NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Reynolds number: 100,000 Max Cl/Cd: 50.84 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc12b3-il-100000.txt Download as CSV file: xf-rc12b3-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4482 0.09557 0.09065 -0.0308 1.0000 0.1241
-9.000 -0.4588 0.09149 0.08664 -0.0347 1.0000 0.1285
-8.750 -0.5043 0.08795 0.08317 -0.0394 1.0000 0.1307
-8.500 -0.5494 0.08702 0.08224 -0.0359 1.0000 0.1313
-8.250 -0.5884 0.08657 0.08170 -0.0303 1.0000 0.1316
-8.000 -0.5299 0.07911 0.07450 -0.0314 1.0000 0.1354
-7.750 -0.5408 0.07728 0.07270 -0.0275 1.0000 0.1375
-7.500 -0.5580 0.07549 0.07093 -0.0234 1.0000 0.1398
-7.250 -0.5789 0.07366 0.06907 -0.0194 1.0000 0.1430
-7.000 -0.6342 0.07403 0.06900 -0.0131 1.0000 0.1477
-6.750 -0.6175 0.06871 0.06394 -0.0120 1.0000 0.1498
-6.500 -0.6119 0.06639 0.06169 -0.0092 1.0000 0.1537
-6.250 -0.6392 0.06599 0.06078 -0.0045 1.0000 0.1639
-6.000 -0.6250 0.06159 0.05667 -0.0029 1.0000 0.1672
-5.750 -0.6211 0.05950 0.05454 -0.0002 1.0000 0.1735
-5.500 -0.6245 0.05694 0.05181 0.0027 1.0000 0.1831
-5.250 -0.6220 0.04451 0.03777 0.0066 1.0000 0.0984
-5.000 -0.6152 0.03975 0.03185 0.0114 1.0000 0.0873
-4.750 -0.5918 0.03623 0.02810 0.0111 0.9975 0.0891
-4.500 -0.5580 0.03438 0.02612 0.0093 0.9932 0.0924
-4.250 -0.5259 0.03209 0.02337 0.0085 0.9884 0.0938
-4.000 -0.4889 0.03049 0.02129 0.0068 0.9838 0.0987
-3.750 -0.4558 0.02885 0.01930 0.0057 0.9789 0.1038
-3.500 -0.4193 0.02785 0.01820 0.0038 0.9735 0.1111
-3.250 -0.3791 0.02676 0.01695 0.0012 0.9692 0.1205
-3.000 -0.3480 0.02620 0.01620 0.0005 0.9624 0.1312
-2.750 -0.3072 0.02533 0.01538 -0.0023 0.9576 0.1456
-2.500 -0.2748 0.02469 0.01481 -0.0035 0.9513 0.1619
-2.250 -0.2393 0.02398 0.01426 -0.0053 0.9452 0.1831
-2.000 0.0152 0.02184 0.01517 -0.0465 0.9722 1.0000
-1.750 0.0541 0.02190 0.01501 -0.0494 0.9643 1.0000
-1.500 0.0995 0.02192 0.01483 -0.0536 0.9576 1.0000
-1.250 0.1352 0.02200 0.01476 -0.0558 0.9487 1.0000
-1.000 0.1842 0.02196 0.01457 -0.0605 0.9426 1.0000
-0.750 0.2183 0.02205 0.01456 -0.0623 0.9330 1.0000
-0.500 0.2719 0.02188 0.01430 -0.0677 0.9275 1.0000
-0.250 0.3033 0.02197 0.01432 -0.0689 0.9169 1.0000
0.000 0.3534 0.02172 0.01402 -0.0733 0.9110 1.0000
0.250 0.3788 0.02184 0.01410 -0.0730 0.8990 1.0000
0.500 0.4080 0.02188 0.01412 -0.0733 0.8884 1.0000
0.750 0.4459 0.02165 0.01386 -0.0749 0.8803 1.0000
1.000 0.4677 0.02175 0.01396 -0.0737 0.8677 1.0000
1.250 0.4920 0.02176 0.01397 -0.0728 0.8560 1.0000
1.500 0.5245 0.02140 0.01360 -0.0728 0.8478 1.0000
1.750 0.5449 0.02142 0.01363 -0.0711 0.8344 1.0000
2.000 0.5664 0.02137 0.01361 -0.0695 0.8216 1.0000
2.250 0.5897 0.02121 0.01346 -0.0680 0.8098 1.0000
2.500 0.6165 0.02076 0.01301 -0.0666 0.8005 1.0000
2.750 0.6374 0.02066 0.01295 -0.0648 0.7867 1.0000
3.000 0.6590 0.02051 0.01283 -0.0630 0.7731 1.0000
3.250 0.6814 0.02028 0.01263 -0.0612 0.7596 1.0000
3.500 0.7044 0.01997 0.01236 -0.0594 0.7459 1.0000
3.750 0.7276 0.01963 0.01203 -0.0576 0.7315 1.0000
4.000 0.7507 0.01929 0.01171 -0.0557 0.7158 1.0000
4.250 0.7736 0.01901 0.01144 -0.0539 0.6991 1.0000
4.500 0.7967 0.01875 0.01121 -0.0522 0.6813 1.0000
4.750 0.8201 0.01850 0.01095 -0.0506 0.6626 1.0000
5.000 0.8436 0.01827 0.01069 -0.0489 0.6425 1.0000
5.250 0.8648 0.01822 0.01067 -0.0471 0.6177 1.0000
5.500 0.8868 0.01817 0.01057 -0.0454 0.5925 1.0000
5.750 0.9086 0.01820 0.01051 -0.0437 0.5658 1.0000
6.000 0.9286 0.01838 0.01065 -0.0419 0.5362 1.0000
6.250 0.9481 0.01865 0.01085 -0.0401 0.5057 1.0000
6.500 0.9666 0.01902 0.01111 -0.0382 0.4743 1.0000
6.750 0.9840 0.01948 0.01145 -0.0361 0.4424 1.0000
7.000 1.0002 0.02003 0.01188 -0.0340 0.4105 1.0000
7.250 1.0150 0.02066 0.01239 -0.0317 0.3788 1.0000
7.500 1.0284 0.02136 0.01296 -0.0292 0.3475 1.0000
7.750 1.0404 0.02212 0.01361 -0.0265 0.3167 1.0000
8.000 1.0509 0.02295 0.01432 -0.0237 0.2870 1.0000
8.250 1.0601 0.02385 0.01513 -0.0207 0.2586 1.0000
8.500 1.0682 0.02484 0.01598 -0.0176 0.2324 1.0000
8.750 1.0755 0.02590 0.01687 -0.0144 0.2095 1.0000
9.000 1.0823 0.02698 0.01789 -0.0111 0.1879 1.0000
9.250 1.0891 0.02812 0.01893 -0.0078 0.1697 1.0000
9.500 1.0963 0.02931 0.02005 -0.0047 0.1541 1.0000
9.750 1.1046 0.03055 0.02125 -0.0018 0.1405 1.0000
10.000 1.1142 0.03187 0.02255 0.0008 0.1289 1.0000
10.250 1.1260 0.03327 0.02389 0.0030 0.1190 1.0000
10.500 1.1376 0.03456 0.02515 0.0053 0.1105 1.0000
10.750 1.1492 0.03611 0.02683 0.0076 0.1031 1.0000
11.000 1.1747 0.03811 0.02865 0.0073 0.0953 1.0000
11.250 1.1777 0.03949 0.03037 0.0110 0.0910 1.0000
11.500 1.1856 0.04090 0.03186 0.0136 0.0862 1.0000
11.750 1.2074 0.04347 0.03447 0.0137 0.0815 1.0000
12.000 1.2047 0.04514 0.03645 0.0179 0.0788 1.0000
12.500 1.2145 0.04863 0.04014 0.0232 0.0726 1.0000
12.750 1.2204 0.05189 0.04357 0.0251 0.0703 1.0000
13.000 1.2046 0.05396 0.04596 0.0298 0.0694 1.0000
13.250 1.1885 0.05643 0.04873 0.0339 0.0684 1.0000
13.500 1.1718 0.05925 0.05184 0.0372 0.0675 1.0000
13.750 1.1539 0.06241 0.05527 0.0399 0.0667 1.0000
14.000 1.1344 0.06598 0.05909 0.0419 0.0660 1.0000
14.250 1.1118 0.07011 0.06347 0.0432 0.0656 1.0000
14.500 1.0845 0.07510 0.06870 0.0436 0.0657 1.0000
14.750 1.0518 0.08124 0.07510 0.0428 0.0663 1.0000
15.000 1.0146 0.08874 0.08283 0.0404 0.0673 1.0000
15.250 0.9764 0.09750 0.09176 0.0366 0.0686 1.0000
15.500 0.9406 0.10718 0.10154 0.0318 0.0699 1.0000
15.750 0.9099 0.11730 0.11172 0.0269 0.0708 1.0000
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Polar data table (+)
Polar graphs
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