NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il) Reynolds number: 100,000 Max Cl/Cd: 30.88 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls013-il-100000-n5.txt Download as CSV file: xf-ls013-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0013 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8795 0.09111 0.08576 -0.0093 1.0000 0.0422
-13.000 -0.9286 0.07897 0.07336 -0.0173 1.0000 0.0415
-12.750 -0.9631 0.07113 0.06525 -0.0211 1.0000 0.0414
-12.500 -0.9894 0.06529 0.05913 -0.0228 1.0000 0.0415
-12.250 -1.0102 0.06056 0.05411 -0.0230 1.0000 0.0419
-12.000 -1.0272 0.05655 0.04980 -0.0223 1.0000 0.0424
-11.750 -1.0411 0.05305 0.04596 -0.0207 1.0000 0.0430
-11.500 -1.0520 0.04994 0.04246 -0.0184 1.0000 0.0437
-11.250 -1.0547 0.04694 0.03902 -0.0165 1.0000 0.0445
-11.000 -1.0421 0.04486 0.03688 -0.0158 1.0000 0.0454
-10.750 -1.0293 0.04297 0.03485 -0.0150 1.0000 0.0463
-10.500 -1.0153 0.04110 0.03280 -0.0142 1.0000 0.0474
-10.250 -1.0001 0.03931 0.03080 -0.0135 1.0000 0.0489
-10.000 -0.9837 0.03751 0.02871 -0.0128 1.0000 0.0508
-9.750 -0.9657 0.03571 0.02653 -0.0121 1.0000 0.0527
-9.500 -0.9444 0.03407 0.02489 -0.0119 1.0000 0.0543
-9.250 -0.9227 0.03273 0.02351 -0.0117 1.0000 0.0560
-9.000 -0.9006 0.03150 0.02215 -0.0115 1.0000 0.0584
-8.750 -0.8778 0.03029 0.02074 -0.0112 1.0000 0.0613
-8.500 -0.8544 0.02900 0.01937 -0.0111 1.0000 0.0639
-8.250 -0.8314 0.02791 0.01831 -0.0110 1.0000 0.0664
-8.000 -0.8081 0.02695 0.01729 -0.0109 1.0000 0.0699
-7.750 -0.7840 0.02606 0.01625 -0.0107 1.0000 0.0737
-7.500 -0.7620 0.02502 0.01528 -0.0105 1.0000 0.0771
-7.250 -0.7399 0.02422 0.01448 -0.0102 1.0000 0.0815
-7.000 -0.7181 0.02352 0.01367 -0.0097 1.0000 0.0863
-6.750 -0.7010 0.02270 0.01294 -0.0086 1.0000 0.0907
-6.500 -0.6717 0.02198 0.01217 -0.0097 0.9856 0.0981
-6.250 -0.6422 0.02116 0.01139 -0.0109 0.9759 0.1067
-6.000 -0.6114 0.02042 0.01065 -0.0122 0.9684 0.1177
-5.750 -0.5830 0.01971 0.01000 -0.0130 0.9602 0.1334
-5.500 -0.5540 0.01900 0.00938 -0.0139 0.9536 0.1574
-5.250 -0.5288 0.01826 0.00886 -0.0141 0.9457 0.1932
-5.000 -0.5040 0.01744 0.00838 -0.0144 0.9393 0.2569
-4.750 -0.4822 0.01662 0.00798 -0.0140 0.9315 0.3393
-4.250 -0.4398 0.01550 0.00797 -0.0116 0.9185 0.5459
-4.000 -0.4147 0.01564 0.00826 -0.0105 0.9129 0.6106
-3.750 -0.3889 0.01581 0.00841 -0.0097 0.9072 0.6491
-3.500 -0.3632 0.01603 0.00859 -0.0088 0.9011 0.6771
-3.250 -0.3374 0.01624 0.00874 -0.0080 0.8962 0.7017
-3.000 -0.3120 0.01657 0.00904 -0.0069 0.8910 0.7212
-2.750 -0.2871 0.01693 0.00937 -0.0055 0.8855 0.7399
-2.500 -0.2622 0.01723 0.00963 -0.0042 0.8809 0.7554
-2.250 -0.2363 0.01736 0.00969 -0.0037 0.8761 0.7674
-2.000 -0.2099 0.01751 0.00981 -0.0030 0.8710 0.7753
-1.750 -0.1837 0.01755 0.00978 -0.0027 0.8663 0.7842
-1.500 -0.1575 0.01765 0.00983 -0.0020 0.8624 0.7909
-1.250 -0.1310 0.01768 0.00983 -0.0020 0.8570 0.7998
-1.000 -0.1055 0.01784 0.00998 -0.0011 0.8522 0.8077
-0.750 -0.0801 0.01790 0.01001 -0.0003 0.8482 0.8171
-0.500 -0.0538 0.01798 0.01010 0.0000 0.8433 0.8233
-0.250 -0.0269 0.01796 0.01005 -0.0002 0.8381 0.8295
0.000 0.0000 0.01794 0.01003 0.0000 0.8338 0.8337
0.250 0.0269 0.01796 0.01005 0.0002 0.8295 0.8381
0.500 0.0538 0.01798 0.01010 0.0000 0.8233 0.8433
0.750 0.0801 0.01790 0.01001 0.0003 0.8171 0.8482
1.000 0.1055 0.01784 0.00998 0.0011 0.8077 0.8522
1.250 0.1310 0.01768 0.00983 0.0020 0.7998 0.8570
1.500 0.1575 0.01765 0.00983 0.0020 0.7909 0.8624
1.750 0.1837 0.01755 0.00978 0.0027 0.7842 0.8663
2.000 0.2099 0.01751 0.00981 0.0030 0.7753 0.8710
2.250 0.2363 0.01736 0.00969 0.0037 0.7674 0.8761
2.500 0.2622 0.01723 0.00963 0.0042 0.7554 0.8809
2.750 0.2871 0.01693 0.00937 0.0055 0.7399 0.8855
3.000 0.3120 0.01657 0.00903 0.0069 0.7212 0.8910
3.250 0.3374 0.01624 0.00874 0.0080 0.7016 0.8962
3.500 0.3632 0.01603 0.00859 0.0088 0.6771 0.9011
3.750 0.3889 0.01581 0.00841 0.0097 0.6491 0.9072
4.000 0.4147 0.01564 0.00826 0.0105 0.6106 0.9129
4.250 0.4398 0.01550 0.00797 0.0116 0.5457 0.9185
4.750 0.4822 0.01662 0.00797 0.0140 0.3393 0.9315
5.000 0.5040 0.01744 0.00838 0.0144 0.2568 0.9393
5.250 0.5288 0.01826 0.00886 0.0141 0.1932 0.9457
5.500 0.5541 0.01899 0.00938 0.0139 0.1573 0.9536
5.750 0.5830 0.01971 0.01000 0.0130 0.1334 0.9602
6.000 0.6114 0.02042 0.01065 0.0122 0.1177 0.9684
6.250 0.6423 0.02116 0.01139 0.0109 0.1067 0.9760
6.500 0.6717 0.02198 0.01217 0.0097 0.0981 0.9856
6.750 0.7009 0.02270 0.01294 0.0086 0.0907 1.0000
7.000 0.7182 0.02351 0.01367 0.0097 0.0863 1.0000
7.250 0.7399 0.02422 0.01448 0.0102 0.0815 1.0000
7.500 0.7620 0.02502 0.01528 0.0105 0.0771 1.0000
7.750 0.7841 0.02606 0.01625 0.0107 0.0737 1.0000
8.000 0.8082 0.02695 0.01729 0.0108 0.0699 1.0000
8.250 0.8316 0.02791 0.01831 0.0110 0.0664 1.0000
8.500 0.8546 0.02900 0.01937 0.0111 0.0639 1.0000
8.750 0.8780 0.03029 0.02075 0.0112 0.0613 1.0000
9.000 0.9008 0.03150 0.02215 0.0114 0.0584 1.0000
9.250 0.9229 0.03273 0.02351 0.0117 0.0560 1.0000
9.500 0.9446 0.03407 0.02489 0.0119 0.0543 1.0000
9.750 0.9660 0.03571 0.02653 0.0120 0.0527 1.0000
10.000 0.9839 0.03751 0.02872 0.0127 0.0508 1.0000
10.250 1.0003 0.03931 0.03081 0.0135 0.0488 1.0000
10.500 1.0156 0.04110 0.03281 0.0142 0.0473 1.0000
10.750 1.0296 0.04298 0.03486 0.0150 0.0463 1.0000
11.000 1.0425 0.04487 0.03689 0.0157 0.0454 1.0000
11.250 1.0551 0.04695 0.03903 0.0164 0.0445 1.0000
11.500 1.0523 0.04996 0.04248 0.0183 0.0437 1.0000
11.750 1.0415 0.05308 0.04599 0.0206 0.0430 1.0000
12.000 1.0276 0.05659 0.04984 0.0222 0.0423 1.0000
12.250 1.0107 0.06060 0.05416 0.0229 0.0419 1.0000
12.500 0.9899 0.06533 0.05918 0.0226 0.0415 1.0000
12.750 0.9637 0.07120 0.06532 0.0209 0.0414 1.0000
13.000 0.9290 0.07908 0.07347 0.0171 0.0415 1.0000
13.250 0.8794 0.09139 0.08605 0.0089 0.0422 1.0000
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