NACA 2410 (naca2410-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2410 (naca2410-il) Reynolds number: 500,000 Max Cl/Cd: 86.33 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2410-il-500000.txt Download as CSV file: xf-naca2410-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.9101 0.04637 0.04339 -0.0565 1.0000 0.0145
-12.250 -0.9304 0.04070 0.03747 -0.0607 1.0000 0.0145
-12.000 -0.9458 0.03698 0.03350 -0.0599 1.0000 0.0146
-11.750 -0.9454 0.03434 0.03068 -0.0591 1.0000 0.0149
-11.500 -0.9352 0.03280 0.02903 -0.0582 1.0000 0.0152
-11.250 -0.9218 0.03159 0.02772 -0.0573 1.0000 0.0156
-11.000 -0.9078 0.03041 0.02642 -0.0562 1.0000 0.0161
-10.750 -0.8947 0.02904 0.02487 -0.0550 1.0000 0.0168
-10.500 -0.8820 0.02758 0.02321 -0.0535 1.0000 0.0174
-10.250 -0.8684 0.02620 0.02161 -0.0519 1.0000 0.0180
-10.000 -0.8559 0.02453 0.01967 -0.0501 1.0000 0.0185
-9.750 -0.8444 0.02265 0.01763 -0.0482 1.0000 0.0194
-9.500 -0.8258 0.02212 0.01707 -0.0469 1.0000 0.0201
-9.250 -0.8070 0.02159 0.01648 -0.0455 1.0000 0.0210
-9.000 -0.7886 0.02092 0.01568 -0.0440 1.0000 0.0220
-8.750 -0.7694 0.02041 0.01504 -0.0426 1.0000 0.0231
-8.500 -0.7529 0.01913 0.01357 -0.0410 1.0000 0.0244
-8.250 -0.7341 0.01849 0.01292 -0.0397 1.0000 0.0256
-8.000 -0.7141 0.01811 0.01251 -0.0384 1.0000 0.0269
-7.750 -0.6938 0.01766 0.01196 -0.0372 1.0000 0.0285
-7.500 -0.6728 0.01743 0.01164 -0.0360 1.0000 0.0298
-7.250 -0.6539 0.01613 0.01022 -0.0348 1.0000 0.0320
-7.000 -0.6274 0.01573 0.00983 -0.0349 0.9993 0.0339
-6.750 -0.5916 0.01531 0.00933 -0.0367 0.9972 0.0362
-6.500 -0.5541 0.01513 0.00905 -0.0388 0.9952 0.0380
-6.250 -0.5209 0.01382 0.00768 -0.0405 0.9931 0.0410
-6.000 -0.4857 0.01341 0.00726 -0.0422 0.9901 0.0435
-5.750 -0.4494 0.01302 0.00681 -0.0441 0.9877 0.0458
-5.500 -0.4122 0.01271 0.00644 -0.0461 0.9857 0.0475
-5.250 -0.3787 0.01188 0.00557 -0.0476 0.9829 0.0504
-5.000 -0.3446 0.01145 0.00514 -0.0490 0.9793 0.0532
-4.750 -0.3081 0.01110 0.00475 -0.0509 0.9768 0.0562
-4.500 -0.2701 0.01078 0.00439 -0.0530 0.9750 0.0587
-4.250 -0.2354 0.01026 0.00391 -0.0545 0.9717 0.0659
-4.000 -0.2022 0.00987 0.00356 -0.0556 0.9671 0.0772
-3.750 -0.1676 0.00940 0.00324 -0.0571 0.9636 0.1062
-3.500 -0.1361 0.00905 0.00301 -0.0579 0.9584 0.1389
-3.250 -0.1061 0.00874 0.00281 -0.0583 0.9518 0.1704
-3.000 -0.0757 0.00844 0.00263 -0.0588 0.9458 0.2045
-2.750 -0.0485 0.00816 0.00247 -0.0585 0.9369 0.2410
-2.500 -0.0208 0.00788 0.00233 -0.0584 0.9284 0.2831
-2.250 0.0061 0.00760 0.00219 -0.0581 0.9190 0.3296
-2.000 0.0322 0.00731 0.00208 -0.0576 0.9078 0.3854
-1.750 0.0580 0.00695 0.00197 -0.0571 0.8968 0.4657
-1.500 0.0832 0.00657 0.00190 -0.0564 0.8852 0.5614
-1.250 0.1081 0.00626 0.00185 -0.0556 0.8723 0.6473
-1.000 0.1322 0.00598 0.00182 -0.0545 0.8583 0.7317
-0.750 0.1560 0.00577 0.00182 -0.0531 0.8437 0.8054
-0.500 0.1796 0.00565 0.00182 -0.0517 0.8285 0.8664
-0.250 0.2051 0.00562 0.00184 -0.0505 0.8127 0.9203
0.000 0.2385 0.00568 0.00185 -0.0512 0.7963 0.9579
0.250 0.2767 0.00575 0.00184 -0.0531 0.7785 0.9778
0.500 0.3175 0.00583 0.00183 -0.0558 0.7591 0.9899
0.750 0.3600 0.00592 0.00182 -0.0589 0.7385 0.9985
1.000 0.3884 0.00602 0.00180 -0.0590 0.7175 1.0000
1.250 0.4134 0.00611 0.00180 -0.0584 0.6958 1.0000
1.500 0.4383 0.00623 0.00181 -0.0577 0.6748 1.0000
1.750 0.4633 0.00635 0.00183 -0.0570 0.6535 1.0000
2.000 0.4883 0.00649 0.00188 -0.0564 0.6323 1.0000
2.250 0.5131 0.00664 0.00193 -0.0557 0.6119 1.0000
2.500 0.5379 0.00679 0.00199 -0.0550 0.5885 1.0000
2.750 0.5622 0.00699 0.00207 -0.0542 0.5605 1.0000
3.000 0.5868 0.00719 0.00216 -0.0535 0.5357 1.0000
3.250 0.6120 0.00737 0.00226 -0.0529 0.5128 1.0000
3.500 0.6370 0.00758 0.00238 -0.0523 0.4889 1.0000
3.750 0.6621 0.00779 0.00250 -0.0518 0.4631 1.0000
4.000 0.6873 0.00802 0.00263 -0.0512 0.4363 1.0000
4.250 0.7124 0.00827 0.00279 -0.0507 0.4084 1.0000
4.500 0.7373 0.00854 0.00297 -0.0502 0.3792 1.0000
4.750 0.7620 0.00887 0.00316 -0.0496 0.3453 1.0000
5.000 0.7861 0.00927 0.00340 -0.0490 0.3059 1.0000
5.250 0.8095 0.00976 0.00369 -0.0483 0.2602 1.0000
5.500 0.8323 0.01034 0.00403 -0.0476 0.2103 1.0000
5.750 0.8542 0.01103 0.00446 -0.0468 0.1580 1.0000
6.000 0.8754 0.01183 0.00495 -0.0459 0.1058 1.0000
6.250 0.8969 0.01259 0.00550 -0.0449 0.0705 1.0000
6.500 0.9200 0.01316 0.00600 -0.0442 0.0586 1.0000
6.750 0.9431 0.01372 0.00658 -0.0434 0.0532 1.0000
7.000 0.9672 0.01414 0.00704 -0.0427 0.0503 1.0000
7.250 0.9905 0.01464 0.00755 -0.0420 0.0477 1.0000
7.500 1.0119 0.01533 0.00826 -0.0410 0.0450 1.0000
7.750 1.0332 0.01601 0.00901 -0.0400 0.0432 1.0000
8.000 1.0563 0.01647 0.00954 -0.0393 0.0418 1.0000
8.250 1.0787 0.01699 0.01011 -0.0385 0.0401 1.0000
8.500 1.1005 0.01755 0.01071 -0.0376 0.0383 1.0000
8.750 1.1201 0.01832 0.01150 -0.0365 0.0364 1.0000
9.000 1.1350 0.01962 0.01287 -0.0346 0.0345 1.0000
9.250 1.1572 0.02005 0.01339 -0.0339 0.0334 1.0000
9.500 1.1783 0.02060 0.01401 -0.0329 0.0318 1.0000
9.750 1.1984 0.02117 0.01463 -0.0320 0.0301 1.0000
10.000 1.2159 0.02199 0.01546 -0.0307 0.0285 1.0000
10.250 1.2265 0.02368 0.01724 -0.0284 0.0269 1.0000
10.500 1.2464 0.02410 0.01777 -0.0274 0.0257 1.0000
10.750 1.2639 0.02469 0.01845 -0.0261 0.0243 1.0000
11.000 1.2791 0.02528 0.01908 -0.0244 0.0230 1.0000
11.250 1.2912 0.02613 0.01995 -0.0225 0.0219 1.0000
11.500 1.2951 0.02802 0.02194 -0.0197 0.0208 1.0000
11.750 1.3087 0.02875 0.02279 -0.0181 0.0200 1.0000
12.000 1.3200 0.02975 0.02391 -0.0164 0.0191 1.0000
12.250 1.3306 0.03078 0.02505 -0.0148 0.0183 1.0000
12.500 1.3411 0.03180 0.02612 -0.0134 0.0175 1.0000
12.750 1.3500 0.03302 0.02738 -0.0121 0.0169 1.0000
13.000 1.3490 0.03537 0.02982 -0.0102 0.0162 1.0000
13.250 1.3528 0.03733 0.03194 -0.0090 0.0157 1.0000
13.500 1.3584 0.03914 0.03390 -0.0081 0.0152 1.0000
13.750 1.3616 0.04132 0.03622 -0.0074 0.0148 1.0000
14.000 1.3633 0.04372 0.03877 -0.0069 0.0143 1.0000
14.250 1.3644 0.04632 0.04149 -0.0067 0.0140 1.0000
14.500 1.3646 0.04913 0.04441 -0.0068 0.0136 1.0000
14.750 1.3641 0.05213 0.04753 -0.0073 0.0133 1.0000
15.000 1.3620 0.05548 0.05098 -0.0080 0.0131 1.0000
15.250 1.3572 0.05930 0.05492 -0.0090 0.0129 1.0000
15.500 1.3488 0.06374 0.05949 -0.0104 0.0127 1.0000
15.750 1.3362 0.06895 0.06484 -0.0121 0.0125 1.0000
16.000 1.3202 0.07486 0.07092 -0.0143 0.0123 1.0000
16.250 1.3009 0.08158 0.07782 -0.0170 0.0122 1.0000
16.500 1.2801 0.08889 0.08532 -0.0203 0.0122 1.0000
17.000 1.2385 0.10461 0.10139 -0.0284 0.0121 1.0000
17.250 1.2175 0.11304 0.10999 -0.0330 0.0121 1.0000
17.500 1.1951 0.12212 0.11924 -0.0381 0.0121 1.0000
17.750 1.1742 0.13137 0.12864 -0.0435 0.0122 1.0000
18.000 1.1536 0.14101 0.13841 -0.0492 0.0123 1.0000
18.250 1.1250 0.15325 0.15083 -0.0565 0.0124 1.0000
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