NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Reynolds number: 50,000 Max Cl/Cd: 24.97 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls417-il-50000-n5.txt Download as CSV file: xf-ls417-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4887 0.09801 0.09001 -0.0707 1.0000 0.0593
-12.250 -0.5196 0.09088 0.08288 -0.0734 1.0000 0.0588
-12.000 -0.5557 0.08487 0.07686 -0.0746 1.0000 0.0583
-11.750 -0.5933 0.08031 0.07226 -0.0740 1.0000 0.0579
-11.500 -0.6308 0.07679 0.06869 -0.0719 1.0000 0.0575
-11.250 -0.6676 0.07397 0.06580 -0.0688 1.0000 0.0572
-11.000 -0.7036 0.07166 0.06341 -0.0648 1.0000 0.0570
-10.750 -0.7384 0.06978 0.06145 -0.0601 1.0000 0.0567
-10.500 -0.7671 0.06753 0.05907 -0.0563 1.0000 0.0566
-10.250 -0.7729 0.06363 0.05482 -0.0569 0.9948 0.0569
-10.000 -0.7705 0.05989 0.05068 -0.0578 0.9891 0.0576
-9.750 -0.7642 0.05637 0.04666 -0.0586 0.9837 0.0588
-9.500 -0.7501 0.05371 0.04369 -0.0592 0.9797 0.0602
-9.250 -0.7332 0.05195 0.04183 -0.0593 0.9754 0.0618
-9.000 -0.7139 0.04985 0.03948 -0.0597 0.9713 0.0636
-8.750 -0.6906 0.04761 0.03685 -0.0605 0.9680 0.0655
-8.500 -0.6693 0.04587 0.03490 -0.0603 0.9643 0.0671
-8.250 -0.6478 0.04462 0.03362 -0.0601 0.9604 0.0693
-8.000 -0.6241 0.04335 0.03215 -0.0600 0.9572 0.0728
-7.750 -0.5986 0.04228 0.03106 -0.0602 0.9545 0.0764
-7.500 -0.5702 0.04129 0.02993 -0.0606 0.9521 0.0810
-7.250 -0.5512 0.04049 0.02916 -0.0594 0.9482 0.0852
-7.000 -0.5296 0.03974 0.02831 -0.0585 0.9443 0.0918
-6.750 -0.5066 0.03895 0.02753 -0.0583 0.9407 0.0996
-6.500 -0.4826 0.03810 0.02670 -0.0584 0.9377 0.1103
-6.250 -0.4579 0.03720 0.02584 -0.0588 0.9353 0.1257
-6.000 -0.4456 0.03630 0.02511 -0.0573 0.9311 0.1417
-5.750 -0.4287 0.03530 0.02430 -0.0568 0.9269 0.1691
-5.500 -0.4083 0.03396 0.02344 -0.0576 0.9232 0.2197
-5.250 -0.3847 0.03247 0.02268 -0.0591 0.9202 0.3152
-5.000 -0.3617 0.03194 0.02292 -0.0585 0.9177 0.4250
-4.750 -0.3504 0.03275 0.02416 -0.0536 0.9138 0.4966
-4.500 -0.3365 0.03378 0.02530 -0.0494 0.9090 0.5529
-4.250 -0.3130 0.03458 0.02593 -0.0484 0.9049 0.6069
-4.000 -0.2879 0.03550 0.02665 -0.0474 0.9015 0.6435
-3.750 -0.2626 0.03647 0.02748 -0.0456 0.8985 0.6659
-3.500 -0.2489 0.03717 0.02806 -0.0424 0.8938 0.6854
-3.250 -0.2346 0.03784 0.02863 -0.0392 0.8891 0.7044
-3.000 -0.2163 0.03849 0.02917 -0.0366 0.8851 0.7230
-2.750 -0.1932 0.03898 0.02953 -0.0350 0.8815 0.7404
-2.500 -0.1661 0.03931 0.02971 -0.0345 0.8785 0.7551
-2.250 -0.1550 0.03955 0.02988 -0.0313 0.8736 0.7649
-2.000 -0.1373 0.03965 0.02987 -0.0301 0.8685 0.7763
-1.750 -0.1148 0.03978 0.02989 -0.0293 0.8642 0.7864
-1.500 -0.0879 0.03988 0.02988 -0.0294 0.8605 0.7961
-1.250 -0.0581 0.04000 0.02987 -0.0302 0.8573 0.8068
-1.000 -0.0507 0.04010 0.02994 -0.0270 0.8504 0.8149
-0.750 -0.0274 0.04020 0.02996 -0.0271 0.8452 0.8246
-0.500 -0.0013 0.04023 0.02992 -0.0268 0.8409 0.8316
-0.250 0.0323 0.04031 0.02990 -0.0284 0.8374 0.8393
0.000 0.0394 0.04044 0.03003 -0.0257 0.8291 0.8460
0.250 0.0649 0.04052 0.03005 -0.0259 0.8234 0.8523
0.500 0.0997 0.04062 0.03009 -0.0279 0.8191 0.8584
0.750 0.1152 0.04076 0.03022 -0.0264 0.8114 0.8636
1.000 0.1391 0.04089 0.03033 -0.0265 0.8044 0.8689
1.250 0.1748 0.04098 0.03038 -0.0285 0.7995 0.8736
1.500 0.1922 0.04120 0.03062 -0.0277 0.7911 0.8781
1.750 0.2181 0.04133 0.03074 -0.0280 0.7836 0.8826
2.000 0.2561 0.04134 0.03075 -0.0301 0.7787 0.8865
2.500 0.3044 0.04166 0.03113 -0.0303 0.7610 0.8945
2.750 0.3256 0.04187 0.03137 -0.0300 0.7508 0.8988
3.000 0.3587 0.04182 0.03135 -0.0312 0.7423 0.9023
3.250 0.3834 0.04196 0.03154 -0.0313 0.7315 0.9060
3.500 0.4157 0.04169 0.03133 -0.0320 0.7226 0.9097
3.750 0.4370 0.04179 0.03149 -0.0314 0.7098 0.9142
4.000 0.4779 0.04115 0.03092 -0.0330 0.7018 0.9178
4.250 0.4971 0.04122 0.03108 -0.0321 0.6869 0.9217
4.500 0.5218 0.04105 0.03099 -0.0318 0.6735 0.9256
4.750 0.5622 0.03999 0.03003 -0.0326 0.6641 0.9296
5.000 0.5841 0.03972 0.02985 -0.0317 0.6474 0.9346
5.250 0.6078 0.03924 0.02947 -0.0308 0.6304 0.9400
5.500 0.6328 0.03872 0.02907 -0.0301 0.6127 0.9456
5.750 0.6576 0.03817 0.02863 -0.0294 0.5945 0.9511
6.250 0.7137 0.03674 0.02742 -0.0284 0.5553 0.9635
6.500 0.7377 0.03642 0.02719 -0.0278 0.5284 0.9719
7.000 0.8008 0.03422 0.02487 -0.0266 0.4648 1.0000
7.250 0.8331 0.03380 0.02416 -0.0265 0.4240 1.0000
7.500 0.8561 0.03429 0.02437 -0.0261 0.3840 1.0000
7.750 0.8742 0.03528 0.02513 -0.0257 0.3483 1.0000
8.000 0.8909 0.03650 0.02616 -0.0254 0.3180 1.0000
8.250 0.9077 0.03779 0.02726 -0.0251 0.2929 1.0000
8.500 0.9249 0.03913 0.02842 -0.0250 0.2718 1.0000
8.750 0.9434 0.04045 0.02964 -0.0251 0.2536 1.0000
9.000 0.9630 0.04175 0.03089 -0.0253 0.2375 1.0000
9.250 0.9838 0.04302 0.03213 -0.0255 0.2234 1.0000
9.500 1.0061 0.04424 0.03332 -0.0258 0.2116 1.0000
9.750 1.0293 0.04539 0.03440 -0.0262 0.2013 1.0000
10.000 1.0530 0.04664 0.03574 -0.0266 0.1913 1.0000
10.250 1.0799 0.04766 0.03666 -0.0272 0.1833 1.0000
10.500 1.1030 0.04903 0.03821 -0.0276 0.1753 1.0000
10.750 1.1304 0.05010 0.03917 -0.0282 0.1688 1.0000
11.000 1.1518 0.05169 0.04099 -0.0285 0.1625 1.0000
11.250 1.1740 0.05313 0.04248 -0.0288 0.1569 1.0000
11.500 1.1994 0.05453 0.04385 -0.0292 0.1519 1.0000
11.750 1.2135 0.05663 0.04625 -0.0291 0.1472 1.0000
12.000 1.2303 0.05844 0.04815 -0.0291 0.1428 1.0000
12.250 1.2547 0.05989 0.04951 -0.0295 0.1387 1.0000
12.500 1.2559 0.06282 0.05284 -0.0287 0.1353 1.0000
12.750 1.2603 0.06551 0.05577 -0.0281 0.1318 1.0000
13.000 1.2715 0.06760 0.05793 -0.0279 0.1285 1.0000
13.250 1.2852 0.06970 0.06004 -0.0278 0.1254 1.0000
13.500 1.2702 0.07398 0.06474 -0.0270 0.1232 1.0000
13.750 1.2557 0.07841 0.06950 -0.0266 0.1210 1.0000
14.000 1.2436 0.08275 0.07408 -0.0266 0.1187 1.0000
14.250 1.2403 0.08630 0.07778 -0.0268 0.1165 1.0000
14.500 1.2566 0.08796 0.07937 -0.0269 0.1139 1.0000
14.750 1.2147 0.09605 0.08789 -0.0285 0.1131 1.0000
15.000 1.1580 0.10748 0.09973 -0.0330 0.1128 1.0000
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Polar data table (+)
Polar graphs
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