HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Reynolds number: 50,000 Max Cl/Cd: 27.11 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hsnlf213-il-50000-n5.txt Download as CSV file: xf-hsnlf213-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HSNLF(1)-0213 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5536 0.10613 0.09959 -0.0301 1.0000 0.0505
-11.000 -0.5512 0.10106 0.09454 -0.0327 1.0000 0.0500
-10.750 -0.5533 0.09528 0.08877 -0.0365 1.0000 0.0495
-10.500 -0.5603 0.08938 0.08287 -0.0406 1.0000 0.0489
-10.250 -0.5714 0.08372 0.07718 -0.0443 1.0000 0.0484
-10.000 -0.5852 0.07860 0.07199 -0.0472 1.0000 0.0480
-9.750 -0.6006 0.07421 0.06750 -0.0488 1.0000 0.0476
-9.500 -0.6175 0.07077 0.06395 -0.0484 1.0000 0.0472
-9.250 -0.6350 0.06803 0.06107 -0.0463 1.0000 0.0470
-9.000 -0.6491 0.06525 0.05810 -0.0442 0.9933 0.0469
-8.500 -0.6458 0.05743 0.04945 -0.0446 0.9737 0.0480
-8.250 -0.6383 0.05382 0.04531 -0.0444 0.9667 0.0491
-8.000 -0.6282 0.05057 0.04149 -0.0437 0.9603 0.0500
-7.750 -0.6117 0.04740 0.03772 -0.0435 0.9557 0.0506
-7.500 -0.5947 0.04455 0.03459 -0.0430 0.9512 0.0514
-7.250 -0.5740 0.04219 0.03196 -0.0428 0.9471 0.0529
-7.000 -0.5500 0.04026 0.02981 -0.0431 0.9434 0.0558
-6.750 -0.5223 0.03822 0.02736 -0.0436 0.9404 0.0591
-6.500 -0.4967 0.03640 0.02511 -0.0431 0.9368 0.0612
-6.250 -0.4681 0.03465 0.02323 -0.0434 0.9338 0.0645
-6.000 -0.4382 0.03339 0.02187 -0.0438 0.9313 0.0701
-5.750 -0.4008 0.03212 0.02036 -0.0446 0.9295 0.0756
-5.500 -0.3678 0.03105 0.01930 -0.0454 0.9275 0.0843
-5.250 -0.3385 0.03006 0.01823 -0.0456 0.9253 0.0935
-5.000 -0.3216 0.02937 0.01751 -0.0440 0.9212 0.1053
-4.750 -0.3058 0.02856 0.01679 -0.0424 0.9175 0.1220
-4.500 -0.2916 0.02757 0.01608 -0.0407 0.9141 0.1558
-4.250 -0.2862 0.02586 0.01537 -0.0382 0.9107 0.2821
-4.000 -0.2682 0.02714 0.01855 -0.0300 0.9091 0.7112
-3.750 -0.2820 0.02731 0.01851 -0.0237 0.9027 0.7550
-3.500 -0.1614 0.03055 0.02124 -0.0290 0.9095 0.8774
-3.250 -0.1063 0.03043 0.02075 -0.0338 0.9088 0.8958
-3.000 -0.0727 0.03025 0.02033 -0.0356 0.9062 0.9053
-2.750 -0.0433 0.03010 0.01996 -0.0367 0.9031 0.9133
-2.500 -0.0128 0.02996 0.01963 -0.0381 0.9001 0.9204
-2.250 0.0147 0.02986 0.01937 -0.0390 0.8972 0.9269
-2.000 0.0500 0.02972 0.01905 -0.0413 0.8950 0.9320
-1.750 0.0683 0.02980 0.01904 -0.0406 0.8909 0.9389
-1.500 0.0981 0.02976 0.01889 -0.0420 0.8875 0.9439
-1.250 0.1274 0.02976 0.01879 -0.0433 0.8843 0.9487
-1.000 0.1533 0.02983 0.01878 -0.0439 0.8812 0.9532
-0.750 0.1775 0.02994 0.01884 -0.0443 0.8774 0.9570
-0.500 0.2019 0.03008 0.01894 -0.0449 0.8731 0.9606
-0.250 0.2275 0.03022 0.01904 -0.0454 0.8690 0.9639
0.250 0.2716 0.03068 0.01948 -0.0453 0.8602 0.9704
0.500 0.2970 0.03090 0.01971 -0.0459 0.8553 0.9731
0.750 0.3259 0.03108 0.01990 -0.0469 0.8511 0.9753
1.000 0.3441 0.03144 0.02031 -0.0462 0.8451 0.9784
1.250 0.3657 0.03175 0.02065 -0.0460 0.8391 0.9810
1.500 0.3945 0.03196 0.02092 -0.0467 0.8346 0.9827
1.750 0.4101 0.03241 0.02144 -0.0457 0.8263 0.9854
2.000 0.4396 0.03262 0.02173 -0.0465 0.8207 0.9871
2.250 0.4558 0.03308 0.02227 -0.0455 0.8120 0.9897
2.500 0.4839 0.03328 0.02257 -0.0458 0.8055 0.9911
2.750 0.4997 0.03374 0.02316 -0.0446 0.7958 0.9938
3.000 0.5323 0.03381 0.02335 -0.0454 0.7891 0.9949
3.250 0.5483 0.03422 0.02389 -0.0441 0.7775 0.9974
3.500 0.5690 0.03447 0.02427 -0.0432 0.7667 0.9993
3.750 0.6001 0.03428 0.02426 -0.0431 0.7574 1.0000
4.000 0.6145 0.03434 0.02446 -0.0406 0.7441 1.0000
4.250 0.6292 0.03426 0.02452 -0.0380 0.7297 1.0000
4.500 0.6466 0.03390 0.02431 -0.0354 0.7142 1.0000
4.750 0.6664 0.03322 0.02382 -0.0327 0.6976 1.0000
5.000 0.6727 0.03295 0.02369 -0.0286 0.6775 1.0000
5.250 0.6820 0.03240 0.02329 -0.0247 0.6562 1.0000
5.500 0.6891 0.03183 0.02286 -0.0205 0.6334 1.0000
5.750 0.6940 0.03122 0.02243 -0.0160 0.6083 1.0000
6.000 0.6885 0.03110 0.02241 -0.0106 0.5801 1.0000
6.250 0.6900 0.03054 0.02195 -0.0056 0.5475 1.0000
6.500 0.7062 0.02925 0.02067 -0.0016 0.4965 1.0000
6.750 0.7464 0.02753 0.01817 0.0010 0.3739 1.0000
7.000 0.7399 0.02836 0.01852 0.0060 0.3120 1.0000
7.250 0.7338 0.02955 0.01931 0.0101 0.2623 1.0000
7.500 0.7334 0.03101 0.02041 0.0127 0.2189 1.0000
7.750 0.7386 0.03254 0.02165 0.0145 0.1856 1.0000
8.000 0.7478 0.03403 0.02292 0.0158 0.1608 1.0000
8.500 0.7763 0.03673 0.02546 0.0177 0.1277 1.0000
8.750 0.7949 0.03796 0.02667 0.0184 0.1160 1.0000
9.000 0.8174 0.03915 0.02775 0.0190 0.1074 1.0000
9.250 0.8458 0.04020 0.02904 0.0192 0.0988 1.0000
9.500 0.8744 0.04144 0.03027 0.0193 0.0919 1.0000
9.750 0.9070 0.04291 0.03200 0.0191 0.0864 1.0000
10.000 0.9382 0.04462 0.03377 0.0186 0.0824 1.0000
10.250 0.9654 0.04675 0.03611 0.0183 0.0788 1.0000
10.500 0.9818 0.04894 0.03867 0.0188 0.0754 1.0000
10.750 0.9967 0.05122 0.04121 0.0193 0.0727 1.0000
11.000 1.0111 0.05374 0.04397 0.0198 0.0710 1.0000
11.250 1.0230 0.05640 0.04682 0.0203 0.0696 1.0000
11.500 1.0339 0.05930 0.04990 0.0207 0.0684 1.0000
11.750 1.0316 0.06257 0.05346 0.0219 0.0676 1.0000
12.000 1.0198 0.06613 0.05740 0.0231 0.0669 1.0000
12.250 1.0041 0.07009 0.06169 0.0239 0.0664 1.0000
12.500 0.9850 0.07453 0.06644 0.0240 0.0660 1.0000
12.750 0.9626 0.07960 0.07177 0.0234 0.0659 1.0000
13.000 0.9369 0.08547 0.07787 0.0219 0.0659 1.0000
13.250 0.9083 0.09238 0.08498 0.0191 0.0661 1.0000
13.500 0.8778 0.10058 0.09330 0.0149 0.0665 1.0000
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Polar data table (+)
Polar graphs
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