NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Reynolds number: 500,000 Max Cl/Cd: 83.51 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc12b3-il-500000.txt Download as CSV file: xf-rc12b3-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6272 0.06360 0.06129 -0.0515 1.0000 0.0245
-10.250 -0.6551 0.05731 0.05489 -0.0522 1.0000 0.0241
-10.000 -0.7099 0.04891 0.04622 -0.0477 1.0000 0.0235
-9.750 -0.7725 0.03349 0.02955 -0.0429 0.9856 0.0232
-9.500 -0.7633 0.02966 0.02520 -0.0416 0.9787 0.0237
-9.250 -0.7487 0.02699 0.02210 -0.0403 0.9719 0.0241
-9.000 -0.7322 0.02524 0.02002 -0.0387 0.9646 0.0244
-8.750 -0.7153 0.02383 0.01832 -0.0369 0.9576 0.0247
-8.500 -0.7007 0.02152 0.01574 -0.0350 0.9506 0.0253
-8.250 -0.6813 0.02059 0.01473 -0.0335 0.9442 0.0259
-8.000 -0.6606 0.01991 0.01395 -0.0322 0.9385 0.0265
-7.750 -0.6390 0.01926 0.01321 -0.0311 0.9323 0.0273
-7.500 -0.6176 0.01868 0.01252 -0.0298 0.9270 0.0282
-7.250 -0.5944 0.01805 0.01174 -0.0288 0.9216 0.0291
-7.000 -0.5710 0.01748 0.01104 -0.0279 0.9161 0.0297
-6.750 -0.5495 0.01625 0.00969 -0.0267 0.9115 0.0308
-6.500 -0.5255 0.01568 0.00910 -0.0260 0.9063 0.0319
-6.250 -0.5012 0.01524 0.00862 -0.0253 0.9010 0.0332
-6.000 -0.4772 0.01482 0.00812 -0.0244 0.8965 0.0346
-5.750 -0.4516 0.01455 0.00777 -0.0239 0.8916 0.0360
-5.500 -0.4285 0.01376 0.00699 -0.0230 0.8862 0.0384
-5.250 -0.4037 0.01345 0.00665 -0.0223 0.8817 0.0406
-5.000 -0.3782 0.01317 0.00631 -0.0218 0.8770 0.0429
-4.750 -0.3542 0.01261 0.00575 -0.0210 0.8716 0.0463
-4.500 -0.3286 0.01237 0.00549 -0.0205 0.8668 0.0499
-4.250 -0.3039 0.01203 0.00512 -0.0198 0.8625 0.0542
-4.000 -0.2779 0.01177 0.00488 -0.0194 0.8568 0.0591
-3.750 -0.2525 0.01149 0.00456 -0.0188 0.8518 0.0644
-3.500 -0.2270 0.01126 0.00434 -0.0183 0.8473 0.0711
-3.250 -0.2012 0.01099 0.00409 -0.0179 0.8414 0.0785
-3.000 -0.1750 0.01081 0.00390 -0.0175 0.8360 0.0864
-2.750 -0.1496 0.01056 0.00367 -0.0169 0.8313 0.0970
-2.500 -0.1236 0.01034 0.00350 -0.0165 0.8251 0.1090
-2.250 -0.0977 0.01012 0.00331 -0.0161 0.8195 0.1243
-2.000 -0.0720 0.00991 0.00315 -0.0156 0.8142 0.1455
-1.750 -0.0467 0.00963 0.00301 -0.0151 0.8076 0.1796
-1.500 -0.0233 0.00921 0.00283 -0.0143 0.8018 0.2508
-1.250 -0.0080 0.00824 0.00265 -0.0120 0.7951 0.4623
-1.000 0.0506 0.00733 0.00337 -0.0179 0.7904 0.9060
-0.750 0.0705 0.00769 0.00365 -0.0155 0.7845 0.9311
-0.500 0.1106 0.00820 0.00412 -0.0175 0.7776 0.9451
-0.250 0.1580 0.00868 0.00452 -0.0211 0.7714 0.9551
0.000 0.2079 0.00901 0.00479 -0.0255 0.7645 0.9622
0.250 0.2422 0.00927 0.00498 -0.0266 0.7564 0.9711
0.500 0.2977 0.00931 0.00497 -0.0325 0.7482 0.9754
0.750 0.3403 0.00946 0.00506 -0.0355 0.7396 0.9837
1.000 0.4049 0.00930 0.00488 -0.0434 0.7303 0.9920
1.250 0.4526 0.00913 0.00464 -0.0478 0.7209 0.9968
1.500 0.4871 0.00901 0.00449 -0.0494 0.7099 0.9986
1.750 0.5203 0.00892 0.00437 -0.0507 0.6980 1.0000
2.000 0.5463 0.00888 0.00429 -0.0505 0.6847 1.0000
2.250 0.5724 0.00887 0.00422 -0.0502 0.6706 1.0000
2.500 0.5985 0.00886 0.00417 -0.0500 0.6567 1.0000
2.750 0.6245 0.00887 0.00414 -0.0498 0.6420 1.0000
3.000 0.6506 0.00890 0.00412 -0.0496 0.6254 1.0000
3.250 0.6765 0.00895 0.00411 -0.0494 0.6062 1.0000
3.500 0.7022 0.00904 0.00412 -0.0492 0.5830 1.0000
3.750 0.7278 0.00915 0.00415 -0.0489 0.5582 1.0000
4.000 0.7532 0.00930 0.00420 -0.0486 0.5327 1.0000
4.250 0.7783 0.00948 0.00428 -0.0483 0.5054 1.0000
4.500 0.8032 0.00968 0.00438 -0.0480 0.4773 1.0000
4.750 0.8277 0.00993 0.00451 -0.0476 0.4475 1.0000
5.000 0.8518 0.01020 0.00467 -0.0472 0.4178 1.0000
5.250 0.8756 0.01050 0.00485 -0.0467 0.3885 1.0000
5.500 0.8989 0.01082 0.00505 -0.0461 0.3592 1.0000
5.750 0.9217 0.01116 0.00527 -0.0455 0.3309 1.0000
6.000 0.9444 0.01150 0.00550 -0.0448 0.3035 1.0000
6.250 0.9666 0.01186 0.00576 -0.0441 0.2770 1.0000
6.500 0.9882 0.01225 0.00604 -0.0432 0.2517 1.0000
6.750 1.0093 0.01266 0.00634 -0.0423 0.2265 1.0000
7.000 1.0300 0.01307 0.00666 -0.0413 0.2027 1.0000
7.500 1.0692 0.01399 0.00739 -0.0389 0.1587 1.0000
7.750 1.0877 0.01449 0.00780 -0.0375 0.1392 1.0000
8.000 1.1054 0.01501 0.00823 -0.0360 0.1215 1.0000
8.250 1.1228 0.01551 0.00867 -0.0343 0.1060 1.0000
8.500 1.1391 0.01605 0.00915 -0.0325 0.0925 1.0000
8.750 1.1543 0.01661 0.00967 -0.0306 0.0809 1.0000
9.000 1.1679 0.01724 0.01024 -0.0283 0.0710 1.0000
9.250 1.1823 0.01774 0.01075 -0.0261 0.0639 1.0000
9.500 1.1942 0.01833 0.01134 -0.0235 0.0578 1.0000
9.750 1.2047 0.01894 0.01194 -0.0207 0.0528 1.0000
10.000 1.2129 0.01957 0.01261 -0.0175 0.0489 1.0000
10.250 1.2198 0.02009 0.01316 -0.0139 0.0458 1.0000
10.500 1.2168 0.02070 0.01378 -0.0087 0.0434 1.0000
10.750 1.2139 0.02144 0.01456 -0.0036 0.0413 1.0000
11.000 1.2187 0.02200 0.01520 -0.0001 0.0394 1.0000
11.250 1.2225 0.02268 0.01592 0.0035 0.0375 1.0000
11.500 1.2231 0.02360 0.01685 0.0072 0.0357 1.0000
11.750 1.2218 0.02470 0.01802 0.0111 0.0341 1.0000
12.000 1.2281 0.02547 0.01886 0.0139 0.0328 1.0000
12.250 1.2331 0.02636 0.01982 0.0166 0.0314 1.0000
12.500 1.2369 0.02739 0.02088 0.0193 0.0301 1.0000
12.750 1.2346 0.02890 0.02242 0.0224 0.0288 1.0000
13.000 1.2365 0.03023 0.02384 0.0249 0.0278 1.0000
13.250 1.2426 0.03136 0.02505 0.0268 0.0267 1.0000
13.500 1.2470 0.03268 0.02644 0.0287 0.0257 1.0000
13.750 1.2506 0.03414 0.02797 0.0305 0.0247 1.0000
14.000 1.2499 0.03603 0.02990 0.0323 0.0239 1.0000
14.250 1.2428 0.03858 0.03251 0.0342 0.0231 1.0000
14.500 1.2483 0.04017 0.03422 0.0352 0.0224 1.0000
14.750 1.2517 0.04203 0.03618 0.0362 0.0216 1.0000
15.000 1.2540 0.04408 0.03831 0.0369 0.0209 1.0000
15.250 1.2557 0.04631 0.04061 0.0374 0.0202 1.0000
15.500 1.2548 0.04892 0.04329 0.0378 0.0196 1.0000
15.750 1.2476 0.05227 0.04670 0.0381 0.0190 1.0000
16.000 1.2442 0.05538 0.04993 0.0382 0.0185 1.0000
16.250 1.2443 0.05828 0.05295 0.0379 0.0181 1.0000
16.500 1.2426 0.06145 0.05624 0.0375 0.0176 1.0000
16.750 1.2399 0.06486 0.05976 0.0369 0.0172 1.0000
17.000 1.2364 0.06846 0.06346 0.0360 0.0168 1.0000
17.250 1.2323 0.07225 0.06734 0.0350 0.0165 1.0000
17.500 1.2273 0.07623 0.07141 0.0338 0.0161 1.0000
17.750 1.2210 0.08045 0.07572 0.0325 0.0159 1.0000
18.000 1.2132 0.08492 0.08026 0.0310 0.0156 1.0000
18.250 1.2028 0.08966 0.08507 0.0297 0.0152 1.0000
18.500 1.1934 0.09450 0.09004 0.0280 0.0150 1.0000
18.750 1.1855 0.09943 0.09511 0.0260 0.0149 1.0000
19.000 1.1767 0.10458 0.10040 0.0238 0.0147 1.0000
19.250 1.1672 0.10991 0.10586 0.0214 0.0145 1.0000
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