NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il) Reynolds number: 100,000 Max Cl/Cd: 48.87 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n5h10-il-100000-n5.txt Download as CSV file: xf-n5h10-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-10 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3909 0.10574 0.10165 -0.0123 1.0000 0.0465
-10.000 -0.3915 0.10162 0.09755 -0.0147 0.9634 0.0478
-9.750 -0.4008 0.09716 0.09310 -0.0205 0.9365 0.0500
-9.250 -0.3908 0.08581 0.08165 -0.0222 0.9151 0.0347
-9.000 -0.3926 0.08111 0.07693 -0.0239 0.9064 0.0330
-8.000 -0.4987 0.06916 0.06451 -0.0355 0.8975 0.0264
-7.750 -0.4984 0.06515 0.06036 -0.0354 0.8885 0.0260
-7.500 -0.4969 0.06109 0.05613 -0.0351 0.8799 0.0258
-7.250 -0.4933 0.05706 0.05188 -0.0346 0.8722 0.0257
-7.000 -0.4884 0.05301 0.04755 -0.0336 0.8652 0.0256
-6.750 -0.4810 0.04903 0.04327 -0.0324 0.8581 0.0257
-6.500 -0.4719 0.04517 0.03893 -0.0306 0.8518 0.0262
-6.250 -0.4624 0.04140 0.03474 -0.0290 0.8453 0.0274
-6.000 -0.4475 0.03959 0.03283 -0.0281 0.8394 0.0293
-5.750 -0.4315 0.03689 0.02976 -0.0267 0.8336 0.0303
-5.500 -0.4142 0.03410 0.02652 -0.0251 0.8276 0.0311
-5.250 -0.3951 0.03171 0.02364 -0.0234 0.8226 0.0330
-5.000 -0.3729 0.02964 0.02104 -0.0222 0.8165 0.0362
-4.750 -0.3495 0.02783 0.01864 -0.0208 0.8116 0.0379
-4.500 -0.3257 0.02573 0.01635 -0.0204 0.8066 0.0408
-4.250 -0.3004 0.02472 0.01515 -0.0200 0.8011 0.0454
-4.000 -0.2736 0.02339 0.01352 -0.0194 0.7967 0.0482
-3.750 -0.2468 0.02229 0.01224 -0.0192 0.7914 0.0525
-3.500 -0.2207 0.02138 0.01129 -0.0189 0.7863 0.0564
-3.250 -0.1950 0.02056 0.01036 -0.0183 0.7823 0.0592
-3.000 -0.1695 0.01991 0.00961 -0.0179 0.7773 0.0624
-2.750 -0.1453 0.01931 0.00900 -0.0174 0.7722 0.0681
-2.500 -0.1213 0.01882 0.00841 -0.0165 0.7682 0.0727
-2.250 -0.0963 0.01843 0.00790 -0.0160 0.7634 0.0773
-2.000 -0.0711 0.01799 0.00746 -0.0156 0.7585 0.0861
-1.750 -0.0453 0.01750 0.00706 -0.0151 0.7548 0.1144
-1.500 0.1608 0.01597 0.00797 -0.0460 0.7576 1.0000
-1.250 0.1841 0.01596 0.00780 -0.0453 0.7536 1.0000
-1.000 0.2084 0.01598 0.00771 -0.0450 0.7487 1.0000
-0.750 0.2327 0.01600 0.00765 -0.0447 0.7439 1.0000
-0.500 0.2565 0.01603 0.00758 -0.0441 0.7402 1.0000
-0.250 0.2804 0.01607 0.00754 -0.0436 0.7366 1.0000
0.250 0.3291 0.01621 0.00761 -0.0430 0.7274 1.0000
0.500 0.3527 0.01624 0.00760 -0.0424 0.7243 1.0000
0.750 0.3774 0.01638 0.00775 -0.0422 0.7198 1.0000
1.000 0.4016 0.01648 0.00786 -0.0419 0.7150 1.0000
1.250 0.4249 0.01650 0.00787 -0.0411 0.7110 1.0000
1.500 0.4487 0.01659 0.00799 -0.0406 0.7055 1.0000
1.750 0.4724 0.01666 0.00810 -0.0400 0.7000 1.0000
2.000 0.4956 0.01667 0.00813 -0.0392 0.6961 1.0000
2.250 0.5194 0.01682 0.00837 -0.0388 0.6902 1.0000
2.500 0.5429 0.01690 0.00851 -0.0381 0.6850 1.0000
2.750 0.5660 0.01690 0.00856 -0.0372 0.6812 1.0000
3.000 0.5895 0.01709 0.00890 -0.0368 0.6745 1.0000
3.250 0.6122 0.01703 0.00890 -0.0356 0.6683 1.0000
3.500 0.6343 0.01693 0.00889 -0.0344 0.6573 1.0000
3.750 0.6559 0.01671 0.00873 -0.0328 0.6450 1.0000
4.000 0.6774 0.01644 0.00854 -0.0311 0.6297 1.0000
4.250 0.6983 0.01609 0.00821 -0.0291 0.6101 1.0000
4.500 0.7192 0.01594 0.00814 -0.0275 0.5855 1.0000
4.750 0.7403 0.01588 0.00815 -0.0261 0.5598 1.0000
5.000 0.7614 0.01591 0.00832 -0.0248 0.5347 1.0000
5.250 0.7809 0.01598 0.00840 -0.0231 0.4807 1.0000
5.500 0.7928 0.01663 0.00831 -0.0202 0.3508 1.0000
5.750 0.8031 0.01790 0.00914 -0.0180 0.2612 1.0000
6.250 0.8168 0.02076 0.01117 -0.0129 0.1110 1.0000
6.500 0.8261 0.02175 0.01209 -0.0103 0.0848 1.0000
6.750 0.8351 0.02264 0.01295 -0.0076 0.0692 1.0000
7.000 0.8433 0.02349 0.01383 -0.0047 0.0616 1.0000
7.250 0.8503 0.02434 0.01468 -0.0017 0.0547 1.0000
7.500 0.8568 0.02521 0.01561 0.0014 0.0500 1.0000
7.750 0.8626 0.02615 0.01661 0.0045 0.0464 1.0000
8.000 0.8650 0.02738 0.01779 0.0078 0.0426 1.0000
8.250 0.8728 0.02844 0.01898 0.0105 0.0391 1.0000
8.500 0.8806 0.02964 0.02028 0.0132 0.0367 1.0000
8.750 0.8892 0.03109 0.02171 0.0156 0.0338 1.0000
9.000 0.9052 0.03274 0.02347 0.0171 0.0307 1.0000
9.250 0.9269 0.03454 0.02549 0.0181 0.0287 1.0000
9.500 0.9444 0.03637 0.02751 0.0193 0.0265 1.0000
9.750 0.9561 0.03810 0.02933 0.0208 0.0244 1.0000
10.000 0.9737 0.04146 0.03280 0.0212 0.0227 1.0000
10.250 0.9815 0.04364 0.03535 0.0233 0.0221 1.0000
10.500 0.9848 0.04612 0.03818 0.0257 0.0217 1.0000
10.750 0.9835 0.04875 0.04115 0.0280 0.0213 1.0000
11.000 0.9781 0.05156 0.04429 0.0301 0.0208 1.0000
11.250 0.9697 0.05462 0.04772 0.0319 0.0204 1.0000
11.500 0.9589 0.05788 0.05126 0.0332 0.0199 1.0000
11.750 0.9460 0.06154 0.05518 0.0340 0.0197 1.0000
12.000 0.9318 0.06535 0.05923 0.0341 0.0192 1.0000
12.250 0.9145 0.06995 0.06405 0.0336 0.0193 1.0000
12.500 0.8969 0.07488 0.06918 0.0323 0.0195 1.0000
12.750 0.8763 0.08057 0.07499 0.0301 0.0193 1.0000
13.000 0.8550 0.08708 0.08166 0.0270 0.0198 1.0000
13.250 0.8334 0.09439 0.08910 0.0228 0.0200 1.0000
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