NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Reynolds number: 100,000 Max Cl/Cd: 49.21 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc12b3-il-100000-n5.txt Download as CSV file: xf-rc12b3-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5016 0.09202 0.08686 -0.0362 1.0000 0.0388
-10.000 -0.5088 0.08621 0.08109 -0.0400 1.0000 0.0386
-9.750 -0.5219 0.07935 0.07427 -0.0456 1.0000 0.0382
-9.500 -0.5407 0.07321 0.06811 -0.0485 1.0000 0.0379
-9.250 -0.5633 0.06834 0.06318 -0.0480 1.0000 0.0377
-9.000 -0.5872 0.06435 0.05913 -0.0451 1.0000 0.0375
-8.750 -0.6123 0.06111 0.05581 -0.0403 1.0000 0.0373
-8.500 -0.6368 0.05817 0.05274 -0.0346 1.0000 0.0373
-8.250 -0.6545 0.05455 0.04891 -0.0301 0.9984 0.0373
-8.000 -0.6530 0.04849 0.04232 -0.0297 0.9903 0.0377
-7.750 -0.6478 0.04269 0.03577 -0.0287 0.9834 0.0391
-7.500 -0.6376 0.03856 0.03095 -0.0272 0.9761 0.0403
-7.250 -0.6123 0.03666 0.02889 -0.0280 0.9720 0.0414
-7.000 -0.5909 0.03465 0.02657 -0.0277 0.9662 0.0424
-6.750 -0.5656 0.03259 0.02415 -0.0279 0.9615 0.0437
-6.500 -0.5365 0.03049 0.02164 -0.0286 0.9581 0.0456
-6.250 -0.5120 0.02882 0.01946 -0.0281 0.9524 0.0484
-6.000 -0.4837 0.02767 0.01829 -0.0287 0.9476 0.0507
-5.750 -0.4519 0.02655 0.01699 -0.0298 0.9441 0.0534
-5.500 -0.4234 0.02541 0.01562 -0.0300 0.9391 0.0567
-5.250 -0.3952 0.02449 0.01459 -0.0303 0.9337 0.0606
-5.000 -0.3637 0.02375 0.01381 -0.0313 0.9298 0.0652
-4.750 -0.3335 0.02297 0.01283 -0.0317 0.9252 0.0705
-4.500 -0.3079 0.02236 0.01229 -0.0316 0.9190 0.0760
-4.250 -0.2766 0.02173 0.01151 -0.0322 0.9148 0.0830
-4.000 -0.2506 0.02118 0.01103 -0.0321 0.9092 0.0905
-3.750 -0.2249 0.02068 0.01049 -0.0316 0.9030 0.0987
-3.500 -0.1956 0.02021 0.01002 -0.0320 0.8987 0.1097
-3.250 -0.1735 0.01983 0.00970 -0.0309 0.8916 0.1202
-3.000 -0.1473 0.01943 0.00931 -0.0306 0.8859 0.1347
-2.750 -0.1197 0.01901 0.00894 -0.0305 0.8812 0.1530
-2.500 -0.0976 0.01871 0.00873 -0.0294 0.8734 0.1760
-2.250 -0.0694 0.01820 0.00840 -0.0295 0.8685 0.2175
-2.000 0.0576 0.01654 0.00933 -0.0480 0.8754 0.8672
-1.750 0.0841 0.01709 0.00974 -0.0467 0.8693 0.9216
-1.500 0.1351 0.01757 0.01004 -0.0504 0.8660 0.9564
-1.250 0.2048 0.01764 0.00997 -0.0588 0.8621 0.9829
-1.000 0.2734 0.01720 0.00940 -0.0674 0.8575 1.0000
-0.750 0.2961 0.01709 0.00919 -0.0663 0.8500 1.0000
-0.500 0.3186 0.01705 0.00908 -0.0655 0.8401 1.0000
-0.250 0.3412 0.01698 0.00893 -0.0644 0.8316 1.0000
0.000 0.3638 0.01690 0.00879 -0.0634 0.8224 1.0000
0.250 0.3866 0.01686 0.00870 -0.0624 0.8127 1.0000
0.500 0.4095 0.01674 0.00852 -0.0612 0.8045 1.0000
0.750 0.4324 0.01673 0.00849 -0.0604 0.7937 1.0000
1.000 0.4555 0.01667 0.00839 -0.0594 0.7842 1.0000
1.250 0.4787 0.01660 0.00828 -0.0583 0.7745 1.0000
1.500 0.5018 0.01658 0.00825 -0.0574 0.7632 1.0000
1.750 0.5251 0.01653 0.00817 -0.0563 0.7524 1.0000
2.000 0.5486 0.01643 0.00805 -0.0552 0.7418 1.0000
2.250 0.5718 0.01643 0.00805 -0.0543 0.7288 1.0000
2.500 0.5951 0.01642 0.00804 -0.0533 0.7157 1.0000
2.750 0.6185 0.01640 0.00804 -0.0523 0.7024 1.0000
3.000 0.6420 0.01640 0.00803 -0.0513 0.6885 1.0000
3.250 0.6654 0.01640 0.00804 -0.0503 0.6737 1.0000
3.500 0.6887 0.01642 0.00806 -0.0493 0.6574 1.0000
3.750 0.7118 0.01644 0.00808 -0.0482 0.6394 1.0000
4.000 0.7349 0.01648 0.00809 -0.0471 0.6201 1.0000
4.250 0.7575 0.01656 0.00815 -0.0460 0.5992 1.0000
4.500 0.7800 0.01668 0.00827 -0.0449 0.5772 1.0000
4.750 0.8023 0.01683 0.00837 -0.0437 0.5547 1.0000
5.000 0.8240 0.01704 0.00853 -0.0425 0.5295 1.0000
5.250 0.8450 0.01729 0.00871 -0.0411 0.5023 1.0000
5.500 0.8653 0.01761 0.00895 -0.0397 0.4741 1.0000
5.750 0.8848 0.01798 0.00923 -0.0382 0.4458 1.0000
6.000 0.9037 0.01840 0.00956 -0.0366 0.4180 1.0000
6.250 0.9219 0.01886 0.00995 -0.0350 0.3904 1.0000
6.500 0.9393 0.01936 0.01039 -0.0333 0.3636 1.0000
6.750 0.9556 0.01992 0.01086 -0.0314 0.3372 1.0000
7.000 0.9712 0.02050 0.01137 -0.0294 0.3111 1.0000
7.250 0.9860 0.02111 0.01191 -0.0273 0.2855 1.0000
7.500 0.9994 0.02178 0.01251 -0.0251 0.2615 1.0000
7.750 1.0124 0.02245 0.01314 -0.0228 0.2379 1.0000
8.000 1.0239 0.02318 0.01380 -0.0202 0.2161 1.0000
8.250 1.0349 0.02392 0.01449 -0.0177 0.1952 1.0000
8.500 1.0442 0.02472 0.01523 -0.0148 0.1763 1.0000
8.750 1.0523 0.02556 0.01603 -0.0119 0.1599 1.0000
9.000 1.0592 0.02642 0.01685 -0.0087 0.1452 1.0000
9.250 1.0654 0.02729 0.01771 -0.0055 0.1321 1.0000
9.500 1.0692 0.02812 0.01856 -0.0018 0.1211 1.0000
9.750 1.0704 0.02901 0.01946 0.0022 0.1120 1.0000
10.000 1.0702 0.03002 0.02044 0.0061 0.1042 1.0000
10.250 1.0737 0.03100 0.02151 0.0094 0.0964 1.0000
10.500 1.0735 0.03223 0.02268 0.0128 0.0906 1.0000
10.750 1.0783 0.03333 0.02390 0.0156 0.0841 1.0000
11.000 1.0793 0.03467 0.02524 0.0185 0.0792 1.0000
11.250 1.0829 0.03599 0.02665 0.0210 0.0746 1.0000
11.500 1.0863 0.03736 0.02810 0.0234 0.0702 1.0000
11.750 1.0867 0.03899 0.02971 0.0258 0.0669 1.0000
12.000 1.0912 0.04049 0.03136 0.0278 0.0635 1.0000
12.250 1.0949 0.04209 0.03307 0.0297 0.0604 1.0000
12.500 1.0970 0.04382 0.03486 0.0315 0.0578 1.0000
12.750 1.0981 0.04575 0.03679 0.0331 0.0555 1.0000
13.000 1.1023 0.04757 0.03881 0.0346 0.0530 1.0000
13.250 1.1050 0.04954 0.04092 0.0359 0.0507 1.0000
13.500 1.1068 0.05161 0.04308 0.0370 0.0488 1.0000
13.750 1.1077 0.05382 0.04532 0.0380 0.0473 1.0000
14.000 1.1089 0.05617 0.04779 0.0390 0.0457 1.0000
14.250 1.1083 0.05880 0.05066 0.0397 0.0440 1.0000
14.500 1.1066 0.06157 0.05361 0.0402 0.0424 1.0000
14.750 1.1041 0.06447 0.05666 0.0405 0.0411 1.0000
15.000 1.1015 0.06746 0.05975 0.0406 0.0399 1.0000
15.250 1.0991 0.07048 0.06284 0.0405 0.0389 1.0000
15.500 1.0969 0.07361 0.06601 0.0404 0.0379 1.0000
15.750 1.0861 0.07814 0.07082 0.0394 0.0371 1.0000
16.000 1.0736 0.08314 0.07608 0.0380 0.0363 1.0000
16.250 1.0596 0.08860 0.08178 0.0361 0.0357 1.0000
16.500 1.0438 0.09462 0.08803 0.0336 0.0352 1.0000
16.750 1.0254 0.10144 0.09506 0.0304 0.0348 1.0000
17.000 1.0031 0.10940 0.10323 0.0264 0.0346 1.0000
17.250 0.9729 0.11960 0.11366 0.0208 0.0347 1.0000
17.500 0.9196 0.13640 0.13070 0.0111 0.0358 1.0000
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Polar data table (+)
Polar graphs
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