NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Reynolds number: 500,000 Max Cl/Cd: 86.73 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls413mod-il-500000.txt Download as CSV file: xf-ls413mod-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0413MOD 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4972 0.08271 0.08031 -0.0452 1.0000 0.0368
-10.500 -0.5228 0.07033 0.06794 -0.0561 1.0000 0.0372
-10.250 -0.5650 0.06134 0.05883 -0.0626 1.0000 0.0372
-10.000 -0.6033 0.05786 0.05530 -0.0604 1.0000 0.0371
-9.750 -0.6290 0.05538 0.05276 -0.0574 1.0000 0.0373
-9.500 -0.6271 0.05171 0.04893 -0.0593 0.9976 0.0379
-9.250 -0.6092 0.04792 0.04433 -0.0660 0.9921 0.0415
-9.000 -0.5966 0.03987 0.03612 -0.0698 0.9882 0.0428
-8.750 -0.5785 0.02712 0.02206 -0.0730 0.9848 0.0288
-8.500 -0.5465 0.02388 0.01854 -0.0754 0.9832 0.0280
-8.250 -0.5144 0.02168 0.01609 -0.0771 0.9803 0.0276
-8.000 -0.4817 0.02001 0.01423 -0.0787 0.9769 0.0275
-7.750 -0.4469 0.01865 0.01272 -0.0805 0.9744 0.0276
-7.500 -0.4120 0.01749 0.01145 -0.0823 0.9719 0.0278
-7.250 -0.3770 0.01649 0.01037 -0.0840 0.9693 0.0280
-7.000 -0.3474 0.01568 0.00951 -0.0845 0.9623 0.0283
-6.750 -0.3150 0.01493 0.00870 -0.0856 0.9574 0.0287
-6.500 -0.2848 0.01432 0.00804 -0.0862 0.9507 0.0291
-6.250 -0.2559 0.01343 0.00712 -0.0867 0.9433 0.0299
-6.000 -0.2269 0.01272 0.00641 -0.0872 0.9355 0.0309
-5.750 -0.1980 0.01223 0.00591 -0.0875 0.9273 0.0319
-5.500 -0.1690 0.01180 0.00544 -0.0879 0.9188 0.0330
-5.250 -0.1399 0.01142 0.00501 -0.0882 0.9105 0.0343
-5.000 -0.1104 0.01098 0.00453 -0.0887 0.9017 0.0360
-4.750 -0.0809 0.01065 0.00418 -0.0890 0.8935 0.0387
-4.500 -0.0512 0.01038 0.00388 -0.0895 0.8845 0.0427
-4.250 -0.0212 0.01007 0.00359 -0.0899 0.8762 0.0531
-4.000 0.0107 0.00940 0.00324 -0.0913 0.8670 0.1230
-3.750 0.0436 0.00864 0.00294 -0.0931 0.8589 0.2529
-3.500 0.0786 0.00783 0.00271 -0.0955 0.8497 0.4099
-3.250 0.1127 0.00727 0.00263 -0.0973 0.8422 0.5554
-3.000 0.1433 0.00719 0.00269 -0.0978 0.8334 0.6130
-2.750 0.1730 0.00724 0.00272 -0.0979 0.8260 0.6431
-2.500 0.2030 0.00729 0.00275 -0.0982 0.8174 0.6637
-2.000 0.2617 0.00745 0.00287 -0.0983 0.8010 0.6957
-1.500 0.3185 0.00765 0.00306 -0.0979 0.7838 0.7218
-1.250 0.3473 0.00775 0.00311 -0.0979 0.7738 0.7322
-1.000 0.3753 0.00782 0.00313 -0.0976 0.7618 0.7383
-0.750 0.4046 0.00790 0.00316 -0.0977 0.7497 0.7459
-0.500 0.4327 0.00796 0.00321 -0.0975 0.7395 0.7514
-0.250 0.4616 0.00802 0.00323 -0.0976 0.7295 0.7555
0.000 0.4911 0.00806 0.00323 -0.0978 0.7180 0.7594
0.250 0.5209 0.00812 0.00322 -0.0982 0.7045 0.7636
0.500 0.5487 0.00817 0.00324 -0.0980 0.6898 0.7672
0.750 0.5768 0.00826 0.00330 -0.0978 0.6757 0.7715
1.000 0.6055 0.00837 0.00335 -0.0979 0.6620 0.7762
1.250 0.6351 0.00846 0.00338 -0.0982 0.6469 0.7804
1.500 0.6630 0.00853 0.00344 -0.0981 0.6316 0.7835
1.750 0.6908 0.00864 0.00351 -0.0980 0.6146 0.7871
2.000 0.7190 0.00877 0.00359 -0.0980 0.5953 0.7908
2.250 0.7478 0.00891 0.00366 -0.0982 0.5738 0.7943
2.500 0.7760 0.00910 0.00374 -0.0983 0.5489 0.7974
2.750 0.8028 0.00929 0.00385 -0.0981 0.5199 0.8000
3.000 0.8291 0.00956 0.00400 -0.0978 0.4878 0.8031
3.250 0.8555 0.00989 0.00418 -0.0976 0.4536 0.8066
3.500 0.8822 0.01023 0.00437 -0.0975 0.4199 0.8102
3.750 0.9088 0.01060 0.00459 -0.0974 0.3864 0.8137
4.000 0.9339 0.01096 0.00483 -0.0970 0.3509 0.8167
4.250 0.9587 0.01140 0.00511 -0.0965 0.3134 0.8202
4.500 0.9837 0.01187 0.00542 -0.0962 0.2799 0.8240
4.750 1.0094 0.01233 0.00573 -0.0960 0.2515 0.8278
5.000 1.0342 0.01277 0.00605 -0.0957 0.2263 0.8310
5.250 1.0586 0.01317 0.00638 -0.0951 0.2046 0.8343
5.500 1.0830 0.01360 0.00673 -0.0947 0.1855 0.8382
5.750 1.1081 0.01404 0.00709 -0.0944 0.1694 0.8424
6.000 1.1331 0.01444 0.00745 -0.0940 0.1572 0.8460
6.250 1.1567 0.01484 0.00783 -0.0934 0.1478 0.8495
6.500 1.1804 0.01526 0.00823 -0.0927 0.1397 0.8538
6.750 1.2048 0.01567 0.00865 -0.0923 0.1330 0.8585
7.000 1.2284 0.01608 0.00905 -0.0917 0.1259 0.8625
7.250 1.2510 0.01648 0.00948 -0.0909 0.1196 0.8666
7.500 1.2748 0.01684 0.00985 -0.0903 0.1142 0.8713
7.750 1.2963 0.01743 0.01042 -0.0894 0.1087 0.8762
8.000 1.3189 0.01772 0.01079 -0.0886 0.1055 0.8807
8.250 1.3414 0.01807 0.01119 -0.0878 0.1015 0.8861
8.500 1.3625 0.01859 0.01170 -0.0868 0.0974 0.8914
8.750 1.3813 0.01910 0.01227 -0.0854 0.0942 0.8964
9.000 1.4032 0.01943 0.01269 -0.0845 0.0916 0.9023
9.250 1.4234 0.01982 0.01313 -0.0834 0.0884 0.9082
9.500 1.4406 0.02035 0.01367 -0.0818 0.0851 0.9150
9.750 1.4567 0.02093 0.01431 -0.0800 0.0822 0.9221
10.000 1.4747 0.02125 0.01473 -0.0784 0.0798 0.9299
10.250 1.4886 0.02163 0.01519 -0.0762 0.0771 0.9390
10.500 1.5001 0.02216 0.01576 -0.0736 0.0741 0.9514
10.750 1.5079 0.02278 0.01644 -0.0706 0.0711 1.0000
11.000 1.5297 0.02328 0.01703 -0.0702 0.0678 1.0000
11.250 1.5466 0.02409 0.01782 -0.0693 0.0634 1.0000
11.500 1.5630 0.02492 0.01871 -0.0683 0.0588 1.0000
11.750 1.5767 0.02595 0.01971 -0.0670 0.0532 1.0000
12.000 1.5904 0.02698 0.02080 -0.0658 0.0480 1.0000
12.250 1.5995 0.02838 0.02218 -0.0642 0.0436 1.0000
12.500 1.6105 0.02964 0.02350 -0.0629 0.0403 1.0000
12.750 1.6171 0.03130 0.02516 -0.0614 0.0378 1.0000
13.000 1.6243 0.03295 0.02689 -0.0600 0.0360 1.0000
13.250 1.6314 0.03465 0.02867 -0.0588 0.0345 1.0000
13.500 1.6359 0.03664 0.03072 -0.0576 0.0332 1.0000
13.750 1.6364 0.03906 0.03320 -0.0564 0.0320 1.0000
14.000 1.6349 0.04178 0.03601 -0.0553 0.0311 1.0000
14.250 1.6390 0.04400 0.03835 -0.0546 0.0304 1.0000
14.500 1.6406 0.04654 0.04100 -0.0539 0.0298 1.0000
14.750 1.6408 0.04930 0.04388 -0.0535 0.0290 1.0000
15.000 1.6393 0.05234 0.04702 -0.0532 0.0283 1.0000
15.250 1.6349 0.05581 0.05058 -0.0531 0.0278 1.0000
15.500 1.6282 0.05970 0.05457 -0.0533 0.0272 1.0000
15.750 1.6187 0.06413 0.05910 -0.0538 0.0268 1.0000
16.000 1.6064 0.06905 0.06415 -0.0546 0.0264 1.0000
16.250 1.5957 0.07393 0.06914 -0.0556 0.0260 1.0000
16.500 1.5905 0.07823 0.07358 -0.0567 0.0257 1.0000
16.750 1.5836 0.08289 0.07839 -0.0581 0.0254 1.0000
17.000 1.5748 0.08789 0.08352 -0.0597 0.0251 1.0000
17.250 1.5648 0.09319 0.08896 -0.0615 0.0248 1.0000
17.500 1.5538 0.09874 0.09463 -0.0636 0.0245 1.0000
17.750 1.5423 0.10448 0.10050 -0.0659 0.0242 1.0000
18.000 1.5301 0.11037 0.10652 -0.0684 0.0239 1.0000
18.250 1.5180 0.11635 0.11260 -0.0711 0.0236 1.0000
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Polar data table (+)
Polar graphs
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