NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: NACA M24 AIRFOIL (m24-il) Reynolds number: 100,000 Max Cl/Cd: 45.23 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m24-il-100000-n5.txt Download as CSV file: xf-m24-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M24 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2700 0.09977 0.09461 -0.0133 0.6902 0.0554
-7.750 -0.2678 0.09692 0.09172 -0.0166 0.6862 0.0568
-7.500 -0.2690 0.09496 0.08974 -0.0213 0.6810 0.0578
-7.250 -0.2644 0.09324 0.08789 -0.0273 0.6763 0.0583
-7.000 -0.2547 0.08845 0.08310 -0.0264 0.6720 0.0590
-6.750 -0.2428 0.08460 0.07924 -0.0248 0.6675 0.0601
-6.500 -0.2308 0.08157 0.07619 -0.0254 0.6621 0.0616
-6.250 -0.2188 0.07870 0.07325 -0.0267 0.6576 0.0631
-6.000 -0.2059 0.07592 0.07035 -0.0283 0.6539 0.0650
-5.750 -0.1861 0.07405 0.06828 -0.0325 0.6490 0.0683
-5.500 -0.1632 0.07288 0.06676 -0.0361 0.6442 0.0692
-5.250 -0.1507 0.06834 0.06220 -0.0361 0.6401 0.0698
-5.000 -0.1387 0.06458 0.05844 -0.0351 0.6366 0.0708
-4.750 -0.1226 0.06182 0.05568 -0.0350 0.6313 0.0728
-4.500 -0.1038 0.05947 0.05324 -0.0354 0.6265 0.0757
-4.250 -0.0803 0.05761 0.05113 -0.0365 0.6225 0.0801
-4.000 -0.0484 0.05767 0.05059 -0.0378 0.6188 0.0824
-3.750 -0.0317 0.05349 0.04644 -0.0380 0.6138 0.0831
-3.500 -0.0138 0.05040 0.04331 -0.0378 0.6094 0.0840
-3.250 0.0061 0.04797 0.04076 -0.0374 0.6056 0.0849
-3.000 0.0280 0.04584 0.03847 -0.0372 0.6018 0.0858
-2.500 0.0834 0.03943 0.03121 -0.0364 0.5929 0.0578
-2.250 0.1057 0.03756 0.02919 -0.0360 0.5892 0.0565
-2.000 0.1302 0.03568 0.02707 -0.0355 0.5856 0.0548
-1.750 0.1563 0.03376 0.02491 -0.0352 0.5804 0.0532
-1.500 0.1833 0.03163 0.02240 -0.0345 0.5762 0.0516
-1.250 0.2108 0.02961 0.01992 -0.0338 0.5727 0.0506
-1.000 0.2382 0.02821 0.01820 -0.0334 0.5690 0.0506
-0.750 0.2653 0.02751 0.01743 -0.0336 0.5637 0.0521
-0.500 0.2930 0.02662 0.01632 -0.0334 0.5593 0.0537
-0.250 0.3217 0.02557 0.01497 -0.0332 0.5559 0.0542
0.000 0.3507 0.02470 0.01390 -0.0333 0.5517 0.0545
0.250 0.3798 0.02400 0.01306 -0.0335 0.5466 0.0552
0.500 0.4090 0.02334 0.01225 -0.0336 0.5424 0.0561
0.750 0.4383 0.02275 0.01149 -0.0336 0.5391 0.0573
1.000 0.4665 0.02243 0.01117 -0.0339 0.5345 0.0595
1.250 0.4954 0.02226 0.01107 -0.0343 0.5296 0.0635
1.500 0.5267 0.02198 0.01070 -0.0349 0.5256 0.0677
1.750 0.5557 0.02167 0.01029 -0.0350 0.5225 0.0717
2.000 0.5819 0.02171 0.01036 -0.0350 0.5173 0.0789
2.250 0.6075 0.02166 0.01033 -0.0347 0.5129 0.0942
2.500 0.6325 0.02150 0.01027 -0.0342 0.5093 0.1404
3.000 0.8053 0.02063 0.01103 -0.0586 0.4978 1.0000
3.250 0.8298 0.02082 0.01111 -0.0582 0.4941 1.0000
3.500 0.8545 0.02094 0.01110 -0.0576 0.4912 1.0000
3.750 0.8781 0.02131 0.01147 -0.0573 0.4866 1.0000
4.000 0.9016 0.02166 0.01182 -0.0570 0.4819 1.0000
4.250 0.9254 0.02186 0.01196 -0.0564 0.4782 1.0000
4.500 0.9497 0.02199 0.01200 -0.0559 0.4753 1.0000
4.750 0.9720 0.02247 0.01254 -0.0555 0.4710 1.0000
5.000 0.9941 0.02293 0.01304 -0.0550 0.4665 1.0000
5.250 1.0170 0.02320 0.01330 -0.0544 0.4629 1.0000
5.500 1.0408 0.02336 0.01341 -0.0537 0.4600 1.0000
5.750 1.0620 0.02384 0.01395 -0.0531 0.4559 1.0000
6.000 1.0819 0.02443 0.01463 -0.0524 0.4513 1.0000
6.250 1.1034 0.02482 0.01504 -0.0517 0.4478 1.0000
6.500 1.1263 0.02506 0.01529 -0.0510 0.4450 1.0000
6.750 1.1484 0.02539 0.01562 -0.0503 0.4421 1.0000
7.000 1.1637 0.02629 0.01670 -0.0492 0.4371 1.0000
7.250 1.1826 0.02681 0.01730 -0.0482 0.4332 1.0000
7.500 1.2041 0.02711 0.01763 -0.0474 0.4302 1.0000
7.750 1.2276 0.02732 0.01783 -0.0468 0.4279 1.0000
8.000 1.2382 0.02846 0.01917 -0.0451 0.4235 1.0000
8.250 1.2509 0.02936 0.02022 -0.0436 0.4193 1.0000
8.500 1.2688 0.02985 0.02077 -0.0424 0.4160 1.0000
8.750 1.2915 0.03005 0.02100 -0.0417 0.4135 1.0000
9.000 1.3055 0.03084 0.02191 -0.0402 0.4103 1.0000
9.250 1.3019 0.03262 0.02391 -0.0371 0.4054 1.0000
9.500 1.3106 0.03358 0.02498 -0.0351 0.4018 1.0000
9.750 1.3316 0.03380 0.02526 -0.0342 0.3989 1.0000
10.000 1.3483 0.03414 0.02567 -0.0328 0.3949 1.0000
10.250 1.2843 0.03902 0.03072 -0.0247 0.3889 1.0000
10.500 1.3046 0.03895 0.03071 -0.0236 0.3846 1.0000
10.750 1.3273 0.03846 0.03027 -0.0225 0.3786 1.0000
11.000 1.2067 0.05189 0.04382 -0.0181 0.3689 1.0000
11.250 1.1998 0.05503 0.04702 -0.0172 0.3629 1.0000
11.500 1.1592 0.06254 0.05459 -0.0169 0.3525 1.0000
11.750 1.1747 0.06300 0.05513 -0.0161 0.3483 1.0000
12.250 1.3020 0.05084 0.04309 -0.0136 0.3352 1.0000
12.750 1.0752 0.08835 0.08075 -0.0175 0.3107 1.0000
13.750 1.1433 0.08774 0.08053 -0.0148 0.2833 1.0000
14.000 1.1898 0.08305 0.07597 -0.0134 0.2761 1.0000
14.250 1.1513 0.09205 0.08504 -0.0149 0.2663 1.0000
14.500 1.1605 0.09340 0.08650 -0.0148 0.2565 1.0000
14.750 1.1653 0.09551 0.08870 -0.0150 0.2444 1.0000
15.000 1.1619 0.09907 0.09233 -0.0156 0.2313 1.0000
15.250 1.1548 0.10331 0.09666 -0.0164 0.2170 1.0000
15.500 1.1507 0.10707 0.10046 -0.0172 0.1980 1.0000
15.750 1.1680 0.10624 0.09880 -0.0163 0.1217 1.0000
16.000 1.1457 0.11272 0.10491 -0.0178 0.0901 1.0000
16.250 1.1297 0.11855 0.11058 -0.0192 0.0733 1.0000
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Polar data table (+)
Polar graphs
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