NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Reynolds number: 500,000 Max Cl/Cd: 92.9 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls417-il-500000.txt Download as CSV file: xf-ls417-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0417 (GA(W)-1) 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.3002 0.14471 0.14233 -0.0536 1.0000 0.0333
-16.000 -0.7979 0.07474 0.07103 -0.0814 1.0000 0.0224
-15.750 -0.8346 0.06617 0.06213 -0.0870 1.0000 0.0222
-15.500 -0.8533 0.06106 0.05683 -0.0895 1.0000 0.0222
-15.250 -0.8677 0.05676 0.05234 -0.0912 1.0000 0.0221
-15.000 -0.8795 0.05297 0.04839 -0.0921 1.0000 0.0221
-14.750 -0.8887 0.04959 0.04484 -0.0925 1.0000 0.0222
-14.500 -0.8954 0.04659 0.04170 -0.0925 1.0000 0.0222
-14.250 -0.9012 0.04404 0.03902 -0.0916 1.0000 0.0222
-14.000 -0.9048 0.04190 0.03678 -0.0906 0.9980 0.0223
-13.750 -0.8896 0.03928 0.03402 -0.0927 0.9938 0.0224
-13.500 -0.8729 0.03709 0.03173 -0.0944 0.9875 0.0226
-13.250 -0.8537 0.03514 0.02967 -0.0962 0.9818 0.0228
-13.000 -0.8360 0.03346 0.02788 -0.0972 0.9729 0.0230
-12.750 -0.8189 0.03196 0.02628 -0.0976 0.9640 0.0232
-12.500 -0.8045 0.03068 0.02490 -0.0971 0.9536 0.0234
-12.250 -0.7913 0.02950 0.02362 -0.0962 0.9433 0.0236
-12.000 -0.7778 0.02840 0.02239 -0.0951 0.9345 0.0238
-11.750 -0.7627 0.02733 0.02123 -0.0943 0.9260 0.0241
-11.500 -0.7473 0.02634 0.02012 -0.0933 0.9188 0.0243
-11.250 -0.7305 0.02540 0.01908 -0.0925 0.9123 0.0246
-11.000 -0.7143 0.02455 0.01813 -0.0916 0.9056 0.0249
-10.750 -0.6977 0.02382 0.01727 -0.0906 0.8996 0.0252
-10.500 -0.6778 0.02306 0.01641 -0.0903 0.8942 0.0256
-10.250 -0.6585 0.02197 0.01534 -0.0896 0.8890 0.0261
-10.000 -0.6383 0.02120 0.01456 -0.0892 0.8842 0.0266
-9.750 -0.6172 0.02051 0.01382 -0.0890 0.8797 0.0271
-9.500 -0.5950 0.01984 0.01311 -0.0890 0.8756 0.0276
-9.250 -0.5721 0.01917 0.01240 -0.0891 0.8714 0.0281
-9.000 -0.5487 0.01855 0.01173 -0.0891 0.8673 0.0287
-8.750 -0.5245 0.01802 0.01112 -0.0891 0.8636 0.0292
-8.500 -0.5026 0.01717 0.01027 -0.0892 0.8600 0.0300
-8.250 -0.4777 0.01662 0.00970 -0.0895 0.8566 0.0309
-8.000 -0.4517 0.01611 0.00918 -0.0899 0.8532 0.0319
-7.750 -0.4250 0.01565 0.00869 -0.0903 0.8496 0.0331
-7.500 -0.3986 0.01507 0.00811 -0.0908 0.8462 0.0347
-7.250 -0.3708 0.01469 0.00771 -0.0912 0.8432 0.0368
-7.000 -0.3429 0.01428 0.00731 -0.0918 0.8404 0.0396
-6.750 -0.3143 0.01396 0.00698 -0.0924 0.8374 0.0436
-6.500 -0.2854 0.01355 0.00663 -0.0932 0.8350 0.0504
-6.250 -0.2562 0.01305 0.00621 -0.0941 0.8322 0.0640
-6.000 -0.2266 0.01257 0.00585 -0.0951 0.8294 0.0846
-5.750 -0.1965 0.01213 0.00557 -0.0962 0.8268 0.1157
-5.500 -0.1658 0.01166 0.00527 -0.0974 0.8243 0.1517
-5.250 -0.1343 0.01111 0.00496 -0.0990 0.8218 0.2077
-5.000 -0.1016 0.01051 0.00467 -0.1009 0.8194 0.2838
-4.750 -0.0679 0.00999 0.00444 -0.1030 0.8169 0.3606
-4.500 -0.0327 0.00939 0.00421 -0.1054 0.8149 0.4473
-4.250 0.0023 0.00895 0.00417 -0.1075 0.8127 0.5441
-4.000 0.0341 0.00895 0.00429 -0.1084 0.8103 0.5917
-3.750 0.0653 0.00904 0.00440 -0.1090 0.8077 0.6172
-3.500 0.0961 0.00915 0.00449 -0.1094 0.8052 0.6327
-3.250 0.1277 0.00925 0.00451 -0.1102 0.8029 0.6437
-3.000 0.1574 0.00936 0.00463 -0.1104 0.8006 0.6516
-2.750 0.1883 0.00951 0.00472 -0.1109 0.7981 0.6591
-2.500 0.2186 0.00962 0.00483 -0.1114 0.7959 0.6660
-2.250 0.2478 0.00977 0.00502 -0.1115 0.7934 0.6733
-2.000 0.2788 0.00990 0.00512 -0.1121 0.7908 0.6806
-1.750 0.3076 0.01001 0.00528 -0.1121 0.7882 0.6871
-1.500 0.3364 0.01018 0.00546 -0.1120 0.7856 0.6935
-1.250 0.3674 0.01026 0.00550 -0.1126 0.7831 0.6984
-1.000 0.3990 0.01029 0.00546 -0.1134 0.7799 0.7018
-0.750 0.4282 0.01030 0.00548 -0.1136 0.7758 0.7044
-0.500 0.4574 0.01028 0.00549 -0.1137 0.7713 0.7068
-0.250 0.4868 0.01023 0.00543 -0.1138 0.7655 0.7097
0.000 0.5164 0.01023 0.00535 -0.1139 0.7587 0.7137
0.250 0.5463 0.01021 0.00533 -0.1142 0.7519 0.7182
0.500 0.5769 0.01016 0.00528 -0.1147 0.7464 0.7213
0.750 0.6061 0.01012 0.00523 -0.1148 0.7416 0.7236
1.000 0.6354 0.01014 0.00525 -0.1150 0.7364 0.7257
1.250 0.6647 0.01012 0.00527 -0.1153 0.7307 0.7280
1.500 0.6946 0.01007 0.00522 -0.1156 0.7244 0.7303
1.750 0.7245 0.01004 0.00516 -0.1160 0.7167 0.7327
2.000 0.7544 0.00998 0.00511 -0.1164 0.7075 0.7349
2.250 0.7848 0.00998 0.00505 -0.1169 0.6996 0.7371
2.500 0.8148 0.00995 0.00505 -0.1174 0.6896 0.7389
2.750 0.8435 0.00991 0.00500 -0.1175 0.6790 0.7405
3.000 0.8718 0.00990 0.00500 -0.1175 0.6653 0.7420
3.250 0.8995 0.00994 0.00503 -0.1175 0.6481 0.7438
3.500 0.9265 0.01003 0.00506 -0.1173 0.6250 0.7457
3.750 0.9513 0.01024 0.00513 -0.1167 0.5826 0.7475
4.000 0.9700 0.01085 0.00538 -0.1150 0.5172 0.7494
4.250 0.9867 0.01162 0.00580 -0.1132 0.4510 0.7514
4.500 1.0041 0.01237 0.00624 -0.1116 0.3965 0.7535
4.750 1.0213 0.01310 0.00670 -0.1100 0.3471 0.7554
5.000 1.0385 0.01374 0.00713 -0.1084 0.3062 0.7574
5.500 1.0718 0.01493 0.00801 -0.1048 0.2419 0.7611
6.000 1.1022 0.01605 0.00892 -0.1006 0.1983 0.7652
6.250 1.1147 0.01659 0.00938 -0.0981 0.1820 0.7674
6.500 1.1306 0.01720 0.00991 -0.0963 0.1675 0.7697
6.750 1.1479 0.01781 0.01046 -0.0949 0.1560 0.7720
7.000 1.1661 0.01840 0.01102 -0.0936 0.1465 0.7741
7.250 1.1819 0.01908 0.01167 -0.0920 0.1379 0.7761
7.500 1.1995 0.01967 0.01227 -0.0907 0.1308 0.7782
7.750 1.2154 0.02040 0.01298 -0.0892 0.1247 0.7805
8.000 1.2334 0.02101 0.01361 -0.0880 0.1194 0.7831
8.250 1.2475 0.02190 0.01445 -0.0864 0.1141 0.7861
8.500 1.2675 0.02245 0.01505 -0.0856 0.1099 0.7890
8.750 1.2843 0.02320 0.01578 -0.0845 0.1058 0.7915
9.000 1.2985 0.02407 0.01667 -0.0830 0.1024 0.7939
9.250 1.3163 0.02473 0.01738 -0.0820 0.0997 0.7964
9.500 1.3325 0.02551 0.01820 -0.0808 0.0968 0.7992
9.750 1.3460 0.02651 0.01918 -0.0794 0.0941 0.8023
10.000 1.3608 0.02744 0.02016 -0.0782 0.0919 0.8054
10.250 1.3781 0.02823 0.02099 -0.0773 0.0898 0.8083
10.500 1.3935 0.02908 0.02189 -0.0762 0.0876 0.8112
10.750 1.4061 0.03014 0.02298 -0.0748 0.0856 0.8142
11.000 1.4165 0.03139 0.02425 -0.0733 0.0835 0.8176
11.250 1.4327 0.03226 0.02520 -0.0724 0.0819 0.8214
11.500 1.4481 0.03322 0.02621 -0.0715 0.0801 0.8251
11.750 1.4615 0.03424 0.02729 -0.0703 0.0783 0.8285
12.000 1.4712 0.03558 0.02865 -0.0689 0.0765 0.8320
12.250 1.4815 0.03690 0.03002 -0.0676 0.0749 0.8358
12.500 1.4959 0.03795 0.03115 -0.0667 0.0734 0.8398
12.750 1.5093 0.03907 0.03235 -0.0658 0.0716 0.8436
13.000 1.5206 0.04032 0.03365 -0.0647 0.0700 0.8475
13.250 1.5272 0.04202 0.03536 -0.0634 0.0683 0.8516
13.500 1.5389 0.04335 0.03678 -0.0625 0.0668 0.8562
13.750 1.5509 0.04467 0.03819 -0.0617 0.0652 0.8606
14.000 1.5615 0.04607 0.03968 -0.0608 0.0636 0.8653
14.250 1.5696 0.04778 0.04142 -0.0598 0.0621 0.8705
14.500 1.5742 0.04983 0.04350 -0.0587 0.0607 0.8756
14.750 1.5849 0.05128 0.04510 -0.0580 0.0592 0.8809
15.000 1.5938 0.05300 0.04691 -0.0573 0.0576 0.8869
15.250 1.6013 0.05487 0.04883 -0.0566 0.0562 0.8927
15.500 1.6028 0.05731 0.05130 -0.0557 0.0548 0.8990
15.750 1.6100 0.05928 0.05340 -0.0551 0.0535 0.9063
16.000 1.6161 0.06131 0.05556 -0.0545 0.0521 0.9150
16.250 1.6204 0.06346 0.05781 -0.0538 0.0509 0.9266
16.500 1.6170 0.06561 0.06005 -0.0521 0.0500 0.9819
16.750 1.6154 0.06889 0.06334 -0.0520 0.0489 1.0000
17.000 1.6211 0.07147 0.06605 -0.0522 0.0479 1.0000
17.250 1.6245 0.07433 0.06901 -0.0524 0.0468 1.0000
17.500 1.6264 0.07739 0.07215 -0.0528 0.0459 1.0000
17.750 1.6269 0.08064 0.07547 -0.0532 0.0450 1.0000
18.000 1.6242 0.08430 0.07917 -0.0537 0.0442 1.0000
18.250 1.6193 0.08824 0.08316 -0.0542 0.0435 1.0000
18.500 1.6184 0.09185 0.08691 -0.0550 0.0428 1.0000
18.750 1.6162 0.09566 0.09083 -0.0559 0.0421 1.0000
19.000 1.6131 0.09960 0.09488 -0.0570 0.0414 1.0000
19.250 1.6093 0.10368 0.09905 -0.0582 0.0408 1.0000
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