NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Reynolds number: 200,000 Max Cl/Cd: 65.69 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls413-il-200000-n5.txt Download as CSV file: xf-ls413-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5923 0.06791 0.06362 -0.0712 1.0000 0.0244
-11.500 -0.6162 0.06232 0.05795 -0.0740 1.0000 0.0243
-11.250 -0.6412 0.05841 0.05396 -0.0740 1.0000 0.0242
-11.000 -0.6696 0.05599 0.05150 -0.0711 1.0000 0.0242
-10.750 -0.6877 0.05230 0.04764 -0.0719 0.9947 0.0242
-10.500 -0.6856 0.04698 0.04192 -0.0767 0.9865 0.0241
-10.250 -0.6755 0.04241 0.03691 -0.0801 0.9812 0.0242
-10.000 -0.6622 0.03867 0.03274 -0.0820 0.9750 0.0243
-9.750 -0.6411 0.03538 0.02899 -0.0843 0.9714 0.0244
-9.500 -0.6175 0.03287 0.02620 -0.0860 0.9676 0.0246
-9.250 -0.5941 0.03096 0.02409 -0.0869 0.9625 0.0248
-9.000 -0.5667 0.02926 0.02220 -0.0883 0.9590 0.0251
-8.750 -0.5373 0.02770 0.02046 -0.0899 0.9564 0.0254
-8.500 -0.5108 0.02644 0.01903 -0.0906 0.9522 0.0259
-8.250 -0.4839 0.02533 0.01779 -0.0913 0.9476 0.0265
-8.000 -0.4545 0.02420 0.01649 -0.0923 0.9442 0.0273
-7.750 -0.4239 0.02303 0.01515 -0.0934 0.9415 0.0280
-7.500 -0.3966 0.02200 0.01396 -0.0937 0.9371 0.0286
-7.250 -0.3693 0.02107 0.01291 -0.0939 0.9323 0.0291
-7.000 -0.3407 0.02010 0.01190 -0.0945 0.9287 0.0297
-6.750 -0.3110 0.01926 0.01106 -0.0954 0.9257 0.0305
-6.500 -0.2840 0.01861 0.01040 -0.0957 0.9210 0.0314
-6.250 -0.2567 0.01798 0.00975 -0.0960 0.9163 0.0325
-6.000 -0.2276 0.01738 0.00909 -0.0966 0.9127 0.0339
-5.750 -0.1977 0.01677 0.00845 -0.0975 0.9097 0.0359
-5.500 -0.1696 0.01628 0.00797 -0.0980 0.9054 0.0383
-5.250 -0.1413 0.01583 0.00748 -0.0985 0.9006 0.0409
-5.000 -0.1114 0.01530 0.00693 -0.0993 0.8967 0.0439
-4.750 -0.0808 0.01489 0.00649 -0.1001 0.8937 0.0485
-4.500 -0.0512 0.01449 0.00611 -0.1009 0.8900 0.0557
-4.250 -0.0220 0.01411 0.00578 -0.1016 0.8856 0.0682
-4.000 0.0087 0.01356 0.00544 -0.1027 0.8819 0.1096
-3.750 0.0416 0.01252 0.00504 -0.1051 0.8790 0.2560
-3.500 0.0757 0.01160 0.00477 -0.1074 0.8766 0.4207
-3.250 0.1049 0.01125 0.00499 -0.1079 0.8727 0.5530
-3.000 0.1331 0.01133 0.00518 -0.1078 0.8682 0.6140
-2.750 0.1609 0.01153 0.00544 -0.1074 0.8643 0.6560
-2.500 0.1886 0.01175 0.00567 -0.1068 0.8609 0.6838
-2.250 0.2166 0.01190 0.00578 -0.1066 0.8564 0.6975
-2.000 0.2443 0.01196 0.00583 -0.1064 0.8519 0.7025
-1.750 0.2740 0.01199 0.00579 -0.1068 0.8484 0.7077
-1.500 0.3042 0.01201 0.00576 -0.1072 0.8453 0.7142
-1.250 0.3316 0.01210 0.00586 -0.1069 0.8413 0.7202
-1.000 0.3607 0.01217 0.00589 -0.1072 0.8363 0.7267
-0.750 0.3897 0.01219 0.00590 -0.1073 0.8321 0.7314
-0.500 0.4184 0.01222 0.00592 -0.1073 0.8286 0.7360
-0.250 0.4469 0.01230 0.00600 -0.1074 0.8234 0.7419
0.000 0.4759 0.01229 0.00597 -0.1076 0.8165 0.7467
0.250 0.5040 0.01224 0.00591 -0.1073 0.8094 0.7497
0.500 0.5316 0.01221 0.00589 -0.1071 0.7997 0.7527
0.750 0.5600 0.01216 0.00581 -0.1070 0.7896 0.7561
1.000 0.5892 0.01206 0.00567 -0.1070 0.7773 0.7598
1.250 0.6175 0.01201 0.00559 -0.1069 0.7643 0.7628
1.500 0.6445 0.01198 0.00559 -0.1065 0.7505 0.7652
1.750 0.6717 0.01197 0.00557 -0.1062 0.7350 0.7682
2.000 0.6993 0.01197 0.00556 -0.1059 0.7182 0.7714
2.250 0.7273 0.01199 0.00555 -0.1059 0.7000 0.7748
2.500 0.7554 0.01203 0.00556 -0.1058 0.6781 0.7783
2.750 0.7812 0.01211 0.00558 -0.1052 0.6493 0.7809
3.000 0.8060 0.01227 0.00561 -0.1043 0.6029 0.7837
3.250 0.8266 0.01274 0.00568 -0.1028 0.5277 0.7869
3.500 0.8441 0.01354 0.00601 -0.1009 0.4427 0.7908
3.750 0.8624 0.01436 0.00646 -0.0994 0.3740 0.7946
4.000 0.8801 0.01511 0.00692 -0.0978 0.3127 0.7973
4.250 0.8996 0.01578 0.00736 -0.0965 0.2687 0.8004
4.750 0.9419 0.01697 0.00824 -0.0947 0.2023 0.8081
5.000 0.9633 0.01751 0.00868 -0.0938 0.1797 0.8117
5.250 0.9842 0.01801 0.00913 -0.0927 0.1632 0.8150
5.500 1.0055 0.01851 0.00959 -0.0917 0.1502 0.8188
5.750 1.0270 0.01903 0.01009 -0.0909 0.1386 0.8229
6.000 1.0490 0.01950 0.01056 -0.0901 0.1285 0.8268
6.250 1.0692 0.01998 0.01106 -0.0889 0.1208 0.8304
6.500 1.0894 0.02049 0.01159 -0.0877 0.1136 0.8347
6.750 1.1097 0.02104 0.01215 -0.0866 0.1077 0.8398
7.000 1.1292 0.02155 0.01270 -0.0854 0.1021 0.8443
7.250 1.1464 0.02218 0.01333 -0.0838 0.0973 0.8492
7.500 1.1649 0.02269 0.01393 -0.0824 0.0932 0.8546
7.750 1.1814 0.02323 0.01454 -0.0806 0.0891 0.8597
8.000 1.1967 0.02390 0.01522 -0.0788 0.0854 0.8653
8.250 1.2139 0.02458 0.01596 -0.0773 0.0820 0.8716
8.500 1.2309 0.02516 0.01666 -0.0758 0.0786 0.8777
8.750 1.2473 0.02585 0.01740 -0.0742 0.0753 0.8851
9.000 1.2605 0.02669 0.01825 -0.0723 0.0723 0.8932
9.500 1.2912 0.02800 0.01981 -0.0689 0.0667 0.9148
10.000 1.3119 0.02949 0.02143 -0.0643 0.0620 1.0000
10.250 1.3288 0.03048 0.02251 -0.0634 0.0596 1.0000
10.500 1.3454 0.03146 0.02360 -0.0625 0.0572 1.0000
10.750 1.3607 0.03250 0.02471 -0.0615 0.0550 1.0000
11.000 1.3738 0.03368 0.02592 -0.0603 0.0530 1.0000
11.250 1.3861 0.03498 0.02728 -0.0591 0.0512 1.0000
11.500 1.3999 0.03618 0.02861 -0.0580 0.0494 1.0000
11.750 1.4123 0.03747 0.03001 -0.0568 0.0476 1.0000
12.000 1.4234 0.03885 0.03148 -0.0556 0.0461 1.0000
12.250 1.4326 0.04038 0.03307 -0.0544 0.0449 1.0000
12.500 1.4394 0.04219 0.03490 -0.0531 0.0437 1.0000
12.750 1.4489 0.04380 0.03669 -0.0519 0.0426 1.0000
13.000 1.4570 0.04555 0.03859 -0.0507 0.0413 1.0000
13.250 1.4639 0.04740 0.04059 -0.0496 0.0402 1.0000
13.500 1.4697 0.04936 0.04266 -0.0486 0.0391 1.0000
13.750 1.4740 0.05147 0.04487 -0.0477 0.0383 1.0000
14.000 1.4767 0.05378 0.04726 -0.0468 0.0375 1.0000
14.250 1.4772 0.05640 0.04995 -0.0459 0.0368 1.0000
14.500 1.4786 0.05904 0.05277 -0.0452 0.0362 1.0000
14.750 1.4786 0.06190 0.05583 -0.0446 0.0355 1.0000
15.000 1.4773 0.06500 0.05911 -0.0442 0.0349 1.0000
15.250 1.4747 0.06834 0.06264 -0.0440 0.0343 1.0000
15.500 1.4710 0.07194 0.06641 -0.0442 0.0338 1.0000
15.750 1.4661 0.07580 0.07043 -0.0446 0.0333 1.0000
16.000 1.4603 0.07994 0.07473 -0.0454 0.0329 1.0000
16.250 1.4536 0.08437 0.07931 -0.0465 0.0325 1.0000
16.500 1.4460 0.08910 0.08419 -0.0480 0.0321 1.0000
16.750 1.4375 0.09414 0.08936 -0.0499 0.0318 1.0000
17.000 1.4280 0.09950 0.09485 -0.0521 0.0314 1.0000
17.250 1.4177 0.10515 0.10063 -0.0547 0.0311 1.0000
17.500 1.4073 0.11094 0.10653 -0.0575 0.0308 1.0000
17.750 1.3894 0.11860 0.11441 -0.0618 0.0306 1.0000
18.000 1.3678 0.12742 0.12347 -0.0672 0.0304 1.0000
18.250 1.3417 0.13770 0.13400 -0.0739 0.0303 1.0000
18.500 1.3052 0.15117 0.14773 -0.0832 0.0303 1.0000
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Polar data table (+)
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