NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Reynolds number: 200,000 Max Cl/Cd: 61.47 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc12b3-il-200000-n5.txt Download as CSV file: xf-rc12b3-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-12(B)3 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5456 0.08502 0.08140 -0.0354 1.0000 0.0240
-10.250 -0.5837 0.07195 0.06837 -0.0467 1.0000 0.0236
-10.000 -0.7228 0.04817 0.04394 -0.0466 1.0000 0.0230
-9.750 -0.7438 0.04380 0.03924 -0.0422 0.9956 0.0233
-9.500 -0.7375 0.03994 0.03498 -0.0418 0.9860 0.0239
-9.250 -0.7294 0.03617 0.03073 -0.0408 0.9776 0.0246
-9.000 -0.7173 0.03255 0.02653 -0.0399 0.9711 0.0254
-8.750 -0.7033 0.02979 0.02325 -0.0385 0.9633 0.0260
-8.500 -0.6827 0.02757 0.02057 -0.0379 0.9581 0.0266
-8.250 -0.6621 0.02599 0.01876 -0.0371 0.9517 0.0272
-8.000 -0.6386 0.02493 0.01760 -0.0367 0.9461 0.0279
-7.750 -0.6144 0.02400 0.01653 -0.0364 0.9412 0.0287
-7.500 -0.5919 0.02316 0.01555 -0.0356 0.9347 0.0297
-7.250 -0.5677 0.02231 0.01452 -0.0350 0.9297 0.0311
-7.000 -0.5438 0.02144 0.01342 -0.0343 0.9243 0.0324
-6.750 -0.5206 0.02054 0.01242 -0.0336 0.9185 0.0336
-6.500 -0.4967 0.01990 0.01173 -0.0329 0.9137 0.0349
-6.250 -0.4730 0.01931 0.01108 -0.0322 0.9080 0.0364
-6.000 -0.4488 0.01871 0.01037 -0.0314 0.9025 0.0382
-5.750 -0.4244 0.01814 0.00968 -0.0307 0.8980 0.0405
-5.500 -0.4007 0.01768 0.00924 -0.0300 0.8920 0.0430
-5.250 -0.3763 0.01727 0.00877 -0.0293 0.8866 0.0460
-5.000 -0.3518 0.01680 0.00821 -0.0285 0.8823 0.0489
-4.750 -0.3277 0.01639 0.00782 -0.0279 0.8760 0.0527
-4.500 -0.3029 0.01607 0.00744 -0.0273 0.8707 0.0573
-4.250 -0.2787 0.01567 0.00703 -0.0265 0.8665 0.0620
-4.000 -0.2538 0.01540 0.00674 -0.0259 0.8601 0.0679
-3.750 -0.2294 0.01506 0.00640 -0.0252 0.8549 0.0739
-3.500 -0.2044 0.01478 0.00609 -0.0245 0.8505 0.0812
-3.250 -0.1798 0.01450 0.00584 -0.0240 0.8440 0.0891
-3.000 -0.1548 0.01425 0.00556 -0.0233 0.8387 0.0981
-2.750 -0.1300 0.01398 0.00531 -0.0226 0.8338 0.1095
-2.500 -0.1053 0.01374 0.00512 -0.0221 0.8271 0.1231
-2.250 -0.0805 0.01348 0.00489 -0.0214 0.8218 0.1405
-2.000 -0.0560 0.01321 0.00471 -0.0207 0.8159 0.1634
-1.750 -0.0322 0.01290 0.00454 -0.0199 0.8093 0.2000
-1.500 -0.0097 0.01244 0.00431 -0.0188 0.8042 0.2678
-1.250 0.0835 0.01108 0.00531 -0.0316 0.8019 0.8769
-1.000 0.1059 0.01141 0.00558 -0.0299 0.7942 0.9122
-0.750 0.1341 0.01171 0.00576 -0.0293 0.7882 0.9327
-0.500 0.1717 0.01203 0.00602 -0.0309 0.7801 0.9473
-0.250 0.2111 0.01227 0.00615 -0.0330 0.7735 0.9599
0.000 0.2574 0.01247 0.00630 -0.0366 0.7650 0.9722
0.250 0.3167 0.01247 0.00621 -0.0431 0.7578 0.9848
0.500 0.3617 0.01233 0.00603 -0.0469 0.7482 0.9909
0.750 0.3922 0.01226 0.00589 -0.0475 0.7390 0.9934
1.000 0.4233 0.01216 0.00573 -0.0483 0.7284 0.9950
1.250 0.4545 0.01206 0.00560 -0.0492 0.7169 0.9964
1.500 0.4854 0.01198 0.00547 -0.0500 0.7054 0.9980
1.750 0.5158 0.01192 0.00536 -0.0506 0.6935 0.9995
2.000 0.5429 0.01190 0.00530 -0.0506 0.6808 1.0000
2.250 0.5681 0.01190 0.00527 -0.0502 0.6672 1.0000
2.500 0.5933 0.01191 0.00524 -0.0497 0.6526 1.0000
2.750 0.6183 0.01194 0.00523 -0.0492 0.6362 1.0000
3.000 0.6431 0.01200 0.00522 -0.0487 0.6170 1.0000
3.250 0.6679 0.01207 0.00523 -0.0481 0.5959 1.0000
3.500 0.6925 0.01218 0.00528 -0.0476 0.5750 1.0000
3.750 0.7169 0.01231 0.00534 -0.0470 0.5535 1.0000
4.000 0.7410 0.01247 0.00542 -0.0464 0.5301 1.0000
4.250 0.7646 0.01268 0.00553 -0.0458 0.5034 1.0000
4.500 0.7877 0.01295 0.00569 -0.0450 0.4741 1.0000
4.750 0.8103 0.01325 0.00587 -0.0442 0.4451 1.0000
5.000 0.8325 0.01357 0.00608 -0.0434 0.4177 1.0000
5.250 0.8545 0.01390 0.00634 -0.0425 0.3908 1.0000
5.500 0.8758 0.01427 0.00661 -0.0416 0.3645 1.0000
5.750 0.8965 0.01468 0.00691 -0.0405 0.3385 1.0000
6.000 0.9168 0.01509 0.00724 -0.0394 0.3122 1.0000
6.250 0.9365 0.01553 0.00760 -0.0382 0.2869 1.0000
6.500 0.9553 0.01601 0.00799 -0.0368 0.2623 1.0000
6.750 0.9737 0.01649 0.00839 -0.0354 0.2379 1.0000
7.000 0.9912 0.01701 0.00882 -0.0338 0.2151 1.0000
7.250 1.0082 0.01754 0.00929 -0.0322 0.1931 1.0000
7.500 1.0241 0.01811 0.00978 -0.0304 0.1734 1.0000
7.750 1.0398 0.01867 0.01029 -0.0285 0.1557 1.0000
8.000 1.0544 0.01925 0.01082 -0.0264 0.1395 1.0000
8.250 1.0682 0.01985 0.01138 -0.0243 0.1244 1.0000
8.500 1.0810 0.02047 0.01198 -0.0219 0.1113 1.0000
8.750 1.0925 0.02111 0.01260 -0.0193 0.1001 1.0000
9.000 1.1022 0.02180 0.01325 -0.0165 0.0903 1.0000
9.250 1.1120 0.02241 0.01390 -0.0136 0.0820 1.0000
9.500 1.1192 0.02309 0.01458 -0.0104 0.0754 1.0000
9.750 1.1220 0.02372 0.01525 -0.0063 0.0697 1.0000
10.000 1.1229 0.02443 0.01597 -0.0020 0.0653 1.0000
10.250 1.1267 0.02511 0.01672 0.0016 0.0612 1.0000
10.500 1.1291 0.02596 0.01758 0.0053 0.0574 1.0000
10.750 1.1325 0.02684 0.01851 0.0086 0.0542 1.0000
11.000 1.1374 0.02771 0.01947 0.0116 0.0510 1.0000
11.250 1.1408 0.02874 0.02052 0.0145 0.0482 1.0000
11.500 1.1425 0.02994 0.02176 0.0175 0.0459 1.0000
11.750 1.1477 0.03100 0.02293 0.0199 0.0438 1.0000
12.000 1.1521 0.03218 0.02420 0.0223 0.0417 1.0000
12.250 1.1553 0.03350 0.02558 0.0245 0.0398 1.0000
12.500 1.1553 0.03514 0.02724 0.0268 0.0382 1.0000
12.750 1.1597 0.03654 0.02875 0.0287 0.0366 1.0000
13.000 1.1634 0.03805 0.03038 0.0304 0.0351 1.0000
13.250 1.1664 0.03970 0.03213 0.0319 0.0337 1.0000
13.500 1.1683 0.04151 0.03401 0.0333 0.0324 1.0000
13.750 1.1672 0.04368 0.03623 0.0346 0.0312 1.0000
14.000 1.1681 0.04576 0.03842 0.0357 0.0301 1.0000
14.250 1.1702 0.04784 0.04064 0.0366 0.0290 1.0000
14.500 1.1711 0.05011 0.04303 0.0372 0.0280 1.0000
14.750 1.1712 0.05256 0.04558 0.0377 0.0270 1.0000
15.000 1.1702 0.05524 0.04835 0.0379 0.0261 1.0000
15.250 1.1670 0.05828 0.05147 0.0379 0.0254 1.0000
15.500 1.1630 0.06152 0.05480 0.0378 0.0247 1.0000
15.750 1.1613 0.06464 0.05810 0.0375 0.0241 1.0000
16.000 1.1584 0.06802 0.06163 0.0370 0.0234 1.0000
16.250 1.1546 0.07165 0.06540 0.0362 0.0227 1.0000
16.500 1.1498 0.07550 0.06938 0.0352 0.0221 1.0000
16.750 1.1444 0.07958 0.07358 0.0340 0.0216 1.0000
17.000 1.1381 0.08390 0.07801 0.0325 0.0211 1.0000
17.250 1.1310 0.08845 0.08265 0.0308 0.0207 1.0000
17.500 1.1230 0.09317 0.08746 0.0290 0.0203 1.0000
17.750 1.1145 0.09811 0.09251 0.0270 0.0199 1.0000
18.000 1.1045 0.10353 0.09811 0.0247 0.0195 1.0000
18.250 1.0936 0.10923 0.10399 0.0221 0.0192 1.0000
18.500 1.0819 0.11518 0.11010 0.0193 0.0188 1.0000
18.750 1.0694 0.12146 0.11654 0.0162 0.0185 1.0000
19.000 1.0560 0.12809 0.12332 0.0128 0.0182 1.0000
19.250 1.0416 0.13514 0.13051 0.0091 0.0180 1.0000
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Polar data table (+)
Polar graphs
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