NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-415 (naca652415-il) Reynolds number: 200,000 Max Cl/Cd: 70.81 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652415-il-200000.txt Download as CSV file: xf-naca652415-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4881 0.08509 0.08159 -0.0726 1.0000 0.0726
-10.750 -0.5231 0.08247 0.07904 -0.0705 1.0000 0.0726
-10.500 -0.5499 0.08157 0.07822 -0.0653 1.0000 0.0724
-10.250 -0.5821 0.07572 0.07212 -0.0739 0.9887 0.0727
-10.000 -0.5975 0.07221 0.06819 -0.0789 0.9759 0.0732
-9.750 -0.5610 0.06378 0.06015 -0.0808 0.9784 0.0761
-9.500 -0.5425 0.06022 0.05652 -0.0840 0.9731 0.0788
-9.250 -0.5387 0.05628 0.05231 -0.0872 0.9640 0.0828
-9.000 -0.4536 0.03772 0.03384 -0.0950 0.9499 0.0936
-8.500 -0.5226 0.03638 0.02985 -0.0891 0.9413 0.0508
-8.250 -0.5038 0.03275 0.02605 -0.0886 0.9335 0.0495
-8.000 -0.4770 0.03009 0.02307 -0.0893 0.9286 0.0494
-7.750 -0.4506 0.02868 0.02132 -0.0895 0.9233 0.0502
-7.500 -0.4285 0.02703 0.01940 -0.0887 0.9157 0.0508
-7.250 -0.3979 0.02468 0.01688 -0.0894 0.9117 0.0514
-7.000 -0.3708 0.02310 0.01525 -0.0895 0.9063 0.0524
-6.750 -0.3460 0.02207 0.01420 -0.0891 0.8997 0.0540
-6.500 -0.3181 0.02121 0.01329 -0.0892 0.8951 0.0564
-6.250 -0.2953 0.02050 0.01252 -0.0883 0.8881 0.0584
-6.000 -0.2708 0.01977 0.01172 -0.0877 0.8821 0.0600
-5.750 -0.2460 0.01887 0.01078 -0.0872 0.8779 0.0621
-5.500 -0.2294 0.01818 0.01016 -0.0856 0.8702 0.0656
-5.250 -0.2071 0.01764 0.00959 -0.0848 0.8647 0.0702
-5.000 -0.1863 0.01700 0.00891 -0.0839 0.8596 0.0753
-4.750 -0.1675 0.01648 0.00840 -0.0827 0.8525 0.0836
-4.500 -0.1465 0.01568 0.00770 -0.0819 0.8478 0.1078
-4.250 -0.1455 0.01308 0.00699 -0.0794 0.8413 0.4793
-4.000 -0.1232 0.01317 0.00736 -0.0780 0.8357 0.5981
-3.750 -0.0960 0.01338 0.00751 -0.0773 0.8318 0.6335
-3.500 -0.0697 0.01367 0.00777 -0.0765 0.8276 0.6546
-3.250 -0.0457 0.01399 0.00808 -0.0755 0.8218 0.6713
-3.000 -0.0205 0.01446 0.00854 -0.0742 0.8177 0.6938
-2.750 0.0026 0.01531 0.00947 -0.0712 0.8146 0.7189
-2.500 0.0239 0.01587 0.01005 -0.0690 0.8093 0.7338
-2.250 0.0488 0.01601 0.01015 -0.0683 0.8043 0.7409
-2.000 0.0772 0.01590 0.00993 -0.0687 0.8008 0.7475
-1.750 0.1054 0.01590 0.00987 -0.0685 0.7980 0.7512
-1.500 0.1289 0.01600 0.00995 -0.0681 0.7926 0.7558
-1.250 0.1567 0.01592 0.00978 -0.0687 0.7880 0.7617
-1.000 0.1847 0.01585 0.00966 -0.0687 0.7846 0.7650
-0.750 0.2135 0.01582 0.00959 -0.0688 0.7820 0.7685
-0.500 0.2369 0.01597 0.00974 -0.0685 0.7769 0.7732
-0.250 0.2649 0.01594 0.00966 -0.0692 0.7725 0.7786
0.000 0.2921 0.01591 0.00963 -0.0690 0.7692 0.7817
0.250 0.3210 0.01590 0.00959 -0.0692 0.7666 0.7854
0.500 0.3451 0.01607 0.00978 -0.0691 0.7620 0.7901
0.750 0.3717 0.01614 0.00985 -0.0694 0.7574 0.7954
1.000 0.3982 0.01616 0.00989 -0.0691 0.7540 0.7988
1.250 0.4271 0.01616 0.00988 -0.0694 0.7514 0.8030
1.500 0.4533 0.01632 0.01006 -0.0696 0.7476 0.8081
1.750 0.4765 0.01650 0.01030 -0.0692 0.7424 0.8129
2.000 0.5023 0.01658 0.01042 -0.0689 0.7389 0.8171
2.250 0.5318 0.01658 0.01044 -0.0693 0.7362 0.8222
2.500 0.5606 0.01667 0.01055 -0.0699 0.7329 0.8275
2.750 0.5789 0.01699 0.01098 -0.0685 0.7271 0.8320
3.000 0.6057 0.01704 0.01108 -0.0684 0.7231 0.8376
3.250 0.6375 0.01695 0.01101 -0.0692 0.7201 0.8434
3.500 0.6579 0.01714 0.01131 -0.0679 0.7145 0.8483
3.750 0.6824 0.01722 0.01146 -0.0675 0.7089 0.8544
4.000 0.7133 0.01706 0.01134 -0.0679 0.7050 0.8601
4.250 0.7359 0.01710 0.01148 -0.0668 0.6993 0.8660
4.500 0.7626 0.01697 0.01141 -0.0665 0.6919 0.8734
4.750 0.7926 0.01650 0.01098 -0.0662 0.6853 0.8785
5.000 0.8233 0.01563 0.01008 -0.0655 0.6715 0.8848
5.250 0.8450 0.01493 0.00939 -0.0635 0.6527 0.8923
5.500 0.8665 0.01448 0.00899 -0.0616 0.6371 0.9005
5.750 0.8886 0.01418 0.00873 -0.0601 0.6239 0.9088
6.000 0.9079 0.01396 0.00858 -0.0582 0.6082 0.9189
6.250 0.9220 0.01375 0.00847 -0.0553 0.5895 0.9298
6.500 0.9364 0.01353 0.00830 -0.0524 0.5648 0.9429
6.750 0.9496 0.01341 0.00818 -0.0495 0.5264 0.9592
7.000 0.9596 0.01400 0.00823 -0.0468 0.4117 0.9807
7.250 0.9453 0.01572 0.00920 -0.0415 0.2948 1.0000
7.500 0.9290 0.01808 0.01083 -0.0368 0.1821 1.0000
7.750 0.9173 0.02059 0.01268 -0.0331 0.0983 1.0000
8.000 0.9200 0.02235 0.01426 -0.0310 0.0746 1.0000
8.250 0.9281 0.02379 0.01567 -0.0294 0.0651 1.0000
8.500 0.9328 0.02548 0.01730 -0.0276 0.0598 1.0000
8.750 0.9451 0.02670 0.01858 -0.0264 0.0555 1.0000
9.000 0.9555 0.02806 0.01993 -0.0252 0.0521 1.0000
9.250 0.9639 0.02971 0.02153 -0.0237 0.0492 1.0000
9.500 0.9793 0.03085 0.02276 -0.0228 0.0469 1.0000
9.750 0.9955 0.03203 0.02396 -0.0219 0.0451 1.0000
10.000 1.0135 0.03321 0.02512 -0.0211 0.0434 1.0000
10.250 1.0415 0.03452 0.02633 -0.0210 0.0415 1.0000
10.500 1.0685 0.03575 0.02767 -0.0208 0.0400 1.0000
10.750 1.0927 0.03695 0.02900 -0.0206 0.0387 1.0000
11.000 1.1194 0.03834 0.03051 -0.0206 0.0375 1.0000
11.250 1.1482 0.03998 0.03227 -0.0208 0.0366 1.0000
11.500 1.1764 0.04186 0.03430 -0.0211 0.0359 1.0000
11.750 1.2026 0.04412 0.03674 -0.0212 0.0355 1.0000
12.000 1.2233 0.04663 0.03948 -0.0209 0.0353 1.0000
12.250 1.2393 0.04920 0.04221 -0.0204 0.0348 1.0000
12.500 1.2537 0.05231 0.04552 -0.0200 0.0343 1.0000
12.750 1.2610 0.05590 0.04935 -0.0189 0.0340 1.0000
13.000 1.2573 0.05866 0.05238 -0.0168 0.0342 1.0000
13.250 1.2409 0.06165 0.05576 -0.0139 0.0348 1.0000
13.500 1.1861 0.06866 0.06353 -0.0101 0.0369 1.0000
13.750 1.1632 0.07416 0.06934 -0.0091 0.0380 1.0000
14.000 1.1431 0.07958 0.07500 -0.0089 0.0390 1.0000
14.250 1.1248 0.08516 0.08076 -0.0093 0.0397 1.0000
14.500 0.9564 0.08962 0.08587 -0.0069 0.0388 1.0000
14.750 0.9181 0.09562 0.09210 -0.0093 0.0394 1.0000
15.000 0.8845 0.10238 0.09904 -0.0128 0.0399 1.0000
15.250 0.8898 0.10594 0.10262 -0.0134 0.0414 1.0000
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