NACA 2410 (naca2410-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 2410 (naca2410-il) Reynolds number: 500,000 Max Cl/Cd: 75.39 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2410-il-500000-n5.txt Download as CSV file: xf-naca2410-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8770 0.08888 0.08623 -0.0213 1.0000 0.0099
-14.000 -1.0205 0.05664 0.05364 -0.0426 1.0000 0.0089
-13.750 -1.0662 0.04080 0.03737 -0.0592 1.0000 0.0087
-13.500 -1.0787 0.03671 0.03307 -0.0610 1.0000 0.0088
-13.250 -1.0827 0.03421 0.03041 -0.0600 1.0000 0.0089
-13.000 -1.0776 0.03214 0.02817 -0.0593 1.0000 0.0091
-12.750 -1.0687 0.03035 0.02622 -0.0584 1.0000 0.0093
-12.500 -1.0573 0.02875 0.02445 -0.0575 1.0000 0.0096
-12.250 -1.0441 0.02730 0.02282 -0.0566 1.0000 0.0098
-12.000 -1.0293 0.02598 0.02135 -0.0556 1.0000 0.0102
-11.750 -1.0134 0.02479 0.01999 -0.0545 1.0000 0.0105
-11.500 -0.9965 0.02372 0.01877 -0.0534 1.0000 0.0108
-11.250 -0.9810 0.02252 0.01746 -0.0522 1.0000 0.0113
-11.000 -0.9631 0.02164 0.01649 -0.0510 1.0000 0.0118
-10.750 -0.9445 0.02087 0.01562 -0.0499 1.0000 0.0123
-10.500 -0.9256 0.02011 0.01474 -0.0487 1.0000 0.0129
-10.250 -0.9067 0.01937 0.01389 -0.0474 1.0000 0.0134
-10.000 -0.8874 0.01867 0.01308 -0.0462 1.0000 0.0140
-9.750 -0.8684 0.01796 0.01228 -0.0449 1.0000 0.0147
-9.500 -0.8482 0.01744 0.01172 -0.0437 1.0000 0.0156
-9.250 -0.8275 0.01700 0.01124 -0.0426 1.0000 0.0166
-9.000 -0.8052 0.01653 0.01068 -0.0418 0.9998 0.0176
-8.750 -0.7743 0.01596 0.01003 -0.0428 0.9980 0.0188
-8.500 -0.7428 0.01554 0.00959 -0.0439 0.9961 0.0202
-8.250 -0.7105 0.01517 0.00915 -0.0451 0.9945 0.0217
-8.000 -0.6795 0.01480 0.00871 -0.0460 0.9922 0.0232
-7.750 -0.6485 0.01433 0.00817 -0.0469 0.9897 0.0246
-7.500 -0.6164 0.01395 0.00778 -0.0481 0.9875 0.0262
-7.250 -0.5833 0.01362 0.00739 -0.0494 0.9857 0.0278
-7.000 -0.5512 0.01330 0.00701 -0.0504 0.9832 0.0293
-6.750 -0.5197 0.01299 0.00663 -0.0513 0.9797 0.0304
-6.500 -0.4876 0.01242 0.00603 -0.0525 0.9766 0.0324
-6.250 -0.4541 0.01206 0.00565 -0.0538 0.9736 0.0341
-6.000 -0.4252 0.01175 0.00531 -0.0540 0.9674 0.0357
-5.750 -0.3934 0.01144 0.00495 -0.0549 0.9631 0.0371
-5.500 -0.3640 0.01118 0.00463 -0.0552 0.9575 0.0381
-5.250 -0.3348 0.01077 0.00420 -0.0556 0.9513 0.0405
-5.000 -0.3052 0.01046 0.00388 -0.0559 0.9455 0.0426
-4.750 -0.2770 0.01021 0.00360 -0.0559 0.9378 0.0447
-4.500 -0.2480 0.00999 0.00334 -0.0561 0.9309 0.0471
-4.250 -0.2204 0.00973 0.00308 -0.0560 0.9219 0.0519
-4.000 -0.1925 0.00951 0.00286 -0.0559 0.9130 0.0581
-3.750 -0.1649 0.00928 0.00265 -0.0557 0.9031 0.0694
-3.500 -0.1377 0.00907 0.00246 -0.0555 0.8922 0.0836
-3.250 -0.1104 0.00888 0.00229 -0.0553 0.8810 0.0987
-3.000 -0.0832 0.00869 0.00213 -0.0551 0.8689 0.1161
-2.750 -0.0560 0.00852 0.00199 -0.0548 0.8561 0.1360
-2.500 -0.0290 0.00836 0.00186 -0.0546 0.8422 0.1595
-2.000 0.0251 0.00806 0.00165 -0.0541 0.8125 0.2177
-1.750 0.0520 0.00789 0.00157 -0.0539 0.7967 0.2564
-1.500 0.0789 0.00774 0.00150 -0.0537 0.7803 0.2975
-1.250 0.1057 0.00761 0.00144 -0.0535 0.7632 0.3394
-1.000 0.1323 0.00742 0.00139 -0.0532 0.7457 0.3962
-0.750 0.1587 0.00725 0.00135 -0.0529 0.7279 0.4590
-0.500 0.1850 0.00709 0.00134 -0.0526 0.7099 0.5228
-0.250 0.2109 0.00692 0.00134 -0.0521 0.6917 0.5975
0.000 0.2364 0.00677 0.00136 -0.0516 0.6737 0.6707
0.250 0.2617 0.00664 0.00139 -0.0509 0.6555 0.7347
0.500 0.2866 0.00655 0.00144 -0.0500 0.6371 0.7945
0.750 0.3108 0.00650 0.00150 -0.0489 0.6189 0.8520
1.000 0.3358 0.00652 0.00157 -0.0479 0.6005 0.9035
1.250 0.3664 0.00661 0.00163 -0.0482 0.5815 0.9435
1.500 0.4015 0.00673 0.00168 -0.0497 0.5618 0.9681
1.750 0.4365 0.00687 0.00174 -0.0512 0.5426 0.9845
2.000 0.4724 0.00702 0.00180 -0.0530 0.5233 0.9951
2.250 0.5046 0.00717 0.00187 -0.0540 0.5048 1.0000
2.500 0.5297 0.00733 0.00195 -0.0535 0.4838 1.0000
2.750 0.5539 0.00757 0.00204 -0.0527 0.4512 1.0000
3.000 0.5785 0.00781 0.00214 -0.0521 0.4201 1.0000
3.250 0.6033 0.00804 0.00226 -0.0515 0.3921 1.0000
3.500 0.6280 0.00833 0.00240 -0.0509 0.3593 1.0000
3.750 0.6523 0.00867 0.00257 -0.0503 0.3214 1.0000
4.000 0.6765 0.00904 0.00277 -0.0497 0.2817 1.0000
4.250 0.7004 0.00947 0.00301 -0.0491 0.2396 1.0000
4.500 0.7246 0.00989 0.00326 -0.0486 0.2046 1.0000
4.750 0.7488 0.01031 0.00353 -0.0480 0.1710 1.0000
5.000 0.7729 0.01075 0.00383 -0.0475 0.1397 1.0000
5.250 0.7970 0.01119 0.00414 -0.0469 0.1126 1.0000
5.500 0.8212 0.01164 0.00446 -0.0464 0.0905 1.0000
5.750 0.8455 0.01206 0.00480 -0.0458 0.0718 1.0000
6.000 0.8694 0.01252 0.00517 -0.0452 0.0554 1.0000
6.250 0.8938 0.01291 0.00553 -0.0447 0.0471 1.0000
6.500 0.9184 0.01328 0.00590 -0.0442 0.0426 1.0000
6.750 0.9431 0.01364 0.00628 -0.0437 0.0401 1.0000
7.000 0.9674 0.01403 0.00669 -0.0432 0.0379 1.0000
7.250 0.9909 0.01450 0.00716 -0.0425 0.0356 1.0000
7.500 1.0147 0.01493 0.00764 -0.0419 0.0342 1.0000
7.750 1.0386 0.01532 0.00808 -0.0413 0.0332 1.0000
8.000 1.0622 0.01573 0.00855 -0.0407 0.0319 1.0000
8.250 1.0854 0.01618 0.00903 -0.0400 0.0305 1.0000
8.500 1.1078 0.01668 0.00955 -0.0393 0.0291 1.0000
8.750 1.1286 0.01733 0.01024 -0.0383 0.0276 1.0000
9.000 1.1504 0.01785 0.01083 -0.0375 0.0266 1.0000
9.250 1.1729 0.01829 0.01134 -0.0368 0.0257 1.0000
9.500 1.1947 0.01877 0.01188 -0.0360 0.0246 1.0000
9.750 1.2162 0.01926 0.01241 -0.0352 0.0234 1.0000
10.000 1.2367 0.01981 0.01299 -0.0342 0.0222 1.0000
10.250 1.2543 0.02060 0.01381 -0.0329 0.0209 1.0000
10.500 1.2749 0.02108 0.01439 -0.0320 0.0202 1.0000
10.750 1.2945 0.02161 0.01501 -0.0309 0.0191 1.0000
11.000 1.3136 0.02216 0.01561 -0.0298 0.0179 1.0000
11.250 1.3318 0.02273 0.01621 -0.0286 0.0167 1.0000
11.500 1.3460 0.02346 0.01698 -0.0268 0.0158 1.0000
11.750 1.3598 0.02419 0.01781 -0.0250 0.0150 1.0000
12.000 1.3731 0.02497 0.01868 -0.0232 0.0142 1.0000
12.250 1.3858 0.02581 0.01958 -0.0215 0.0134 1.0000
12.500 1.3975 0.02674 0.02056 -0.0198 0.0127 1.0000
12.750 1.4064 0.02790 0.02179 -0.0180 0.0120 1.0000
13.000 1.4155 0.02909 0.02309 -0.0163 0.0115 1.0000
13.250 1.4237 0.03040 0.02451 -0.0147 0.0110 1.0000
13.500 1.4313 0.03182 0.02603 -0.0133 0.0105 1.0000
13.750 1.4376 0.03340 0.02770 -0.0121 0.0101 1.0000
14.000 1.4425 0.03521 0.02961 -0.0110 0.0097 1.0000
14.250 1.4450 0.03734 0.03185 -0.0101 0.0093 1.0000
14.500 1.4442 0.03994 0.03456 -0.0094 0.0090 1.0000
14.750 1.4453 0.04249 0.03725 -0.0091 0.0089 1.0000
15.000 1.4447 0.04535 0.04025 -0.0091 0.0087 1.0000
15.250 1.4425 0.04856 0.04361 -0.0094 0.0085 1.0000
15.500 1.4385 0.05212 0.04731 -0.0100 0.0083 1.0000
15.750 1.4330 0.05605 0.05138 -0.0110 0.0082 1.0000
16.000 1.4255 0.06040 0.05588 -0.0123 0.0081 1.0000
16.250 1.4162 0.06515 0.06078 -0.0139 0.0079 1.0000
16.500 1.4050 0.07039 0.06617 -0.0160 0.0078 1.0000
16.750 1.3918 0.07612 0.07204 -0.0184 0.0078 1.0000
17.000 1.3766 0.08235 0.07842 -0.0211 0.0077 1.0000
17.250 1.3597 0.08908 0.08530 -0.0242 0.0076 1.0000
17.500 1.3405 0.09639 0.09276 -0.0276 0.0076 1.0000
17.750 1.3197 0.10421 0.10073 -0.0314 0.0076 1.0000
18.000 1.2974 0.11258 0.10924 -0.0356 0.0076 1.0000
18.250 1.2740 0.12134 0.11816 -0.0401 0.0076 1.0000
18.500 1.2497 0.13059 0.12755 -0.0450 0.0076 1.0000
18.750 1.2246 0.14037 0.13747 -0.0503 0.0077 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 2410 (naca2410-il)