NACA 63-212 AIRFOIL (n63212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-212 AIRFOIL (n63212-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.89 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63212-il-1000000-n5.txt Download as CSV file: xf-n63212-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9225 0.08473 0.08249 -0.0238 1.0000 0.0078
-15.250 -0.9530 0.07394 0.07152 -0.0309 1.0000 0.0078
-15.000 -0.9767 0.06556 0.06297 -0.0365 1.0000 0.0078
-14.750 -0.9974 0.05848 0.05573 -0.0410 1.0000 0.0078
-14.500 -1.0109 0.05306 0.05016 -0.0442 1.0000 0.0078
-14.250 -1.0251 0.04796 0.04490 -0.0468 1.0000 0.0078
-14.000 -1.0319 0.04415 0.04095 -0.0485 1.0000 0.0079
-13.750 -1.0372 0.04078 0.03744 -0.0497 1.0000 0.0079
-13.500 -1.0386 0.03805 0.03459 -0.0503 1.0000 0.0080
-13.250 -1.0415 0.03533 0.03172 -0.0505 1.0000 0.0081
-13.000 -1.0404 0.03320 0.02947 -0.0503 1.0000 0.0082
-12.750 -1.0410 0.03102 0.02716 -0.0497 1.0000 0.0081
-12.500 -1.0377 0.02938 0.02540 -0.0487 1.0000 0.0082
-12.250 -1.0336 0.02796 0.02387 -0.0474 1.0000 0.0083
-12.000 -1.0296 0.02674 0.02254 -0.0454 1.0000 0.0084
-11.750 -1.0216 0.02569 0.02138 -0.0437 1.0000 0.0084
-11.500 -1.0090 0.02458 0.02017 -0.0425 1.0000 0.0085
-11.250 -0.9927 0.02379 0.01928 -0.0416 1.0000 0.0085
-11.000 -0.9757 0.02295 0.01835 -0.0407 1.0000 0.0086
-10.750 -0.9594 0.02189 0.01718 -0.0398 1.0000 0.0087
-10.500 -0.9467 0.02020 0.01534 -0.0385 1.0000 0.0089
-10.250 -0.9288 0.01920 0.01425 -0.0377 1.0000 0.0091
-10.000 -0.8972 0.01816 0.01313 -0.0396 0.9730 0.0092
-9.750 -0.8654 0.01729 0.01217 -0.0414 0.9517 0.0093
-9.500 -0.8417 0.01661 0.01137 -0.0412 0.9294 0.0094
-9.250 -0.8204 0.01603 0.01068 -0.0405 0.9108 0.0095
-9.000 -0.7985 0.01548 0.01002 -0.0398 0.8956 0.0096
-8.750 -0.7760 0.01494 0.00938 -0.0392 0.8827 0.0097
-8.500 -0.7528 0.01444 0.00880 -0.0386 0.8706 0.0098
-8.250 -0.7291 0.01395 0.00822 -0.0382 0.8593 0.0099
-8.000 -0.7049 0.01348 0.00767 -0.0378 0.8489 0.0100
-7.750 -0.6802 0.01305 0.00716 -0.0375 0.8392 0.0101
-7.500 -0.6551 0.01263 0.00666 -0.0373 0.8296 0.0103
-7.250 -0.6296 0.01225 0.00621 -0.0371 0.8206 0.0104
-7.000 -0.6038 0.01190 0.00580 -0.0369 0.8116 0.0107
-6.750 -0.5777 0.01155 0.00538 -0.0368 0.8032 0.0108
-6.250 -0.5247 0.01093 0.00464 -0.0366 0.7867 0.0110
-6.000 -0.4979 0.01066 0.00430 -0.0366 0.7786 0.0112
-5.750 -0.4707 0.01040 0.00399 -0.0366 0.7706 0.0113
-5.500 -0.4436 0.01014 0.00368 -0.0365 0.7630 0.0115
-5.250 -0.4162 0.00990 0.00340 -0.0366 0.7552 0.0119
-5.000 -0.3887 0.00970 0.00314 -0.0366 0.7477 0.0123
-4.750 -0.3609 0.00950 0.00292 -0.0367 0.7403 0.0127
-4.250 -0.3051 0.00917 0.00253 -0.0369 0.7256 0.0138
-4.000 -0.2771 0.00903 0.00236 -0.0370 0.7181 0.0148
-3.750 -0.2491 0.00884 0.00220 -0.0371 0.7112 0.0205
-3.500 -0.2210 0.00868 0.00204 -0.0372 0.7037 0.0288
-3.250 -0.1928 0.00852 0.00190 -0.0374 0.6968 0.0368
-3.000 -0.1648 0.00833 0.00176 -0.0375 0.6894 0.0542
-2.750 -0.1368 0.00810 0.00161 -0.0377 0.6826 0.0819
-2.500 -0.1088 0.00783 0.00147 -0.0379 0.6750 0.1219
-2.250 -0.0811 0.00744 0.00130 -0.0382 0.6685 0.1917
-2.000 -0.0538 0.00687 0.00110 -0.0385 0.6612 0.3007
-1.750 -0.0262 0.00644 0.00097 -0.0389 0.6541 0.3937
-1.500 0.0019 0.00615 0.00091 -0.0391 0.6469 0.4637
-1.250 0.0302 0.00600 0.00089 -0.0393 0.6398 0.5100
-1.000 0.0591 0.00594 0.00088 -0.0395 0.6327 0.5355
-0.750 0.0878 0.00592 0.00087 -0.0397 0.6256 0.5525
-0.500 0.1165 0.00587 0.00087 -0.0399 0.6187 0.5714
-0.250 0.1453 0.00586 0.00087 -0.0401 0.6112 0.5841
0.000 0.1742 0.00586 0.00087 -0.0403 0.6042 0.5930
0.250 0.2030 0.00588 0.00088 -0.0405 0.5962 0.6010
0.500 0.2318 0.00589 0.00090 -0.0406 0.5886 0.6093
0.750 0.2605 0.00592 0.00092 -0.0408 0.5798 0.6171
1.000 0.2893 0.00594 0.00095 -0.0410 0.5711 0.6255
1.250 0.3180 0.00599 0.00099 -0.0411 0.5618 0.6331
1.500 0.3467 0.00602 0.00103 -0.0413 0.5515 0.6416
1.750 0.3751 0.00608 0.00108 -0.0414 0.5375 0.6493
2.000 0.4034 0.00618 0.00114 -0.0415 0.5198 0.6574
2.250 0.4316 0.00627 0.00120 -0.0416 0.5022 0.6651
2.500 0.4594 0.00643 0.00128 -0.0417 0.4738 0.6733
2.750 0.4866 0.00665 0.00139 -0.0417 0.4348 0.6806
3.000 0.5130 0.00700 0.00154 -0.0416 0.3818 0.6887
3.250 0.5387 0.00745 0.00175 -0.0414 0.3186 0.6962
3.500 0.5646 0.00786 0.00198 -0.0413 0.2664 0.7041
3.750 0.5902 0.00832 0.00224 -0.0412 0.2126 0.7114
4.000 0.6152 0.00886 0.00254 -0.0409 0.1531 0.7196
4.250 0.6403 0.00936 0.00284 -0.0407 0.1039 0.7269
4.500 0.6662 0.00975 0.00311 -0.0406 0.0741 0.7351
4.750 0.6923 0.01008 0.00337 -0.0404 0.0538 0.7427
5.000 0.7186 0.01037 0.00362 -0.0403 0.0409 0.7511
5.250 0.7452 0.01062 0.00386 -0.0402 0.0343 0.7589
5.500 0.7718 0.01085 0.00411 -0.0401 0.0300 0.7678
5.750 0.7981 0.01111 0.00437 -0.0399 0.0263 0.7764
6.250 0.8506 0.01159 0.00492 -0.0396 0.0214 0.7944
6.500 0.8764 0.01188 0.00523 -0.0394 0.0191 0.8033
6.750 0.9022 0.01213 0.00553 -0.0392 0.0177 0.8128
7.000 0.9275 0.01243 0.00585 -0.0389 0.0162 0.8218
7.250 0.9524 0.01278 0.00623 -0.0385 0.0149 0.8312
7.500 0.9774 0.01307 0.00659 -0.0382 0.0143 0.8411
7.750 1.0020 0.01338 0.00696 -0.0377 0.0137 0.8516
8.250 1.0495 0.01408 0.00775 -0.0367 0.0124 0.8756
8.500 1.0720 0.01447 0.00820 -0.0359 0.0120 0.8890
8.750 1.0928 0.01496 0.00878 -0.0349 0.0114 0.9051
9.000 1.1134 0.01532 0.00923 -0.0337 0.0113 0.9250
9.250 1.1330 0.01567 0.00968 -0.0324 0.0111 0.9600
9.500 1.1577 0.01615 0.01022 -0.0323 0.0109 1.0000
9.750 1.1797 0.01666 0.01078 -0.0317 0.0107 1.0000
10.000 1.2008 0.01722 0.01139 -0.0309 0.0105 1.0000
10.250 1.2213 0.01779 0.01200 -0.0301 0.0103 1.0000
10.500 1.2410 0.01838 0.01264 -0.0292 0.0101 1.0000
10.750 1.2600 0.01898 0.01328 -0.0282 0.0099 1.0000
11.000 1.2785 0.01957 0.01391 -0.0272 0.0097 1.0000
11.250 1.2946 0.02020 0.01460 -0.0258 0.0095 1.0000
11.500 1.3074 0.02088 0.01533 -0.0238 0.0093 1.0000
11.750 1.3182 0.02167 0.01617 -0.0218 0.0092 1.0000
12.000 1.3283 0.02255 0.01711 -0.0198 0.0090 1.0000
12.250 1.3364 0.02362 0.01825 -0.0178 0.0089 1.0000
12.500 1.3434 0.02482 0.01954 -0.0160 0.0087 1.0000
12.750 1.3465 0.02641 0.02122 -0.0141 0.0085 1.0000
13.000 1.3563 0.02757 0.02245 -0.0129 0.0085 1.0000
13.250 1.3642 0.02894 0.02392 -0.0117 0.0085 1.0000
13.500 1.3725 0.03033 0.02539 -0.0107 0.0084 1.0000
13.750 1.3803 0.03182 0.02697 -0.0098 0.0083 1.0000
14.000 1.3868 0.03349 0.02873 -0.0091 0.0082 1.0000
14.250 1.3947 0.03509 0.03041 -0.0085 0.0080 1.0000
14.500 1.3974 0.03724 0.03267 -0.0079 0.0080 1.0000
14.750 1.4040 0.03908 0.03460 -0.0076 0.0079 1.0000
15.000 1.4064 0.04144 0.03705 -0.0074 0.0078 1.0000
15.250 1.4082 0.04394 0.03965 -0.0074 0.0077 1.0000
15.500 1.4098 0.04655 0.04236 -0.0076 0.0076 1.0000
15.750 1.4088 0.04957 0.04549 -0.0080 0.0075 1.0000
16.000 1.4074 0.05274 0.04878 -0.0087 0.0075 1.0000
16.250 1.4055 0.05614 0.05229 -0.0095 0.0074 1.0000
16.500 1.3999 0.06020 0.05647 -0.0108 0.0074 1.0000
16.750 1.3978 0.06394 0.06031 -0.0122 0.0073 1.0000
17.000 1.3910 0.06854 0.06504 -0.0141 0.0072 1.0000
17.250 1.3812 0.07384 0.07047 -0.0164 0.0072 1.0000
17.500 1.3718 0.07929 0.07604 -0.0191 0.0072 1.0000
17.750 1.3616 0.08511 0.08199 -0.0221 0.0071 1.0000
18.000 1.3488 0.09166 0.08867 -0.0256 0.0071 1.0000
18.250 1.3339 0.09885 0.09600 -0.0296 0.0070 1.0000
18.500 1.3162 0.10691 0.10420 -0.0343 0.0070 1.0000
18.750 1.2937 0.11630 0.11375 -0.0399 0.0070 1.0000
19.000 1.2709 0.12603 0.12363 -0.0458 0.0070 1.0000
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Polar data table (+)
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