NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il) Reynolds number: 500,000 Max Cl/Cd: 113.08 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652415a05-il-500000.txt Download as CSV file: xf-naca652415a05-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415 a=0.5
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5943 0.04663 0.04299 -0.0826 0.8161 0.0216
-10.500 -0.6151 0.04372 0.03987 -0.0789 0.8091 0.0215
-10.250 -0.6334 0.04021 0.03599 -0.0754 0.8030 0.0216
-10.000 -0.6406 0.03726 0.03266 -0.0725 0.7971 0.0217
-9.750 -0.6485 0.03274 0.02767 -0.0696 0.7922 0.0220
-9.500 -0.6318 0.03147 0.02639 -0.0692 0.7876 0.0227
-9.250 -0.5990 0.03331 0.02854 -0.0702 0.7827 0.0237
-9.000 -0.5934 0.02993 0.02473 -0.0680 0.7781 0.0238
-8.750 -0.5808 0.02745 0.02189 -0.0664 0.7740 0.0241
-8.500 -0.5637 0.02546 0.01962 -0.0653 0.7695 0.0247
-8.250 -0.5442 0.02378 0.01765 -0.0644 0.7651 0.0254
-8.000 -0.5225 0.02272 0.01632 -0.0636 0.7613 0.0261
-7.750 -0.5012 0.02100 0.01434 -0.0630 0.7578 0.0271
-7.500 -0.4769 0.01996 0.01327 -0.0628 0.7539 0.0279
-7.250 -0.4521 0.01919 0.01244 -0.0626 0.7500 0.0287
-7.000 -0.4270 0.01843 0.01160 -0.0624 0.7465 0.0295
-6.750 -0.4018 0.01772 0.01075 -0.0621 0.7433 0.0304
-6.500 -0.3760 0.01725 0.01019 -0.0619 0.7398 0.0316
-6.250 -0.3501 0.01674 0.00959 -0.0617 0.7361 0.0323
-6.000 -0.3266 0.01543 0.00826 -0.0612 0.7326 0.0334
-5.750 -0.3020 0.01485 0.00766 -0.0609 0.7295 0.0345
-5.500 -0.2770 0.01443 0.00718 -0.0606 0.7266 0.0357
-5.250 -0.2513 0.01403 0.00677 -0.0604 0.7236 0.0372
-5.000 -0.2254 0.01368 0.00638 -0.0602 0.7204 0.0385
-4.750 -0.2011 0.01315 0.00580 -0.0598 0.7174 0.0397
-4.500 -0.1772 0.01258 0.00521 -0.0593 0.7146 0.0417
-4.250 -0.1514 0.01229 0.00487 -0.0591 0.7120 0.0438
-4.000 -0.1249 0.01206 0.00462 -0.0590 0.7092 0.0464
-3.750 -0.0992 0.01168 0.00423 -0.0588 0.7063 0.0499
-3.500 -0.0726 0.01141 0.00396 -0.0588 0.7035 0.0547
-3.250 -0.0461 0.01113 0.00368 -0.0587 0.7010 0.0641
-3.000 -0.0229 0.01041 0.00335 -0.0583 0.6986 0.1556
-2.750 -0.0072 0.00889 0.00295 -0.0572 0.6963 0.4516
-2.500 0.0166 0.00850 0.00294 -0.0567 0.6939 0.5691
-2.250 0.0434 0.00837 0.00295 -0.0566 0.6913 0.6153
-2.000 0.0708 0.00832 0.00296 -0.0565 0.6887 0.6461
-1.750 0.0989 0.00831 0.00295 -0.0566 0.6863 0.6677
-1.500 0.1265 0.00829 0.00298 -0.0566 0.6842 0.6908
-1.250 0.1534 0.00833 0.00307 -0.0563 0.6821 0.7224
-1.000 0.1805 0.00843 0.00318 -0.0560 0.6800 0.7470
-0.750 0.2082 0.00847 0.00326 -0.0560 0.6778 0.7603
-0.500 0.2367 0.00848 0.00328 -0.0562 0.6755 0.7689
-0.250 0.2651 0.00850 0.00331 -0.0564 0.6732 0.7760
0.000 0.2938 0.00853 0.00332 -0.0567 0.6710 0.7839
0.250 0.3222 0.00853 0.00335 -0.0569 0.6689 0.7907
0.500 0.3510 0.00858 0.00336 -0.0572 0.6668 0.7990
0.750 0.3793 0.00863 0.00342 -0.0574 0.6649 0.8060
1.000 0.4077 0.00872 0.00351 -0.0576 0.6630 0.8141
1.250 0.4356 0.00874 0.00359 -0.0578 0.6609 0.8214
1.500 0.4636 0.00879 0.00367 -0.0580 0.6585 0.8298
1.750 0.4916 0.00883 0.00376 -0.0581 0.6563 0.8374
2.000 0.5197 0.00888 0.00383 -0.0582 0.6542 0.8457
2.250 0.5477 0.00892 0.00390 -0.0584 0.6521 0.8533
2.500 0.5758 0.00899 0.00398 -0.0585 0.6502 0.8619
2.750 0.6035 0.00912 0.00412 -0.0586 0.6481 0.8698
3.000 0.6303 0.00917 0.00426 -0.0585 0.6458 0.8787
3.250 0.6569 0.00922 0.00440 -0.0584 0.6432 0.8868
3.500 0.6838 0.00926 0.00449 -0.0583 0.6402 0.8963
3.750 0.7104 0.00927 0.00453 -0.0581 0.6371 0.9045
4.000 0.7378 0.00931 0.00456 -0.0580 0.6339 0.9138
4.250 0.7624 0.00931 0.00466 -0.0574 0.6294 0.9231
4.500 0.7877 0.00925 0.00466 -0.0568 0.6241 0.9329
4.750 0.8139 0.00921 0.00463 -0.0565 0.6197 0.9435
5.000 0.8398 0.00910 0.00459 -0.0560 0.6114 0.9536
5.250 0.8683 0.00884 0.00433 -0.0561 0.5959 0.9634
5.500 0.8997 0.00877 0.00428 -0.0570 0.5827 0.9725
5.750 0.9358 0.00878 0.00431 -0.0589 0.5710 0.9787
6.000 0.9716 0.00883 0.00439 -0.0609 0.5555 0.9853
6.250 1.0087 0.00892 0.00453 -0.0633 0.5331 0.9907
6.500 1.0420 0.00930 0.00473 -0.0652 0.4821 0.9992
6.750 1.0367 0.01009 0.00516 -0.0597 0.4136 1.0000
7.000 1.0286 0.01137 0.00600 -0.0541 0.3360 1.0000
7.250 1.0187 0.01260 0.00688 -0.0482 0.2734 1.0000
7.500 1.0067 0.01393 0.00791 -0.0425 0.2199 1.0000
7.750 0.9982 0.01546 0.00916 -0.0379 0.1671 1.0000
8.000 0.9922 0.01711 0.01052 -0.0341 0.1172 1.0000
8.250 0.9881 0.01882 0.01197 -0.0308 0.0754 1.0000
8.500 0.9883 0.02040 0.01338 -0.0281 0.0498 1.0000
8.750 0.9953 0.02164 0.01457 -0.0263 0.0409 1.0000
9.000 1.0051 0.02275 0.01568 -0.0247 0.0364 1.0000
9.250 1.0134 0.02399 0.01694 -0.0231 0.0330 1.0000
9.500 1.0248 0.02504 0.01803 -0.0219 0.0309 1.0000
9.750 1.0326 0.02637 0.01937 -0.0205 0.0290 1.0000
10.000 1.0389 0.02784 0.02088 -0.0189 0.0276 1.0000
10.250 1.0498 0.02901 0.02211 -0.0178 0.0266 1.0000
10.500 1.0600 0.03024 0.02338 -0.0167 0.0255 1.0000
10.750 1.0684 0.03162 0.02481 -0.0155 0.0248 1.0000
11.000 1.0758 0.03313 0.02633 -0.0144 0.0238 1.0000
11.250 1.0817 0.03478 0.02802 -0.0131 0.0234 1.0000
11.500 1.0870 0.03651 0.02981 -0.0118 0.0225 1.0000
11.750 1.0975 0.03787 0.03122 -0.0109 0.0223 1.0000
12.000 1.1083 0.03923 0.03265 -0.0102 0.0216 1.0000
12.250 1.1189 0.04062 0.03409 -0.0094 0.0211 1.0000
12.500 1.1294 0.04203 0.03556 -0.0087 0.0204 1.0000
12.750 1.1399 0.04347 0.03704 -0.0079 0.0202 1.0000
13.000 1.1503 0.04495 0.03855 -0.0073 0.0196 1.0000
13.250 1.1607 0.04642 0.04005 -0.0065 0.0192 1.0000
13.500 1.1723 0.04782 0.04147 -0.0057 0.0189 1.0000
13.750 1.1890 0.04896 0.04266 -0.0045 0.0184 1.0000
14.000 1.2001 0.05051 0.04431 -0.0040 0.0182 1.0000
14.250 1.2120 0.05204 0.04595 -0.0035 0.0180 1.0000
14.500 1.2232 0.05369 0.04773 -0.0030 0.0178 1.0000
14.750 1.2325 0.05553 0.04969 -0.0025 0.0175 1.0000
15.000 1.2408 0.05750 0.05178 -0.0021 0.0172 1.0000
15.250 1.2485 0.05960 0.05400 -0.0018 0.0169 1.0000
15.500 1.2546 0.06183 0.05636 -0.0015 0.0166 1.0000
15.750 1.2597 0.06426 0.05891 -0.0013 0.0164 1.0000
16.000 1.2636 0.06693 0.06172 -0.0012 0.0163 1.0000
16.250 1.2651 0.06991 0.06485 -0.0011 0.0162 1.0000
16.500 1.2669 0.07277 0.06784 -0.0013 0.0159 1.0000
16.750 1.2656 0.07612 0.07133 -0.0016 0.0158 1.0000
17.000 1.2627 0.07972 0.07507 -0.0021 0.0157 1.0000
17.250 1.2578 0.08369 0.07919 -0.0029 0.0156 1.0000
17.500 1.2493 0.08831 0.08399 -0.0039 0.0156 1.0000
17.750 1.2436 0.09250 0.08830 -0.0051 0.0154 1.0000
18.000 1.2233 0.09935 0.09543 -0.0073 0.0156 1.0000
18.250 1.2042 0.10619 0.10251 -0.0099 0.0156 1.0000
18.500 1.1840 0.11352 0.11006 -0.0133 0.0156 1.0000
18.750 1.1127 0.13192 0.12902 -0.0231 0.0162 1.0000
19.000 1.0468 0.15218 0.14965 -0.0355 0.0169 1.0000
19.250 0.9645 0.18256 0.18029 -0.0533 0.0190 1.0000
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Polar data table (+)
Polar graphs
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