NACA 63-212 AIRFOIL (n63212-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-212 AIRFOIL (n63212-il) Reynolds number: 500,000 Max Cl/Cd: 69.12 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63212-il-500000-n5.txt Download as CSV file: xf-n63212-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-212 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8010 0.08046 0.07779 -0.0267 1.0000 0.0104
-13.500 -0.8382 0.06827 0.06538 -0.0355 1.0000 0.0103
-13.250 -0.8668 0.05966 0.05656 -0.0415 1.0000 0.0103
-13.000 -0.8882 0.05322 0.04991 -0.0455 1.0000 0.0104
-12.750 -0.9054 0.04801 0.04451 -0.0480 1.0000 0.0103
-12.500 -0.9186 0.04381 0.04010 -0.0494 1.0000 0.0103
-12.250 -0.9276 0.04043 0.03653 -0.0499 1.0000 0.0104
-12.000 -0.9352 0.03745 0.03335 -0.0497 1.0000 0.0105
-11.750 -0.9393 0.03505 0.03076 -0.0488 1.0000 0.0106
-11.500 -0.9412 0.03307 0.02860 -0.0473 1.0000 0.0107
-11.250 -0.9406 0.03142 0.02676 -0.0452 1.0000 0.0109
-11.000 -0.9335 0.02969 0.02483 -0.0439 1.0000 0.0110
-10.750 -0.9223 0.02818 0.02314 -0.0427 1.0000 0.0111
-10.500 -0.9085 0.02686 0.02162 -0.0417 1.0000 0.0112
-10.250 -0.8932 0.02553 0.02013 -0.0408 1.0000 0.0113
-10.000 -0.8773 0.02413 0.01857 -0.0398 1.0000 0.0114
-9.750 -0.8616 0.02257 0.01688 -0.0388 1.0000 0.0116
-9.500 -0.8436 0.02142 0.01562 -0.0380 1.0000 0.0117
-9.250 -0.8252 0.02037 0.01450 -0.0371 1.0000 0.0118
-9.000 -0.7980 0.01936 0.01340 -0.0379 0.9858 0.0120
-8.750 -0.7661 0.01840 0.01235 -0.0397 0.9690 0.0122
-8.500 -0.7347 0.01755 0.01142 -0.0412 0.9540 0.0124
-8.250 -0.7066 0.01680 0.01058 -0.0419 0.9380 0.0126
-8.000 -0.6819 0.01619 0.00987 -0.0418 0.9223 0.0129
-7.750 -0.6585 0.01566 0.00925 -0.0413 0.9080 0.0132
-7.500 -0.6355 0.01511 0.00861 -0.0407 0.8950 0.0134
-7.250 -0.6121 0.01458 0.00798 -0.0401 0.8833 0.0136
-7.000 -0.5884 0.01409 0.00739 -0.0396 0.8722 0.0138
-6.750 -0.5639 0.01362 0.00684 -0.0392 0.8616 0.0141
-6.500 -0.5390 0.01320 0.00633 -0.0389 0.8519 0.0143
-6.250 -0.5138 0.01282 0.00586 -0.0385 0.8423 0.0145
-6.000 -0.4882 0.01241 0.00538 -0.0383 0.8330 0.0150
-5.750 -0.4623 0.01207 0.00498 -0.0381 0.8244 0.0155
-5.500 -0.4359 0.01177 0.00464 -0.0380 0.8154 0.0162
-5.250 -0.4092 0.01151 0.00432 -0.0379 0.8073 0.0171
-5.000 -0.3823 0.01126 0.00401 -0.0378 0.7987 0.0183
-4.750 -0.3554 0.01100 0.00373 -0.0377 0.7908 0.0212
-4.500 -0.3283 0.01076 0.00347 -0.0377 0.7826 0.0266
-4.250 -0.3010 0.01052 0.00321 -0.0377 0.7750 0.0345
-4.000 -0.2738 0.01027 0.00298 -0.0377 0.7670 0.0459
-3.750 -0.2467 0.00995 0.00274 -0.0378 0.7595 0.0711
-3.500 -0.2194 0.00965 0.00252 -0.0379 0.7516 0.1004
-3.250 -0.1923 0.00930 0.00230 -0.0380 0.7444 0.1441
-3.000 -0.1652 0.00889 0.00208 -0.0382 0.7366 0.2019
-2.750 -0.1390 0.00822 0.00181 -0.0384 0.7295 0.3135
-2.500 -0.1123 0.00767 0.00165 -0.0387 0.7219 0.4224
-2.250 -0.0846 0.00745 0.00158 -0.0388 0.7148 0.4770
-2.000 -0.0565 0.00731 0.00155 -0.0389 0.7072 0.5209
-1.750 -0.0285 0.00721 0.00152 -0.0389 0.7002 0.5560
-1.500 -0.0002 0.00714 0.00151 -0.0390 0.6926 0.5814
-1.250 0.0282 0.00712 0.00148 -0.0391 0.6857 0.5966
-1.000 0.0568 0.00710 0.00147 -0.0392 0.6782 0.6068
-0.750 0.0854 0.00710 0.00144 -0.0393 0.6710 0.6162
-0.500 0.1141 0.00709 0.00144 -0.0394 0.6637 0.6252
-0.250 0.1426 0.00711 0.00143 -0.0395 0.6564 0.6332
0.000 0.1714 0.00711 0.00144 -0.0397 0.6490 0.6418
0.250 0.1999 0.00713 0.00145 -0.0398 0.6417 0.6495
0.500 0.2286 0.00715 0.00147 -0.0399 0.6343 0.6578
0.750 0.2570 0.00717 0.00150 -0.0400 0.6266 0.6655
1.000 0.2857 0.00720 0.00154 -0.0402 0.6188 0.6739
1.250 0.3140 0.00724 0.00158 -0.0402 0.6106 0.6814
1.500 0.3426 0.00727 0.00163 -0.0403 0.6019 0.6899
1.750 0.3708 0.00733 0.00169 -0.0404 0.5930 0.6975
2.000 0.3992 0.00737 0.00176 -0.0405 0.5829 0.7057
2.250 0.4273 0.00743 0.00183 -0.0405 0.5713 0.7135
2.500 0.4553 0.00752 0.00190 -0.0405 0.5551 0.7217
2.750 0.4829 0.00761 0.00199 -0.0405 0.5374 0.7293
3.000 0.5103 0.00774 0.00208 -0.0404 0.5146 0.7377
3.250 0.5369 0.00794 0.00218 -0.0402 0.4791 0.7455
3.500 0.5631 0.00822 0.00233 -0.0400 0.4365 0.7539
3.750 0.5889 0.00852 0.00251 -0.0397 0.3936 0.7619
4.000 0.6136 0.00902 0.00276 -0.0394 0.3307 0.7704
4.250 0.6371 0.00963 0.00312 -0.0390 0.2619 0.7789
4.500 0.6601 0.01034 0.00353 -0.0385 0.1893 0.7876
4.750 0.6831 0.01100 0.00394 -0.0380 0.1303 0.7969
5.000 0.7067 0.01158 0.00433 -0.0376 0.0879 0.8060
5.250 0.7310 0.01204 0.00470 -0.0372 0.0623 0.8158
5.500 0.7557 0.01241 0.00505 -0.0368 0.0484 0.8251
5.750 0.7804 0.01276 0.00540 -0.0364 0.0394 0.8349
6.000 0.8048 0.01312 0.00577 -0.0359 0.0332 0.8453
6.250 0.8291 0.01343 0.00614 -0.0354 0.0295 0.8555
6.500 0.8528 0.01380 0.00654 -0.0348 0.0263 0.8664
6.750 0.8761 0.01416 0.00697 -0.0341 0.0241 0.8788
7.500 0.9397 0.01534 0.00833 -0.0308 0.0193 0.9275
7.750 0.9618 0.01571 0.00881 -0.0299 0.0185 0.9552
8.000 0.9885 0.01621 0.00936 -0.0302 0.0175 1.0000
8.250 1.0114 0.01675 0.00994 -0.0297 0.0167 1.0000
8.500 1.0336 0.01733 0.01055 -0.0292 0.0162 1.0000
8.750 1.0545 0.01800 0.01125 -0.0285 0.0154 1.0000
9.000 1.0736 0.01879 0.01209 -0.0276 0.0148 1.0000
9.250 1.0938 0.01944 0.01280 -0.0268 0.0145 1.0000
9.500 1.1127 0.02016 0.01359 -0.0258 0.0141 1.0000
9.750 1.1305 0.02092 0.01442 -0.0247 0.0138 1.0000
10.000 1.1470 0.02173 0.01531 -0.0235 0.0135 1.0000
10.250 1.1611 0.02253 0.01618 -0.0218 0.0132 1.0000
10.500 1.1735 0.02340 0.01711 -0.0200 0.0130 1.0000
10.750 1.1852 0.02432 0.01810 -0.0183 0.0127 1.0000
11.000 1.1965 0.02532 0.01917 -0.0167 0.0126 1.0000
11.250 1.2074 0.02637 0.02030 -0.0152 0.0123 1.0000
11.500 1.2178 0.02750 0.02150 -0.0138 0.0121 1.0000
11.750 1.2269 0.02879 0.02286 -0.0125 0.0118 1.0000
12.000 1.2340 0.03032 0.02447 -0.0112 0.0117 1.0000
12.250 1.2380 0.03229 0.02654 -0.0099 0.0114 1.0000
12.500 1.2469 0.03373 0.02810 -0.0090 0.0113 1.0000
12.750 1.2543 0.03540 0.02989 -0.0082 0.0111 1.0000
13.000 1.2605 0.03724 0.03186 -0.0074 0.0110 1.0000
13.250 1.2647 0.03937 0.03412 -0.0068 0.0109 1.0000
13.500 1.2686 0.04154 0.03644 -0.0063 0.0108 1.0000
13.750 1.2709 0.04398 0.03902 -0.0061 0.0106 1.0000
14.000 1.2722 0.04659 0.04178 -0.0060 0.0105 1.0000
14.250 1.2709 0.04963 0.04497 -0.0061 0.0103 1.0000
14.500 1.2699 0.05269 0.04819 -0.0066 0.0102 1.0000
14.750 1.2665 0.05620 0.05185 -0.0073 0.0101 1.0000
15.000 1.2611 0.06009 0.05590 -0.0083 0.0100 1.0000
15.250 1.2546 0.06433 0.06030 -0.0097 0.0100 1.0000
15.500 1.2479 0.06882 0.06494 -0.0116 0.0099 1.0000
15.750 1.2382 0.07403 0.07031 -0.0139 0.0098 1.0000
16.000 1.2286 0.07950 0.07593 -0.0166 0.0097 1.0000
16.250 1.2170 0.08564 0.08222 -0.0199 0.0096 1.0000
16.500 1.2003 0.09306 0.08983 -0.0241 0.0096 1.0000
16.750 1.1857 0.10050 0.09742 -0.0285 0.0095 1.0000
17.000 1.1639 0.10992 0.10704 -0.0342 0.0096 1.0000
17.250 1.1297 0.12293 0.12030 -0.0424 0.0096 1.0000
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