NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Reynolds number: 50,000 Max Cl/Cd: 29.7 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls417-il-50000.txt Download as CSV file: xf-ls417-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5855 0.09682 0.09002 -0.0483 1.0000 0.1537
-9.750 -0.5515 0.09622 0.08947 -0.0446 1.0000 0.1568
-9.500 -0.5953 0.08996 0.08325 -0.0448 1.0000 0.1485
-9.250 -0.7146 0.08201 0.07511 -0.0431 1.0000 0.1378
-9.000 -0.7266 0.07817 0.07121 -0.0415 1.0000 0.1359
-8.750 -0.7449 0.07379 0.06668 -0.0401 1.0000 0.1337
-8.500 -0.7641 0.06871 0.06128 -0.0392 1.0000 0.1309
-8.250 -0.7774 0.06323 0.05522 -0.0389 1.0000 0.1281
-8.000 -0.7743 0.05923 0.05078 -0.0386 1.0000 0.1277
-7.750 -0.7639 0.05599 0.04722 -0.0382 1.0000 0.1285
-7.500 -0.7500 0.05293 0.04383 -0.0381 1.0000 0.1295
-7.250 -0.7331 0.05002 0.04056 -0.0380 1.0000 0.1305
-7.000 -0.7137 0.04741 0.03759 -0.0379 1.0000 0.1321
-6.750 -0.6926 0.04517 0.03497 -0.0378 1.0000 0.1354
-6.500 -0.6701 0.04311 0.03248 -0.0378 1.0000 0.1401
-6.250 -0.6493 0.04154 0.03101 -0.0371 1.0000 0.1462
-6.000 -0.6257 0.04005 0.02916 -0.0366 1.0000 0.1534
-5.750 -0.6049 0.03872 0.02801 -0.0356 1.0000 0.1635
-5.500 -0.5835 0.03752 0.02689 -0.0343 1.0000 0.1770
-5.250 -0.5624 0.03643 0.02595 -0.0329 1.0000 0.1972
-5.000 -0.5416 0.03523 0.02505 -0.0316 1.0000 0.2294
-4.750 -0.5181 0.03346 0.02400 -0.0316 1.0000 0.3004
-4.500 -0.5096 0.03226 0.02512 -0.0259 1.0000 0.5101
-4.000 -0.5049 0.03728 0.03017 -0.0081 1.0000 0.6655
-3.750 -0.4987 0.03895 0.03168 -0.0013 1.0000 0.7013
-3.500 -0.4961 0.04037 0.03300 0.0068 1.0000 0.7272
-3.250 -0.4915 0.04145 0.03397 0.0138 1.0000 0.7594
-3.000 -0.4870 0.04221 0.03462 0.0208 1.0000 0.7921
-2.750 -0.4807 0.04255 0.03483 0.0271 1.0000 0.8242
-2.500 -0.4685 0.04257 0.03470 0.0320 1.0000 0.8543
-2.250 -0.4476 0.04246 0.03441 0.0346 1.0000 0.8859
-2.000 -0.3881 0.04302 0.03468 0.0303 1.0000 0.9242
-1.750 -0.2731 0.04440 0.03564 0.0137 1.0000 0.9583
-1.500 -0.1975 0.04486 0.03584 0.0026 1.0000 0.9763
-1.250 -0.1359 0.04526 0.03603 -0.0063 1.0000 0.9916
-1.000 -0.0974 0.04545 0.03610 -0.0111 1.0000 1.0000
-0.750 -0.0949 0.04519 0.03578 -0.0091 1.0000 1.0000
-0.500 -0.0922 0.04496 0.03550 -0.0070 1.0000 1.0000
-0.250 -0.0895 0.04477 0.03527 -0.0050 1.0000 1.0000
0.000 -0.0868 0.04461 0.03506 -0.0029 1.0000 1.0000
0.250 -0.0841 0.04446 0.03489 -0.0008 1.0000 1.0000
0.500 -0.0815 0.04434 0.03474 0.0013 1.0000 1.0000
0.750 -0.0789 0.04424 0.03462 0.0033 1.0000 1.0000
1.000 -0.0763 0.04416 0.03452 0.0053 1.0000 1.0000
1.250 -0.0737 0.04409 0.03445 0.0073 1.0000 1.0000
1.500 -0.0709 0.04406 0.03440 0.0092 1.0000 1.0000
1.750 -0.0678 0.04405 0.03440 0.0110 1.0000 1.0000
2.000 -0.0644 0.04410 0.03445 0.0127 1.0000 1.0000
2.250 -0.0587 0.04428 0.03464 0.0138 1.0000 1.0000
2.500 -0.0497 0.04468 0.03505 0.0143 1.0000 1.0000
2.750 -0.0374 0.04533 0.03571 0.0140 1.0000 1.0000
3.000 -0.0225 0.04620 0.03660 0.0132 1.0000 1.0000
3.250 -0.0058 0.04728 0.03770 0.0119 1.0000 1.0000
3.500 0.0185 0.04888 0.03932 0.0091 0.9971 1.0000
3.750 0.0779 0.05246 0.04293 -0.0002 0.9733 1.0000
4.000 0.2338 0.05564 0.04604 -0.0188 0.8433 1.0000
4.250 0.2837 0.05659 0.04702 -0.0228 0.8133 1.0000
4.500 0.3186 0.05722 0.04771 -0.0248 0.7873 1.0000
4.750 0.3627 0.05784 0.04840 -0.0278 0.7633 1.0000
5.000 0.4137 0.05813 0.04877 -0.0312 0.7405 1.0000
5.250 0.4515 0.05816 0.04889 -0.0326 0.7158 1.0000
5.500 0.4874 0.05795 0.04877 -0.0336 0.6903 1.0000
5.750 0.5382 0.05694 0.04787 -0.0354 0.6675 1.0000
6.000 0.5928 0.05528 0.04634 -0.0370 0.6467 1.0000
6.250 0.6272 0.05434 0.04553 -0.0370 0.6219 1.0000
6.500 0.6721 0.05233 0.04366 -0.0371 0.5980 1.0000
6.750 0.7333 0.04830 0.03981 -0.0370 0.5772 1.0000
7.000 0.8057 0.04232 0.03399 -0.0365 0.5573 1.0000
7.250 0.8763 0.03679 0.02848 -0.0360 0.5232 1.0000
7.500 0.9473 0.03304 0.02425 -0.0367 0.4646 1.0000
7.750 0.9846 0.03337 0.02406 -0.0370 0.4110 1.0000
8.000 1.0235 0.03446 0.02472 -0.0383 0.3691 1.0000
8.250 1.0560 0.03599 0.02604 -0.0395 0.3385 1.0000
8.500 1.0923 0.03757 0.02743 -0.0412 0.3140 1.0000
8.750 1.1263 0.03930 0.02908 -0.0427 0.2947 1.0000
9.000 1.1563 0.04124 0.03105 -0.0439 0.2796 1.0000
9.250 1.1888 0.04328 0.03306 -0.0454 0.2667 1.0000
9.500 1.2195 0.04529 0.03508 -0.0467 0.2555 1.0000
9.750 1.2361 0.04775 0.03782 -0.0463 0.2473 1.0000
10.000 1.2615 0.04995 0.04011 -0.0469 0.2387 1.0000
10.250 1.2789 0.05277 0.04311 -0.0468 0.2324 1.0000
10.500 1.2782 0.05567 0.04641 -0.0445 0.2274 1.0000
10.750 1.3002 0.05813 0.04893 -0.0449 0.2208 1.0000
11.000 1.3115 0.06145 0.05241 -0.0443 0.2162 1.0000
11.250 1.2878 0.06509 0.05649 -0.0401 0.2144 1.0000
11.500 1.2577 0.06931 0.06107 -0.0361 0.2132 1.0000
11.750 1.2192 0.07464 0.06674 -0.0329 0.2128 1.0000
12.000 1.1687 0.08181 0.07422 -0.0310 0.2137 1.0000
12.250 1.1079 0.09159 0.08425 -0.0313 0.2157 1.0000
12.500 1.0514 0.10347 0.09626 -0.0343 0.2175 1.0000
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Polar data table (+)
Polar graphs
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