NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Reynolds number: 50,000 Max Cl/Cd: 33.55 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc12b3-il-50000-n5.txt Download as CSV file: xf-rc12b3-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4737 0.10401 0.09666 -0.0343 1.0000 0.0688
-10.000 -0.4734 0.09970 0.09238 -0.0360 1.0000 0.0679
-9.750 -0.4762 0.09502 0.08774 -0.0384 1.0000 0.0671
-9.500 -0.4824 0.08993 0.08270 -0.0415 1.0000 0.0662
-9.250 -0.4934 0.08487 0.07769 -0.0442 1.0000 0.0654
-9.000 -0.5088 0.08044 0.07328 -0.0449 1.0000 0.0647
-8.750 -0.5278 0.07670 0.06955 -0.0436 1.0000 0.0641
-8.500 -0.5458 0.07316 0.06599 -0.0414 1.0000 0.0636
-8.250 -0.5645 0.07002 0.06282 -0.0381 1.0000 0.0632
-8.000 -0.5821 0.06708 0.05979 -0.0341 1.0000 0.0629
-7.750 -0.5974 0.06427 0.05686 -0.0299 1.0000 0.0629
-7.500 -0.6092 0.06162 0.05405 -0.0257 1.0000 0.0632
-7.250 -0.6180 0.05904 0.05127 -0.0217 1.0000 0.0639
-7.000 -0.6243 0.05645 0.04845 -0.0178 1.0000 0.0648
-6.750 -0.6287 0.05377 0.04549 -0.0139 1.0000 0.0659
-6.500 -0.6306 0.05100 0.04237 -0.0101 1.0000 0.0671
-6.250 -0.6296 0.04823 0.03919 -0.0065 1.0000 0.0680
-6.000 -0.6254 0.04549 0.03601 -0.0032 1.0000 0.0688
-5.750 -0.6180 0.04286 0.03286 -0.0001 1.0000 0.0698
-5.500 -0.5945 0.04074 0.03053 -0.0004 0.9958 0.0724
-5.250 -0.5669 0.03916 0.02873 -0.0012 0.9905 0.0765
-5.000 -0.5379 0.03699 0.02603 -0.0018 0.9855 0.0805
-4.750 -0.5077 0.03505 0.02364 -0.0025 0.9807 0.0846
-4.500 -0.4773 0.03390 0.02240 -0.0036 0.9754 0.0906
-4.250 -0.4408 0.03243 0.02039 -0.0052 0.9713 0.0972
-4.000 -0.4110 0.03145 0.01948 -0.0061 0.9656 0.1048
-3.750 -0.3736 0.03038 0.01818 -0.0080 0.9611 0.1139
-3.500 -0.3322 0.02962 0.01725 -0.0107 0.9574 0.1273
-3.250 -0.2964 0.02891 0.01650 -0.0125 0.9520 0.1408
-3.000 -0.2573 0.02826 0.01582 -0.0149 0.9473 0.1589
-2.750 -0.2173 0.02757 0.01522 -0.0177 0.9432 0.1830
-2.500 -0.1889 0.02698 0.01474 -0.0182 0.9364 0.2114
-2.250 -0.0651 0.02460 0.01543 -0.0347 0.9471 0.9003
-2.000 0.0476 0.02519 0.01537 -0.0508 0.9547 1.0000
-1.750 0.0815 0.02522 0.01514 -0.0527 0.9465 1.0000
-1.500 0.1168 0.02526 0.01496 -0.0548 0.9390 1.0000
-1.250 0.1518 0.02531 0.01481 -0.0568 0.9310 1.0000
-1.000 0.1835 0.02540 0.01474 -0.0581 0.9223 1.0000
-0.750 0.2185 0.02544 0.01464 -0.0600 0.9144 1.0000
-0.500 0.2449 0.02559 0.01467 -0.0601 0.9041 1.0000
-0.250 0.2788 0.02563 0.01462 -0.0616 0.8961 1.0000
0.000 0.3042 0.02577 0.01469 -0.0614 0.8853 1.0000
0.250 0.3286 0.02593 0.01478 -0.0611 0.8745 1.0000
0.500 0.3620 0.02592 0.01471 -0.0621 0.8662 1.0000
0.750 0.3837 0.02609 0.01486 -0.0612 0.8541 1.0000
1.000 0.4068 0.02624 0.01498 -0.0604 0.8425 1.0000
1.250 0.4351 0.02625 0.01497 -0.0603 0.8326 1.0000
1.500 0.4604 0.02630 0.01502 -0.0597 0.8214 1.0000
1.750 0.4814 0.02644 0.01518 -0.0584 0.8088 1.0000
2.000 0.5044 0.02652 0.01527 -0.0573 0.7969 1.0000
2.250 0.5310 0.02645 0.01523 -0.0567 0.7861 1.0000
2.500 0.5554 0.02642 0.01523 -0.0557 0.7741 1.0000
2.750 0.5762 0.02650 0.01535 -0.0541 0.7605 1.0000
3.000 0.5977 0.02653 0.01545 -0.0526 0.7468 1.0000
3.250 0.6199 0.02653 0.01549 -0.0511 0.7330 1.0000
3.500 0.6424 0.02648 0.01550 -0.0497 0.7190 1.0000
3.750 0.6650 0.02642 0.01551 -0.0482 0.7047 1.0000
4.000 0.6874 0.02636 0.01553 -0.0466 0.6898 1.0000
4.250 0.7094 0.02631 0.01554 -0.0450 0.6740 1.0000
4.500 0.7311 0.02626 0.01557 -0.0432 0.6574 1.0000
4.750 0.7528 0.02620 0.01559 -0.0415 0.6398 1.0000
5.000 0.7752 0.02608 0.01554 -0.0398 0.6213 1.0000
5.250 0.7979 0.02596 0.01545 -0.0380 0.6020 1.0000
5.500 0.8162 0.02610 0.01566 -0.0359 0.5795 1.0000
5.750 0.8380 0.02608 0.01568 -0.0341 0.5578 1.0000
6.000 0.8564 0.02628 0.01591 -0.0320 0.5338 1.0000
6.250 0.8770 0.02638 0.01598 -0.0301 0.5099 1.0000
6.500 0.8933 0.02673 0.01635 -0.0278 0.4833 1.0000
6.750 0.9096 0.02712 0.01672 -0.0254 0.4565 1.0000
7.000 0.9250 0.02757 0.01710 -0.0230 0.4299 1.0000
7.250 0.9385 0.02814 0.01762 -0.0204 0.4033 1.0000
7.500 0.9503 0.02882 0.01827 -0.0177 0.3770 1.0000
7.750 0.9612 0.02954 0.01895 -0.0149 0.3518 1.0000
8.000 0.9704 0.03035 0.01972 -0.0119 0.3272 1.0000
8.250 0.9782 0.03124 0.02056 -0.0089 0.3033 1.0000
8.500 0.9847 0.03218 0.02144 -0.0057 0.2809 1.0000
8.750 0.9901 0.03319 0.02241 -0.0024 0.2595 1.0000
9.000 0.9944 0.03427 0.02346 0.0008 0.2393 1.0000
9.250 0.9963 0.03537 0.02453 0.0044 0.2216 1.0000
9.500 0.9977 0.03653 0.02565 0.0080 0.2054 1.0000
9.750 0.9992 0.03779 0.02687 0.0113 0.1901 1.0000
10.000 1.0018 0.03913 0.02820 0.0142 0.1759 1.0000
10.250 1.0047 0.04056 0.02964 0.0170 0.1627 1.0000
10.500 1.0083 0.04207 0.03117 0.0195 0.1507 1.0000
10.750 1.0128 0.04364 0.03275 0.0218 0.1402 1.0000
11.000 1.0169 0.04523 0.03432 0.0239 0.1311 1.0000
11.250 1.0228 0.04697 0.03623 0.0259 0.1218 1.0000
11.500 1.0286 0.04871 0.03798 0.0277 0.1145 1.0000
11.750 1.0331 0.05059 0.04000 0.0295 0.1075 1.0000
12.000 1.0397 0.05246 0.04189 0.0310 0.1017 1.0000
12.250 1.0433 0.05467 0.04433 0.0326 0.0962 1.0000
12.500 1.0490 0.05653 0.04616 0.0339 0.0915 1.0000
12.750 1.0502 0.05918 0.04909 0.0353 0.0875 1.0000
13.000 1.0495 0.06198 0.05214 0.0365 0.0839 1.0000
13.250 1.0500 0.06451 0.05476 0.0375 0.0807 1.0000
13.500 1.0542 0.06688 0.05712 0.0384 0.0776 1.0000
13.750 1.0410 0.07107 0.06168 0.0388 0.0757 1.0000
14.000 1.0264 0.07563 0.06653 0.0387 0.0742 1.0000
14.250 1.0097 0.08073 0.07188 0.0380 0.0730 1.0000
14.500 0.9887 0.08671 0.07810 0.0365 0.0723 1.0000
14.750 0.9604 0.09428 0.08590 0.0336 0.0721 1.0000
15.000 0.9203 0.10495 0.09679 0.0283 0.0727 1.0000
15.250 0.8602 0.12214 0.11410 0.0187 0.0743 1.0000
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Polar data table (+)
Polar graphs
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