FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il) Reynolds number: 50,000 Max Cl/Cd: 5.76 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxs21158-il-50000.txt Download as CSV file: xf-fxs21158-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX S 02/1-158 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3004 0.12896 0.12271 -0.0220 1.0000 0.2686
-10.750 -0.2974 0.12647 0.12030 -0.0224 1.0000 0.2817
-10.500 -0.3044 0.12573 0.11965 -0.0229 1.0000 0.2942
-10.250 -0.2820 0.12068 0.11462 -0.0226 1.0000 0.3074
-10.000 -0.2662 0.11639 0.11038 -0.0228 1.0000 0.3163
-9.750 -0.2648 0.11391 0.10796 -0.0232 1.0000 0.3267
-9.500 -0.2709 0.11271 0.10689 -0.0234 1.0000 0.3386
-9.250 -0.2487 0.10815 0.10237 -0.0235 1.0000 0.3492
-9.000 -0.2398 0.10495 0.09928 -0.0237 1.0000 0.3580
-8.750 -0.2398 0.10287 0.09735 -0.0238 1.0000 0.3692
-8.500 -0.2462 0.10193 0.09661 -0.0235 1.0000 0.3811
-8.250 -0.2300 0.09802 0.09289 -0.0236 1.0000 0.3856
-8.000 -0.2445 0.09897 0.09416 -0.0229 0.9860 0.3894
-7.750 -0.2918 0.08910 0.08437 -0.0433 0.9612 0.2806
-7.500 -0.3786 0.06388 0.05902 -0.0795 0.9351 0.1632
-7.250 -0.3720 0.05501 0.04945 -0.0911 0.9186 0.1483
-7.000 -0.3512 0.04907 0.04253 -0.0978 0.9037 0.1385
-6.750 -0.3197 0.04516 0.03811 -0.1014 0.8907 0.1366
-6.500 -0.2884 0.04214 0.03446 -0.1041 0.8785 0.1377
-6.250 -0.2528 0.03945 0.03126 -0.1062 0.8682 0.1376
-6.000 -0.2260 0.03766 0.02906 -0.1064 0.8563 0.1370
-5.750 -0.1978 0.03618 0.02725 -0.1065 0.8457 0.1375
-5.500 -0.1634 0.03478 0.02554 -0.1069 0.8370 0.1393
-5.250 -0.1372 0.03381 0.02453 -0.1059 0.8272 0.1425
-5.000 -0.1137 0.03315 0.02391 -0.1046 0.8185 0.1477
-4.750 -0.0875 0.03249 0.02318 -0.1036 0.8112 0.1555
-4.500 -0.0720 0.03216 0.02294 -0.1022 0.8031 0.1677
-4.250 -0.0496 0.03114 0.02211 -0.1022 0.7965 0.1955
-4.000 -0.0398 0.02969 0.02210 -0.1018 0.7892 0.3084
-3.750 -0.0357 0.03485 0.02765 -0.0895 0.7826 0.5710
-3.500 -0.0395 0.03756 0.03045 -0.0784 0.7765 0.6214
-3.250 -0.0402 0.03915 0.03200 -0.0701 0.7706 0.6617
-3.000 -0.0360 0.04048 0.03329 -0.0592 0.7665 0.7155
-2.750 -0.0462 0.04141 0.03423 -0.0524 0.7612 0.7403
-2.500 -0.0484 0.04197 0.03472 -0.0471 0.7568 0.7655
-2.250 -0.0342 0.04212 0.03466 -0.0441 0.7531 0.7887
-2.000 -0.0345 0.04252 0.03495 -0.0411 0.7494 0.8010
-1.750 -0.0513 0.04311 0.03554 -0.0376 0.7462 0.8082
-1.500 -0.0583 0.04358 0.03595 -0.0347 0.7442 0.8162
-1.250 -0.0597 0.04407 0.03634 -0.0330 0.7436 0.8239
-1.000 -0.0556 0.04464 0.03680 -0.0322 0.7437 0.8308
-0.750 -0.0465 0.04528 0.03729 -0.0327 0.7441 0.8362
-0.500 -0.0358 0.04589 0.03778 -0.0328 0.7444 0.8408
-0.250 -0.0237 0.04663 0.03839 -0.0335 0.7455 0.8463
0.000 -0.0082 0.04747 0.03908 -0.0348 0.7479 0.8519
0.250 0.0116 0.04841 0.03989 -0.0363 0.7520 0.8575
0.500 -0.0084 0.04979 0.04130 -0.0352 0.7764 0.8624
0.750 -0.2131 0.04502 0.03737 -0.0081 1.0000 0.8627
1.000 -0.1777 0.04666 0.03879 -0.0123 0.9939 0.8703
1.250 -0.1392 0.04846 0.04037 -0.0173 0.9842 0.8769
1.500 -0.1031 0.05005 0.04176 -0.0217 0.9723 0.8837
1.750 -0.0692 0.05155 0.04311 -0.0256 0.9599 0.8913
2.000 -0.0357 0.05307 0.04451 -0.0294 0.9472 0.8990
2.250 -0.0020 0.05468 0.04600 -0.0332 0.9345 0.9090
2.500 0.0331 0.05644 0.04770 -0.0373 0.9231 0.9221
2.750 0.0791 0.05902 0.05023 -0.0437 0.9120 0.9422
3.000 0.1103 0.06034 0.05149 -0.0474 0.8975 1.0000
3.250 0.1388 0.06176 0.05279 -0.0507 0.8842 1.0000
3.500 0.1675 0.06340 0.05433 -0.0539 0.8713 1.0000
3.750 0.1963 0.06523 0.05605 -0.0572 0.8590 1.0000
4.000 0.2272 0.06742 0.05814 -0.0608 0.8491 1.0000
4.250 0.2649 0.07015 0.06077 -0.0655 0.8395 1.0000
4.500 0.2867 0.07164 0.06219 -0.0675 0.8272 1.0000
4.750 0.3105 0.07351 0.06398 -0.0697 0.8156 1.0000
5.000 0.3383 0.07584 0.06623 -0.0725 0.8054 1.0000
5.250 0.3760 0.07894 0.06925 -0.0767 0.7954 1.0000
5.500 0.3945 0.08045 0.07072 -0.0778 0.7824 1.0000
5.750 0.4127 0.08220 0.07242 -0.0789 0.7702 1.0000
6.000 0.4323 0.08429 0.07446 -0.0802 0.7600 1.0000
6.250 0.4667 0.08754 0.07766 -0.0833 0.7521 1.0000
6.500 0.4763 0.08883 0.07895 -0.0832 0.7404 1.0000
6.750 0.4913 0.09088 0.08098 -0.0838 0.7309 1.0000
7.000 0.5246 0.09431 0.08439 -0.0864 0.7229 1.0000
7.250 0.5323 0.09563 0.08571 -0.0860 0.7109 1.0000
7.500 0.5437 0.09765 0.08777 -0.0861 0.7012 1.0000
7.750 0.5757 0.10127 0.09140 -0.0884 0.6939 1.0000
8.000 0.5830 0.10272 0.09288 -0.0879 0.6813 1.0000
8.250 0.5939 0.10473 0.09492 -0.0879 0.6693 1.0000
8.500 0.6083 0.10723 0.09747 -0.0884 0.6595 1.0000
8.750 0.6375 0.11076 0.10109 -0.0901 0.6506 1.0000
9.000 0.6395 0.11224 0.10262 -0.0895 0.6392 1.0000
9.250 0.6498 0.11480 0.10524 -0.0898 0.6307 1.0000
9.500 0.6752 0.11827 0.10880 -0.0912 0.6221 1.0000
9.750 0.6779 0.12003 0.11063 -0.0908 0.6106 1.0000
10.000 0.6874 0.12257 0.11326 -0.0911 0.6000 1.0000
10.250 0.7144 0.12668 0.11752 -0.0925 0.5914 1.0000
10.500 0.7256 0.12901 0.11995 -0.0928 0.5788 1.0000
10.750 0.7289 0.13102 0.12205 -0.0927 0.5666 1.0000
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