NASA/LANGLEY RC12-64C AIRFOIL (rc1264c-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC12-64C AIRFOIL (rc1264c-il) Reynolds number: 200,000 Max Cl/Cd: 46.15 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc1264c-il-200000-n5.txt Download as CSV file: xf-rc1264c-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC12-64C AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4216 0.08227 0.07864 -0.0466 1.0000 0.0369
-9.500 -0.5388 0.07695 0.07306 -0.0488 1.0000 0.0254
-9.250 -0.5636 0.07049 0.06654 -0.0516 1.0000 0.0248
-9.000 -0.5937 0.06587 0.06180 -0.0497 1.0000 0.0245
-8.750 -0.6220 0.06301 0.05886 -0.0446 1.0000 0.0244
-8.500 -0.6378 0.06064 0.05642 -0.0405 1.0000 0.0245
-8.250 -0.6510 0.05845 0.05415 -0.0362 1.0000 0.0247
-8.000 -0.6626 0.05626 0.05186 -0.0318 1.0000 0.0250
-7.750 -0.6806 0.05283 0.04812 -0.0268 0.9994 0.0268
-7.250 -0.6472 0.04758 0.04256 -0.0282 0.9919 0.0308
-7.000 -0.6306 0.04472 0.03943 -0.0285 0.9874 0.0341
-6.750 -0.6107 0.04198 0.03642 -0.0287 0.9836 0.0355
-6.500 -0.5929 0.03889 0.03292 -0.0280 0.9784 0.0361
-6.250 -0.5698 0.03603 0.02962 -0.0280 0.9750 0.0364
-6.000 -0.5488 0.03364 0.02693 -0.0272 0.9697 0.0364
-5.750 -0.5230 0.03130 0.02430 -0.0272 0.9659 0.0361
-5.500 -0.4937 0.02906 0.02177 -0.0277 0.9632 0.0356
-5.250 -0.4673 0.02704 0.01945 -0.0273 0.9589 0.0345
-5.000 -0.4389 0.02545 0.01739 -0.0268 0.9543 0.0325
-4.750 -0.4061 0.02373 0.01556 -0.0277 0.9517 0.0314
-4.500 -0.3721 0.02260 0.01399 -0.0283 0.9492 0.0296
-4.250 -0.3400 0.02125 0.01269 -0.0290 0.9460 0.0285
-4.000 -0.3118 0.02058 0.01177 -0.0285 0.9402 0.0264
-3.750 -0.2790 0.01947 0.01075 -0.0294 0.9368 0.0252
-3.500 -0.2453 0.01903 0.01012 -0.0302 0.9337 0.0237
-3.250 -0.2170 0.01817 0.00936 -0.0303 0.9286 0.0230
-3.000 -0.1893 0.01761 0.00879 -0.0301 0.9227 0.0221
-2.750 -0.1574 0.01733 0.00840 -0.0307 0.9184 0.0214
-2.500 -0.1301 0.01660 0.00778 -0.0306 0.9132 0.0210
-2.250 -0.1053 0.01605 0.00730 -0.0299 0.9060 0.0206
-2.000 -0.0764 0.01553 0.00682 -0.0301 0.9011 0.0202
-1.750 -0.0521 0.01515 0.00645 -0.0293 0.8934 0.0200
-1.500 -0.0251 0.01476 0.00607 -0.0290 0.8868 0.0198
-1.250 0.0017 0.01442 0.00572 -0.0287 0.8802 0.0197
-1.000 0.0270 0.01409 0.00538 -0.0280 0.8722 0.0199
-0.750 0.0549 0.01375 0.00501 -0.0279 0.8660 0.0210
-0.500 0.0795 0.01351 0.00475 -0.0271 0.8568 0.0218
-0.250 0.1080 0.01327 0.00447 -0.0270 0.8502 0.0219
0.000 0.1330 0.01312 0.00431 -0.0263 0.8405 0.0221
0.250 0.1610 0.01295 0.00411 -0.0261 0.8328 0.0224
0.500 0.1869 0.01283 0.00398 -0.0256 0.8224 0.0228
0.750 0.2136 0.01271 0.00385 -0.0251 0.8111 0.0233
1.000 0.2406 0.01260 0.00371 -0.0246 0.7984 0.0242
1.250 0.2565 0.01142 0.00348 -0.0225 0.7838 0.3450
1.500 0.2628 0.00989 0.00357 -0.0176 0.7685 0.7688
1.750 0.2913 0.00988 0.00371 -0.0170 0.7480 0.8295
2.000 0.3212 0.00997 0.00379 -0.0168 0.7225 0.8636
2.250 0.3520 0.01013 0.00390 -0.0168 0.6949 0.8909
2.500 0.3854 0.01042 0.00414 -0.0172 0.6680 0.9206
2.750 0.4155 0.01066 0.00426 -0.0173 0.6373 0.9348
3.000 0.4562 0.01109 0.00455 -0.0194 0.5981 0.9519
3.250 0.5106 0.01172 0.00489 -0.0246 0.5321 0.9684
3.500 0.5350 0.01213 0.00500 -0.0240 0.4720 0.9742
3.750 0.5638 0.01263 0.00516 -0.0246 0.3993 0.9769
4.000 0.5904 0.01323 0.00540 -0.0249 0.3271 0.9804
4.250 0.6148 0.01384 0.00570 -0.0247 0.2656 0.9850
4.500 0.6439 0.01442 0.00600 -0.0256 0.2109 0.9875
4.750 0.6725 0.01498 0.00634 -0.0263 0.1671 0.9906
5.000 0.7002 0.01553 0.00670 -0.0268 0.1337 0.9939
5.250 0.7298 0.01602 0.00706 -0.0277 0.1103 0.9964
5.500 0.7595 0.01649 0.00746 -0.0286 0.0967 0.9992
5.750 0.7802 0.01691 0.00783 -0.0276 0.0887 1.0000
6.000 0.7966 0.01726 0.00819 -0.0256 0.0831 1.0000
6.250 0.8112 0.01773 0.00861 -0.0233 0.0783 1.0000
6.500 0.8273 0.01805 0.00900 -0.0212 0.0749 1.0000
6.750 0.8427 0.01842 0.00940 -0.0190 0.0713 1.0000
7.000 0.8569 0.01886 0.00982 -0.0166 0.0679 1.0000
7.250 0.8709 0.01929 0.01028 -0.0141 0.0648 1.0000
7.500 0.8856 0.01967 0.01070 -0.0118 0.0618 1.0000
7.750 0.8994 0.02010 0.01114 -0.0094 0.0589 1.0000
8.000 0.9115 0.02065 0.01167 -0.0067 0.0563 1.0000
8.250 0.9254 0.02110 0.01218 -0.0043 0.0537 1.0000
8.500 0.9385 0.02160 0.01272 -0.0018 0.0514 1.0000
8.750 0.9499 0.02222 0.01333 0.0009 0.0493 1.0000
9.000 0.9613 0.02289 0.01403 0.0036 0.0472 1.0000
9.250 0.9751 0.02342 0.01466 0.0059 0.0448 1.0000
9.500 0.9872 0.02397 0.01526 0.0085 0.0426 1.0000
9.750 0.9979 0.02459 0.01589 0.0111 0.0409 1.0000
10.000 1.0104 0.02527 0.01666 0.0134 0.0392 1.0000
10.250 1.0235 0.02599 0.01748 0.0156 0.0375 1.0000
10.500 1.0365 0.02672 0.01828 0.0176 0.0360 1.0000
10.750 1.0492 0.02747 0.01909 0.0195 0.0348 1.0000
11.000 1.0602 0.02839 0.02003 0.0214 0.0338 1.0000
11.250 1.0726 0.02942 0.02119 0.0232 0.0327 1.0000
11.500 1.0846 0.03050 0.02239 0.0250 0.0317 1.0000
11.750 1.0959 0.03159 0.02359 0.0267 0.0307 1.0000
12.000 1.1066 0.03268 0.02477 0.0283 0.0298 1.0000
12.250 1.1164 0.03379 0.02597 0.0298 0.0290 1.0000
12.500 1.1250 0.03504 0.02728 0.0313 0.0283 1.0000
12.750 1.1314 0.03658 0.02886 0.0328 0.0277 1.0000
13.000 1.1389 0.03817 0.03066 0.0342 0.0271 1.0000
13.250 1.1448 0.03993 0.03260 0.0356 0.0265 1.0000
13.500 1.1491 0.04185 0.03470 0.0368 0.0259 1.0000
13.750 1.1518 0.04396 0.03698 0.0379 0.0255 1.0000
14.000 1.1530 0.04625 0.03944 0.0388 0.0251 1.0000
14.250 1.1528 0.04875 0.04211 0.0395 0.0248 1.0000
14.500 1.1508 0.05149 0.04502 0.0399 0.0244 1.0000
14.750 1.1473 0.05453 0.04823 0.0400 0.0242 1.0000
15.000 1.1420 0.05788 0.05175 0.0398 0.0240 1.0000
15.250 1.1348 0.06162 0.05566 0.0391 0.0238 1.0000
15.500 1.1256 0.06582 0.06004 0.0380 0.0236 1.0000
15.750 1.1140 0.07060 0.06500 0.0363 0.0235 1.0000
16.000 1.0994 0.07616 0.07075 0.0338 0.0234 1.0000
16.250 1.0811 0.08276 0.07755 0.0305 0.0233 1.0000
16.500 1.0556 0.09118 0.08621 0.0258 0.0233 1.0000
16.750 1.0078 0.10516 0.10052 0.0171 0.0234 1.0000
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