NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Reynolds number: 100,000 Max Cl/Cd: 33.09 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls417mod-il-100000.txt Download as CSV file: xf-ls417mod-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0417MOD 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4297 0.11906 0.11380 -0.0391 1.0000 0.1603
-11.000 -0.3927 0.11569 0.11041 -0.0353 1.0000 0.1621
-10.750 -0.6595 0.07259 0.06685 -0.0619 1.0000 0.0854
-10.500 -0.6273 0.06972 0.06414 -0.0619 1.0000 0.0865
-10.000 -0.7529 0.06160 0.05537 -0.0509 1.0000 0.0778
-9.750 -0.7602 0.05899 0.05268 -0.0480 1.0000 0.0774
-9.500 -0.7669 0.05630 0.04986 -0.0452 1.0000 0.0770
-9.250 -0.7717 0.05346 0.04682 -0.0427 1.0000 0.0765
-9.000 -0.7735 0.05045 0.04355 -0.0405 1.0000 0.0757
-8.750 -0.7718 0.04726 0.04003 -0.0386 1.0000 0.0748
-8.500 -0.7655 0.04421 0.03657 -0.0371 1.0000 0.0743
-8.250 -0.7540 0.04160 0.03361 -0.0359 1.0000 0.0742
-8.000 -0.7390 0.03938 0.03109 -0.0349 1.0000 0.0747
-7.750 -0.7221 0.03752 0.02889 -0.0341 1.0000 0.0763
-7.500 -0.7031 0.03578 0.02669 -0.0335 1.0000 0.0781
-7.250 -0.6825 0.03441 0.02543 -0.0328 1.0000 0.0799
-7.000 -0.6612 0.03315 0.02408 -0.0320 1.0000 0.0817
-6.750 -0.6392 0.03193 0.02267 -0.0313 1.0000 0.0837
-6.500 -0.6172 0.03080 0.02145 -0.0305 1.0000 0.0864
-6.250 -0.5958 0.02998 0.02071 -0.0298 1.0000 0.0902
-6.000 -0.5735 0.02911 0.01975 -0.0291 1.0000 0.0942
-5.750 -0.5518 0.02830 0.01908 -0.0284 1.0000 0.0984
-5.500 -0.5295 0.02753 0.01835 -0.0277 1.0000 0.1039
-5.250 -0.5066 0.02690 0.01778 -0.0273 1.0000 0.1122
-5.000 -0.4648 0.02593 0.01712 -0.0305 0.9951 0.1276
-4.750 -0.4149 0.02451 0.01619 -0.0356 0.9883 0.1728
-4.500 -0.3584 0.02161 0.01551 -0.0436 0.9828 0.4661
-4.250 -0.3261 0.02269 0.01709 -0.0423 0.9735 0.5895
-4.000 -0.2861 0.02416 0.01848 -0.0425 0.9654 0.6375
-3.750 -0.2620 0.02543 0.01972 -0.0396 0.9546 0.6635
-3.500 -0.2359 0.02681 0.02106 -0.0365 0.9448 0.6846
-3.250 -0.2043 0.02801 0.02219 -0.0342 0.9352 0.7034
-3.000 -0.1792 0.02873 0.02284 -0.0317 0.9237 0.7209
-2.750 -0.1337 0.02926 0.02326 -0.0326 0.9157 0.7395
-2.500 -0.1150 0.02969 0.02366 -0.0282 0.9026 0.7508
-2.250 -0.0638 0.02986 0.02374 -0.0294 0.8959 0.7680
-2.000 -0.0387 0.02978 0.02360 -0.0272 0.8816 0.7844
-1.750 0.0220 0.02924 0.02294 -0.0313 0.8753 0.8005
-1.500 0.0510 0.02871 0.02237 -0.0293 0.8600 0.8093
-1.250 0.0926 0.02786 0.02143 -0.0309 0.8473 0.8205
-1.000 0.1387 0.02689 0.02038 -0.0321 0.8334 0.8289
-0.750 0.1673 0.02606 0.01948 -0.0312 0.8132 0.8391
-0.500 0.2031 0.02513 0.01846 -0.0309 0.7899 0.8473
-0.250 0.2297 0.02430 0.01750 -0.0297 0.7607 0.8562
0.000 0.2586 0.02353 0.01658 -0.0285 0.7199 0.8638
0.250 0.2774 0.02302 0.01585 -0.0265 0.6723 0.8719
0.500 0.3062 0.02259 0.01509 -0.0258 0.6252 0.8782
0.750 0.3269 0.02247 0.01460 -0.0246 0.5924 0.8853
1.000 0.3533 0.02234 0.01421 -0.0243 0.5653 0.8904
1.250 0.3792 0.02234 0.01396 -0.0241 0.5449 0.8959
1.500 0.4001 0.02246 0.01382 -0.0234 0.5294 0.9011
1.750 0.4279 0.02243 0.01369 -0.0236 0.5142 0.9053
2.000 0.4554 0.02254 0.01364 -0.0239 0.5018 0.9096
2.250 0.4782 0.02267 0.01365 -0.0236 0.4905 0.9141
2.500 0.5038 0.02285 0.01372 -0.0237 0.4806 0.9175
2.750 0.5312 0.02295 0.01378 -0.0240 0.4704 0.9210
3.000 0.5598 0.02328 0.01392 -0.0246 0.4617 0.9246
3.250 0.5812 0.02343 0.01415 -0.0242 0.4532 0.9278
3.500 0.6066 0.02366 0.01433 -0.0243 0.4451 0.9309
3.750 0.6363 0.02404 0.01460 -0.0251 0.4376 0.9341
4.000 0.6598 0.02424 0.01491 -0.0249 0.4298 0.9373
4.250 0.6855 0.02455 0.01518 -0.0251 0.4226 0.9401
4.500 0.7133 0.02516 0.01564 -0.0258 0.4162 0.9432
4.750 0.7367 0.02536 0.01604 -0.0256 0.4092 0.9467
5.000 0.7624 0.02570 0.01642 -0.0258 0.4022 0.9502
5.250 0.7909 0.02617 0.01680 -0.0265 0.3961 0.9531
5.500 0.8144 0.02678 0.01748 -0.0265 0.3901 0.9563
5.750 0.8396 0.02719 0.01804 -0.0267 0.3832 0.9597
6.000 0.8677 0.02762 0.01847 -0.0274 0.3769 0.9638
6.250 0.8988 0.02842 0.01913 -0.0286 0.3713 0.9677
6.500 0.9211 0.02895 0.01995 -0.0286 0.3649 0.9717
6.750 0.9485 0.02952 0.02061 -0.0294 0.3583 0.9756
7.000 0.9798 0.03004 0.02108 -0.0306 0.3526 0.9797
7.250 1.0087 0.03100 0.02215 -0.0319 0.3468 0.9838
7.500 1.0348 0.03180 0.02315 -0.0327 0.3398 0.9894
7.750 1.0688 0.03237 0.02374 -0.0346 0.3337 0.9953
8.000 1.0984 0.03319 0.02443 -0.0357 0.3288 1.0000
8.250 1.1079 0.03429 0.02590 -0.0340 0.3227 1.0000
8.500 1.1316 0.03509 0.02680 -0.0344 0.3167 1.0000
8.750 1.1644 0.03557 0.02718 -0.0358 0.3115 1.0000
9.000 1.1835 0.03697 0.02878 -0.0359 0.3059 1.0000
9.250 1.2019 0.03818 0.03022 -0.0358 0.2994 1.0000
9.500 1.2347 0.03860 0.03058 -0.0373 0.2939 1.0000
9.750 1.2617 0.03968 0.03169 -0.0383 0.2888 1.0000
10.000 1.2699 0.04149 0.03386 -0.0372 0.2823 1.0000
10.250 1.3013 0.04189 0.03424 -0.0385 0.2767 1.0000
10.500 1.3364 0.04248 0.03472 -0.0403 0.2718 1.0000
10.750 1.3305 0.04504 0.03774 -0.0378 0.2657 1.0000
11.000 1.3585 0.04553 0.03825 -0.0387 0.2601 1.0000
11.250 1.4029 0.04547 0.03798 -0.0412 0.2553 1.0000
11.500 1.3782 0.04899 0.04203 -0.0371 0.2500 1.0000
11.750 1.3950 0.04998 0.04310 -0.0368 0.2447 1.0000
12.000 1.4582 0.04871 0.04150 -0.0409 0.2394 1.0000
12.250 1.4076 0.05334 0.04668 -0.0344 0.2359 1.0000
12.500 1.3608 0.05876 0.05247 -0.0306 0.2324 1.0000
12.750 1.4566 0.05420 0.04754 -0.0350 0.2259 1.0000
13.000 1.4331 0.05804 0.05162 -0.0323 0.2226 1.0000
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Polar data table (+)
Polar graphs
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