NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Reynolds number: 100,000 Max Cl/Cd: 33.1 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls421-il-100000.txt Download as CSV file: xf-ls421-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0421 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.3481 0.15969 0.15417 -0.0472 1.0000 0.1499
-14.500 -0.3627 0.15946 0.15400 -0.0442 1.0000 0.1531
-14.250 -0.6067 0.10368 0.09807 -0.0722 1.0000 0.0909
-14.000 -0.6124 0.10231 0.09676 -0.0699 1.0000 0.0915
-13.750 -0.6145 0.10160 0.09610 -0.0675 1.0000 0.0925
-13.500 -0.6053 0.10280 0.09739 -0.0642 1.0000 0.0941
-13.250 -0.9528 0.07328 0.06646 -0.0641 1.0000 0.0825
-13.000 -0.9758 0.07033 0.06332 -0.0618 0.9978 0.0824
-12.750 -0.9962 0.06735 0.06009 -0.0600 0.9937 0.0824
-12.500 -1.0109 0.06416 0.05657 -0.0586 0.9899 0.0824
-12.250 -1.0100 0.06127 0.05351 -0.0576 0.9864 0.0830
-12.000 -0.9797 0.05977 0.05216 -0.0590 0.9836 0.0847
-11.750 -0.9693 0.05759 0.04980 -0.0593 0.9800 0.0861
-11.500 -0.9647 0.05528 0.04720 -0.0586 0.9765 0.0874
-11.250 -0.9673 0.05324 0.04488 -0.0562 0.9730 0.0885
-11.000 -0.9651 0.05115 0.04241 -0.0543 0.9699 0.0897
-10.750 -0.9550 0.04911 0.04002 -0.0534 0.9672 0.0910
-10.500 -0.9261 0.04766 0.03864 -0.0546 0.9648 0.0931
-10.250 -0.8997 0.04650 0.03739 -0.0556 0.9622 0.0959
-10.000 -0.8936 0.04532 0.03598 -0.0531 0.9588 0.0982
-9.750 -0.8793 0.04408 0.03461 -0.0518 0.9565 0.1006
-9.500 -0.8597 0.04323 0.03383 -0.0512 0.9544 0.1034
-9.250 -0.8403 0.04234 0.03284 -0.0506 0.9523 0.1067
-9.000 -0.8157 0.04137 0.03180 -0.0508 0.9499 0.1108
-8.750 -0.7847 0.04069 0.03118 -0.0520 0.9474 0.1160
-8.500 -0.7631 0.03995 0.03035 -0.0516 0.9448 0.1209
-8.250 -0.7515 0.03938 0.02993 -0.0494 0.9429 0.1254
-8.000 -0.7386 0.03885 0.02927 -0.0477 0.9413 0.1315
-7.750 -0.7232 0.03822 0.02887 -0.0463 0.9395 0.1382
-7.500 -0.7051 0.03758 0.02830 -0.0453 0.9370 0.1471
-7.250 -0.6848 0.03694 0.02778 -0.0450 0.9345 0.1597
-7.000 -0.6663 0.03627 0.02730 -0.0445 0.9330 0.1758
-6.750 -0.6471 0.03553 0.02680 -0.0443 0.9318 0.1994
-6.500 -0.6200 0.03463 0.02630 -0.0459 0.9298 0.2410
-6.250 -0.5935 0.03363 0.02588 -0.0478 0.9269 0.3064
-6.000 -0.5781 0.03275 0.02553 -0.0474 0.9245 0.3795
-5.750 -0.5605 0.03259 0.02595 -0.0464 0.9235 0.4564
-5.500 -0.5476 0.03335 0.02711 -0.0433 0.9225 0.5129
-5.250 -0.5320 0.03437 0.02824 -0.0406 0.9203 0.5541
-5.000 -0.5156 0.03554 0.02940 -0.0382 0.9193 0.5839
-4.750 -0.5020 0.03686 0.03070 -0.0353 0.9198 0.6055
-4.500 -0.4874 0.03824 0.03204 -0.0323 0.9187 0.6236
-4.250 -0.4737 0.03953 0.03327 -0.0295 0.9193 0.6405
-4.000 -0.4667 0.04123 0.03498 -0.0247 0.9239 0.6499
-3.750 -0.4490 0.04279 0.03648 -0.0226 0.9266 0.6634
-3.500 -0.5317 0.04050 0.03439 -0.0066 0.9835 0.6659
-3.250 -0.4964 0.04291 0.03668 -0.0073 0.9783 0.6824
-3.000 -0.4867 0.04384 0.03762 -0.0026 0.9705 0.6903
-2.750 -0.4550 0.04568 0.03936 -0.0029 0.9643 0.7052
-2.500 -0.4432 0.04663 0.04030 0.0011 0.9562 0.7149
-2.250 -0.4150 0.04807 0.04165 0.0016 0.9488 0.7281
-2.000 -0.3924 0.04940 0.04292 0.0024 0.9445 0.7422
-1.750 -0.3768 0.04994 0.04345 0.0059 0.9325 0.7517
-1.500 -0.3405 0.05201 0.04542 0.0042 0.9278 0.7676
-1.250 -0.2463 0.05265 0.04586 -0.0012 0.8678 0.7809
-1.000 -0.2419 0.05279 0.04598 0.0013 0.8684 0.7904
-0.750 -0.2089 0.05228 0.04538 0.0019 0.8437 0.7991
-0.500 -0.2025 0.05207 0.04514 0.0036 0.8360 0.8084
-0.250 -0.1556 0.05237 0.04536 0.0018 0.8265 0.8160
0.000 -0.1463 0.05230 0.04525 0.0026 0.8148 0.8254
0.250 -0.1154 0.05221 0.04512 0.0034 0.8069 0.8319
0.500 -0.0977 0.05229 0.04517 0.0042 0.7961 0.8400
0.750 -0.0715 0.05219 0.04504 0.0041 0.7875 0.8471
1.000 -0.0168 0.05232 0.04509 0.0007 0.7823 0.8541
1.250 -0.0215 0.05232 0.04509 0.0034 0.7684 0.8606
1.500 0.0223 0.05201 0.04475 0.0017 0.7627 0.8656
1.750 0.0258 0.05210 0.04485 0.0042 0.7498 0.8705
2.000 0.0703 0.05192 0.04462 0.0012 0.7432 0.8753
2.250 0.0852 0.05211 0.04481 0.0017 0.7313 0.8793
2.500 0.1198 0.05171 0.04440 0.0008 0.7239 0.8831
2.750 0.1720 0.05122 0.04388 -0.0023 0.7202 0.8869
3.000 0.1754 0.05158 0.04426 -0.0006 0.7048 0.8905
3.250 0.2290 0.05099 0.04365 -0.0044 0.7008 0.8937
3.500 0.2336 0.05130 0.04399 -0.0023 0.6860 0.8968
3.750 0.2820 0.05038 0.04306 -0.0047 0.6817 0.8992
4.000 0.2928 0.05075 0.04347 -0.0036 0.6672 0.9025
4.250 0.3423 0.04965 0.04237 -0.0061 0.6628 0.9056
4.500 0.3599 0.04996 0.04272 -0.0060 0.6486 0.9081
4.750 0.4122 0.04847 0.04124 -0.0087 0.6440 0.9101
5.000 0.4659 0.04636 0.03915 -0.0105 0.6415 0.9126
5.250 0.4763 0.04651 0.03935 -0.0090 0.6255 0.9160
5.500 0.5311 0.04425 0.03712 -0.0111 0.6230 0.9189
5.750 0.5482 0.04434 0.03727 -0.0105 0.6075 0.9214
6.000 0.6034 0.04190 0.03487 -0.0127 0.6048 0.9237
6.250 0.6218 0.04168 0.03471 -0.0119 0.5900 0.9262
6.500 0.6709 0.03891 0.03198 -0.0127 0.5871 0.9295
6.750 0.7270 0.03580 0.02891 -0.0143 0.5849 0.9330
7.000 0.7495 0.03530 0.02847 -0.0137 0.5688 0.9363
7.250 0.7833 0.03417 0.02738 -0.0142 0.5541 0.9390
7.500 0.8253 0.03218 0.02539 -0.0148 0.5399 0.9420
7.750 0.8642 0.03066 0.02384 -0.0153 0.5192 0.9452
8.000 0.9049 0.02929 0.02232 -0.0161 0.4925 0.9485
8.250 0.9326 0.02898 0.02182 -0.0159 0.4599 0.9524
8.500 0.9559 0.02888 0.02143 -0.0151 0.4270 0.9568
8.750 0.9700 0.02954 0.02187 -0.0139 0.3953 0.9615
9.000 0.9862 0.03032 0.02239 -0.0131 0.3664 0.9657
9.250 0.9991 0.03127 0.02318 -0.0121 0.3409 0.9702
9.500 1.0145 0.03223 0.02396 -0.0115 0.3187 0.9753
9.750 1.0320 0.03319 0.02478 -0.0113 0.2992 0.9807
10.000 1.0511 0.03413 0.02559 -0.0113 0.2823 0.9873
10.250 1.0686 0.03481 0.02616 -0.0110 0.2683 1.0000
10.500 1.0964 0.03576 0.02689 -0.0121 0.2547 1.0000
10.750 1.1132 0.03711 0.02833 -0.0124 0.2433 1.0000
11.000 1.1394 0.03823 0.02936 -0.0135 0.2329 1.0000
11.250 1.1630 0.03938 0.03046 -0.0143 0.2233 1.0000
11.500 1.1882 0.04065 0.03174 -0.0154 0.2148 1.0000
11.750 1.2121 0.04184 0.03290 -0.0163 0.2069 1.0000
12.000 1.2397 0.04314 0.03418 -0.0176 0.1998 1.0000
12.250 1.2585 0.04459 0.03573 -0.0181 0.1932 1.0000
12.500 1.2979 0.04559 0.03652 -0.0204 0.1865 1.0000
12.750 1.3055 0.04753 0.03874 -0.0199 0.1817 1.0000
13.000 1.3278 0.04894 0.04017 -0.0208 0.1763 1.0000
13.250 1.3633 0.05026 0.04136 -0.0227 0.1710 1.0000
13.500 1.3670 0.05250 0.04390 -0.0220 0.1673 1.0000
13.750 1.3803 0.05437 0.04588 -0.0222 0.1632 1.0000
14.000 1.4297 0.05533 0.04656 -0.0252 0.1580 1.0000
14.250 1.4200 0.05816 0.04978 -0.0235 0.1556 1.0000
14.500 1.4189 0.06092 0.05281 -0.0227 0.1527 1.0000
15.000 1.4581 0.06448 0.05639 -0.0241 0.1461 1.0000
15.250 1.4590 0.06763 0.05974 -0.0236 0.1438 1.0000
15.500 1.4354 0.07189 0.06439 -0.0220 0.1423 1.0000
15.750 1.4123 0.07654 0.06937 -0.0210 0.1408 1.0000
16.000 1.3886 0.08155 0.07468 -0.0205 0.1393 1.0000
16.250 1.3652 0.08687 0.08028 -0.0206 0.1378 1.0000
16.500 1.3627 0.09052 0.08404 -0.0212 0.1359 1.0000
16.750 1.2966 0.10122 0.09519 -0.0231 0.1358 1.0000
17.000 1.2763 0.10760 0.10174 -0.0252 0.1345 1.0000
17.250 1.2536 0.11482 0.10910 -0.0280 0.1333 1.0000
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Polar data table (+)
Polar graphs
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