NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il) Reynolds number: 200,000 Max Cl/Cd: 74.74 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652415a05-il-200000.txt Download as CSV file: xf-naca652415a05-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2422 0.09909 0.09567 -0.0631 0.8880 0.0658
-11.250 -0.2729 0.09215 0.08876 -0.0700 0.8852 0.0683
-11.000 -0.3033 0.08358 0.08020 -0.0777 0.8814 0.0686
-10.750 -0.2755 0.08199 0.07859 -0.0722 0.8751 0.0703
-10.500 -0.2578 0.08123 0.07777 -0.0694 0.8698 0.0725
-10.250 -0.2546 0.07776 0.07431 -0.0705 0.8644 0.0757
-10.000 -0.2663 0.07204 0.06859 -0.0737 0.8600 0.0780
-9.750 -0.3002 0.06301 0.05955 -0.0808 0.8566 0.0793
-9.500 -0.4164 0.06289 0.05910 -0.0906 0.8653 0.0717
-9.250 -0.4206 0.06072 0.05688 -0.0891 0.8583 0.0731
-9.000 -0.4277 0.05824 0.05427 -0.0877 0.8523 0.0746
-8.750 -0.4342 0.05560 0.05147 -0.0867 0.8453 0.0771
-8.500 -0.4643 0.05757 0.05257 -0.0814 0.8385 0.0817
-8.250 -0.4448 0.04971 0.04509 -0.0836 0.8342 0.0851
-8.000 -0.4309 0.04778 0.04311 -0.0829 0.8289 0.0888
-7.750 -0.4370 0.04565 0.04043 -0.0803 0.8240 0.0975
-7.500 -0.4315 0.03513 0.02871 -0.0762 0.8200 0.0552
-7.250 -0.4150 0.03187 0.02510 -0.0751 0.8151 0.0527
-7.000 -0.3957 0.02978 0.02267 -0.0739 0.8112 0.0529
-6.750 -0.3744 0.02784 0.02040 -0.0728 0.8080 0.0530
-6.500 -0.3509 0.02609 0.01836 -0.0721 0.8047 0.0529
-6.250 -0.3257 0.02472 0.01679 -0.0719 0.8001 0.0535
-6.000 -0.3005 0.02377 0.01564 -0.0714 0.7962 0.0553
-5.750 -0.2750 0.02294 0.01461 -0.0708 0.7930 0.0566
-5.500 -0.2491 0.02183 0.01336 -0.0703 0.7905 0.0576
-5.250 -0.2234 0.02058 0.01217 -0.0704 0.7866 0.0595
-5.000 -0.1988 0.01996 0.01159 -0.0701 0.7828 0.0625
-4.750 -0.1743 0.01943 0.01103 -0.0697 0.7796 0.0658
-4.500 -0.1500 0.01892 0.01043 -0.0690 0.7769 0.0684
-4.250 -0.1290 0.01810 0.00964 -0.0679 0.7746 0.0723
-4.000 -0.1061 0.01779 0.00937 -0.0676 0.7703 0.0785
-3.750 -0.0841 0.01734 0.00895 -0.0669 0.7667 0.0876
-3.500 -0.0618 0.01683 0.00850 -0.0662 0.7637 0.1086
-3.250 -0.0593 0.01449 0.00796 -0.0630 0.7610 0.4883
-3.000 -0.0406 0.01425 0.00819 -0.0607 0.7590 0.6378
-2.750 -0.0176 0.01450 0.00851 -0.0597 0.7554 0.6813
-2.500 0.0060 0.01475 0.00880 -0.0588 0.7516 0.7115
-2.250 0.0307 0.01495 0.00898 -0.0580 0.7487 0.7354
-2.000 0.0536 0.01524 0.00930 -0.0564 0.7464 0.7660
-1.750 0.0739 0.01569 0.00980 -0.0535 0.7444 0.7997
-1.500 0.0966 0.01600 0.01012 -0.0514 0.7427 0.8190
-1.250 0.1175 0.01640 0.01055 -0.0504 0.7383 0.8308
-1.000 0.1413 0.01662 0.01075 -0.0499 0.7349 0.8381
-0.750 0.1664 0.01673 0.01081 -0.0497 0.7324 0.8472
-0.500 0.1925 0.01679 0.01083 -0.0493 0.7302 0.8542
-0.250 0.2190 0.01681 0.01079 -0.0490 0.7284 0.8629
0.000 0.2461 0.01684 0.01077 -0.0487 0.7268 0.8702
0.250 0.2615 0.01749 0.01149 -0.0475 0.7216 0.8814
0.500 0.2838 0.01779 0.01181 -0.0468 0.7182 0.8890
0.750 0.3083 0.01788 0.01187 -0.0463 0.7157 0.8990
1.000 0.3362 0.01790 0.01188 -0.0461 0.7139 0.9072
1.250 0.3640 0.01795 0.01190 -0.0461 0.7122 0.9162
1.500 0.3939 0.01801 0.01194 -0.0465 0.7109 0.9250
1.750 0.4070 0.01911 0.01317 -0.0456 0.7035 0.9377
2.000 0.4390 0.01934 0.01342 -0.0469 0.7009 0.9465
2.250 0.4782 0.01939 0.01346 -0.0493 0.6991 0.9530
2.500 0.5184 0.01936 0.01343 -0.0517 0.6976 0.9594
2.750 0.5632 0.01936 0.01344 -0.0552 0.6963 0.9634
3.000 0.6056 0.01939 0.01348 -0.0582 0.6949 0.9686
3.250 0.6374 0.02074 0.01498 -0.0618 0.6869 0.9768
3.500 0.6790 0.02071 0.01500 -0.0648 0.6844 0.9827
3.750 0.7252 0.02049 0.01481 -0.0684 0.6827 0.9864
4.000 0.7705 0.02020 0.01456 -0.0717 0.6810 0.9907
4.250 0.8085 0.02074 0.01522 -0.0751 0.6757 0.9978
4.500 0.8251 0.02107 0.01561 -0.0741 0.6699 1.0000
4.750 0.8488 0.02057 0.01514 -0.0730 0.6670 1.0000
5.000 0.8792 0.01984 0.01440 -0.0727 0.6645 1.0000
5.250 0.8621 0.02087 0.01551 -0.0661 0.6550 1.0000
5.500 0.8958 0.02006 0.01473 -0.0663 0.6516 1.0000
5.750 0.9245 0.01912 0.01382 -0.0654 0.6440 1.0000
6.000 0.9673 0.01660 0.01120 -0.0655 0.6268 1.0000
6.250 0.9949 0.01562 0.01019 -0.0645 0.6140 1.0000
6.500 1.0206 0.01504 0.00959 -0.0635 0.6025 1.0000
6.750 1.0382 0.01480 0.00943 -0.0615 0.5883 1.0000
7.000 1.0576 0.01454 0.00921 -0.0598 0.5713 1.0000
7.250 1.0712 0.01452 0.00930 -0.0572 0.5477 1.0000
7.500 1.0837 0.01450 0.00923 -0.0544 0.5094 1.0000
7.750 1.0818 0.01498 0.00926 -0.0492 0.4273 1.0000
8.000 1.0600 0.01632 0.01012 -0.0415 0.3586 1.0000
8.250 1.0369 0.01828 0.01166 -0.0350 0.2948 1.0000
8.500 1.0142 0.02077 0.01370 -0.0296 0.2274 1.0000
8.750 0.9941 0.02352 0.01599 -0.0252 0.1570 1.0000
9.000 0.9777 0.02634 0.01834 -0.0215 0.0998 1.0000
9.250 0.9715 0.02866 0.02044 -0.0189 0.0752 1.0000
9.500 0.9727 0.03054 0.02227 -0.0170 0.0647 1.0000
9.750 0.9745 0.03242 0.02415 -0.0152 0.0587 1.0000
10.000 0.9811 0.03400 0.02576 -0.0138 0.0539 1.0000
10.250 0.9824 0.03601 0.02772 -0.0121 0.0507 1.0000
10.500 0.9920 0.03742 0.02920 -0.0109 0.0483 1.0000
10.750 1.0027 0.03878 0.03060 -0.0098 0.0461 1.0000
11.000 1.0136 0.04016 0.03197 -0.0087 0.0438 1.0000
11.250 1.0292 0.04137 0.03308 -0.0074 0.0417 1.0000
11.500 1.0453 0.04246 0.03428 -0.0066 0.0402 1.0000
11.750 1.0655 0.04340 0.03529 -0.0059 0.0390 1.0000
12.000 1.0875 0.04439 0.03633 -0.0052 0.0377 1.0000
12.250 1.1118 0.04540 0.03740 -0.0046 0.0367 1.0000
12.500 1.1387 0.04652 0.03855 -0.0043 0.0356 1.0000
12.750 1.1908 0.04831 0.04036 -0.0054 0.0342 1.0000
13.000 1.1957 0.05011 0.04242 -0.0041 0.0337 1.0000
13.250 1.2088 0.05229 0.04485 -0.0033 0.0333 1.0000
13.500 1.2193 0.05477 0.04759 -0.0024 0.0330 1.0000
13.750 1.2264 0.05766 0.05074 -0.0015 0.0329 1.0000
14.000 1.2290 0.06085 0.05421 -0.0005 0.0330 1.0000
14.250 1.2279 0.06438 0.05800 0.0005 0.0331 1.0000
14.500 1.2238 0.06820 0.06207 0.0013 0.0333 1.0000
14.750 1.2157 0.07244 0.06655 0.0020 0.0335 1.0000
15.000 1.2075 0.07704 0.07137 0.0024 0.0338 1.0000
15.250 1.2126 0.08230 0.07680 0.0023 0.0344 1.0000
15.500 1.1958 0.08556 0.08027 0.0026 0.0346 1.0000
15.750 1.0199 0.08817 0.08363 0.0053 0.0349 1.0000
16.000 0.9385 0.09805 0.09410 0.0007 0.0361 1.0000
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Polar data table (+)
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