.0000
17.000 0.8276 0.10920 0.10337 0.0381 0.0294 1.0000
17.250 0.8008 0.11822 0.11258 0.0328 0.0296 1.0000
17.500 0.7725 0.12856 0.12308 0.0265 0.0298 1.0000
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