NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(2)-415 (naca642415-il) Reynolds number: 500,000 Max Cl/Cd: 90.82 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca642415-il-500000-n5.txt Download as CSV file: xf-naca642415-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(2)-415
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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8628 0.08659 0.08330 -0.0551 1.0000 0.0140
-16.750 -0.8835 0.07866 0.07523 -0.0600 1.0000 0.0141
-16.500 -0.9048 0.07122 0.06761 -0.0645 1.0000 0.0141
-16.250 -0.9159 0.06586 0.06213 -0.0676 1.0000 0.0142
-16.000 -0.9282 0.06071 0.05683 -0.0704 1.0000 0.0143
-15.750 -0.9323 0.05692 0.05293 -0.0724 1.0000 0.0144
-15.500 -0.9371 0.05328 0.04918 -0.0741 1.0000 0.0146
-15.250 -0.9414 0.04991 0.04569 -0.0754 1.0000 0.0147
-15.000 -0.9432 0.04695 0.04262 -0.0765 1.0000 0.0150
-14.750 -0.9445 0.04416 0.03971 -0.0772 1.0000 0.0151
-14.500 -0.9448 0.04158 0.03700 -0.0777 1.0000 0.0153
-14.250 -0.9437 0.03923 0.03452 -0.0780 1.0000 0.0155
-14.000 -0.9413 0.03709 0.03225 -0.0780 1.0000 0.0158
-13.750 -0.9376 0.03515 0.03019 -0.0779 1.0000 0.0159
-13.500 -0.9329 0.03337 0.02828 -0.0775 1.0000 0.0161
-13.250 -0.9274 0.03173 0.02652 -0.0769 1.0000 0.0163
-13.000 -0.9223 0.03018 0.02491 -0.0761 1.0000 0.0165
-12.750 -0.9162 0.02882 0.02351 -0.0752 1.0000 0.0167
-12.500 -0.9096 0.02761 0.02225 -0.0741 1.0000 0.0169
-12.250 -0.9026 0.02658 0.02118 -0.0727 1.0000 0.0172
-12.000 -0.8949 0.02566 0.02022 -0.0713 0.9992 0.0174
-11.750 -0.8674 0.02448 0.01896 -0.0735 0.9831 0.0178
-11.500 -0.8357 0.02348 0.01787 -0.0764 0.9689 0.0184
-11.250 -0.8030 0.02236 0.01664 -0.0793 0.9550 0.0189
-11.000 -0.7722 0.02135 0.01548 -0.0817 0.9395 0.0194
-10.750 -0.7490 0.02052 0.01451 -0.0823 0.9213 0.0197
-10.500 -0.7349 0.01972 0.01362 -0.0812 0.9033 0.0201
-10.250 -0.7181 0.01911 0.01292 -0.0802 0.8891 0.0205
-10.000 -0.6996 0.01863 0.01236 -0.0792 0.8769 0.0211
-9.750 -0.6808 0.01813 0.01178 -0.0783 0.8654 0.0215
-9.500 -0.6614 0.01762 0.01119 -0.0774 0.8552 0.0221
-9.000 -0.6207 0.01665 0.01002 -0.0758 0.8359 0.0232
-8.750 -0.5992 0.01621 0.00948 -0.0752 0.8272 0.0236
-8.500 -0.5786 0.01563 0.00886 -0.0745 0.8181 0.0243
-8.250 -0.5562 0.01521 0.00838 -0.0740 0.8101 0.0251
-8.000 -0.5327 0.01484 0.00795 -0.0736 0.8015 0.0259
-7.750 -0.5091 0.01449 0.00752 -0.0732 0.7938 0.0269
-7.500 -0.4846 0.01413 0.00711 -0.0729 0.7859 0.0278
-7.250 -0.4604 0.01377 0.00666 -0.0726 0.7784 0.0287
-7.000 -0.4360 0.01336 0.00623 -0.0723 0.7713 0.0299
-6.750 -0.4108 0.01304 0.00587 -0.0722 0.7639 0.0312
-6.500 -0.3850 0.01276 0.00552 -0.0720 0.7569 0.0327
-6.250 -0.3589 0.01249 0.00520 -0.0720 0.7495 0.0342
-6.000 -0.3331 0.01219 0.00487 -0.0719 0.7429 0.0366
-5.750 -0.3064 0.01194 0.00458 -0.0719 0.7363 0.0390
-5.500 -0.2798 0.01169 0.00430 -0.0719 0.7297 0.0419
-5.250 -0.2529 0.01145 0.00404 -0.0719 0.7237 0.0462
-5.000 -0.2259 0.01120 0.00379 -0.0720 0.7171 0.0527
-4.750 -0.1989 0.01097 0.00356 -0.0721 0.7109 0.0622
-4.500 -0.1716 0.01071 0.00334 -0.0723 0.7047 0.0771
-4.250 -0.1446 0.01040 0.00311 -0.0724 0.6980 0.1030
-4.000 -0.1177 0.01003 0.00287 -0.0726 0.6920 0.1426
-3.750 -0.0907 0.00955 0.00261 -0.0730 0.6857 0.2046
-3.500 -0.0643 0.00891 0.00230 -0.0734 0.6798 0.3013
-3.250 -0.0373 0.00830 0.00209 -0.0739 0.6745 0.4123
-3.000 -0.0088 0.00813 0.00204 -0.0742 0.6687 0.4620
-2.750 0.0198 0.00807 0.00199 -0.0744 0.6631 0.4857
-2.500 0.0485 0.00802 0.00197 -0.0747 0.6580 0.5104
-2.250 0.0773 0.00798 0.00197 -0.0749 0.6525 0.5353
-2.000 0.1060 0.00799 0.00199 -0.0751 0.6472 0.5575
-1.750 0.1347 0.00799 0.00199 -0.0753 0.6422 0.5682
-1.500 0.1638 0.00800 0.00196 -0.0756 0.6367 0.5738
-1.250 0.1925 0.00800 0.00195 -0.0757 0.6312 0.5791
-1.000 0.2213 0.00803 0.00193 -0.0760 0.6264 0.5841
-0.750 0.2504 0.00804 0.00192 -0.0762 0.6215 0.5883
-0.500 0.2793 0.00805 0.00192 -0.0765 0.6166 0.5921
-0.250 0.3080 0.00808 0.00193 -0.0767 0.6122 0.5960
0.000 0.3370 0.00810 0.00195 -0.0769 0.6079 0.6006
0.250 0.3660 0.00813 0.00197 -0.0772 0.6034 0.6055
0.500 0.3947 0.00816 0.00200 -0.0774 0.5991 0.6100
0.750 0.4233 0.00820 0.00204 -0.0776 0.5952 0.6146
1.000 0.4522 0.00823 0.00209 -0.0779 0.5910 0.6196
1.500 0.5096 0.00831 0.00220 -0.0783 0.5825 0.6291
1.750 0.5382 0.00838 0.00227 -0.0785 0.5790 0.6345
2.000 0.5670 0.00842 0.00234 -0.0788 0.5751 0.6399
2.250 0.5955 0.00847 0.00243 -0.0790 0.5700 0.6451
2.500 0.6237 0.00854 0.00251 -0.0791 0.5645 0.6511
2.750 0.6522 0.00861 0.00260 -0.0793 0.5600 0.6574
3.000 0.6806 0.00865 0.00271 -0.0794 0.5554 0.6633
3.250 0.7085 0.00873 0.00281 -0.0795 0.5486 0.6696
3.750 0.7632 0.00890 0.00301 -0.0794 0.5263 0.6818
4.000 0.7900 0.00902 0.00312 -0.0793 0.5116 0.6885
4.250 0.8165 0.00915 0.00324 -0.0791 0.4952 0.6948
4.500 0.8422 0.00932 0.00338 -0.0788 0.4722 0.7014
4.750 0.8673 0.00955 0.00356 -0.0784 0.4471 0.7084
5.000 0.8910 0.00986 0.00377 -0.0778 0.4082 0.7151
5.250 0.9089 0.01060 0.00419 -0.0764 0.3425 0.7228
5.500 0.9260 0.01142 0.00473 -0.0749 0.2800 0.7302
5.750 0.9426 0.01225 0.00531 -0.0734 0.2220 0.7381
6.000 0.9597 0.01301 0.00586 -0.0719 0.1750 0.7457
6.250 0.9770 0.01370 0.00638 -0.0705 0.1374 0.7535
6.750 1.0111 0.01497 0.00743 -0.0675 0.0834 0.7695
7.250 1.0443 0.01610 0.00846 -0.0643 0.0531 0.7876
7.500 1.0592 0.01659 0.00895 -0.0623 0.0451 0.7974
7.750 1.0731 0.01707 0.00946 -0.0602 0.0395 0.8077
8.000 1.0875 0.01756 0.01000 -0.0582 0.0358 0.8185
8.250 1.1009 0.01812 0.01059 -0.0562 0.0327 0.8302
8.500 1.1147 0.01866 0.01121 -0.0543 0.0306 0.8432
8.750 1.1274 0.01924 0.01186 -0.0523 0.0287 0.8573
9.000 1.1383 0.01991 0.01260 -0.0501 0.0270 0.8740
9.250 1.1487 0.02052 0.01332 -0.0478 0.0257 0.8956
9.500 1.1573 0.02113 0.01404 -0.0452 0.0245 0.9319
9.750 1.1713 0.02193 0.01490 -0.0441 0.0231 1.0000
10.000 1.1833 0.02294 0.01593 -0.0429 0.0221 1.0000
10.250 1.1973 0.02384 0.01688 -0.0418 0.0211 1.0000
10.500 1.2101 0.02484 0.01793 -0.0408 0.0201 1.0000
10.750 1.2221 0.02593 0.01906 -0.0397 0.0194 1.0000
11.000 1.2327 0.02717 0.02032 -0.0386 0.0185 1.0000
11.250 1.2432 0.02843 0.02163 -0.0376 0.0179 1.0000
11.500 1.2547 0.02966 0.02291 -0.0367 0.0172 1.0000
11.750 1.2657 0.03094 0.02425 -0.0359 0.0165 1.0000
12.000 1.2756 0.03235 0.02572 -0.0351 0.0160 1.0000
12.250 1.2850 0.03384 0.02725 -0.0343 0.0155 1.0000
12.500 1.2930 0.03547 0.02893 -0.0335 0.0152 1.0000
12.750 1.2992 0.03732 0.03082 -0.0328 0.0148 1.0000
13.000 1.3074 0.03903 0.03261 -0.0322 0.0146 1.0000
13.250 1.3146 0.04086 0.03452 -0.0317 0.0143 1.0000
13.500 1.3215 0.04277 0.03651 -0.0312 0.0141 1.0000
13.750 1.3285 0.04473 0.03855 -0.0308 0.0137 1.0000
14.000 1.3344 0.04684 0.04074 -0.0305 0.0135 1.0000
14.250 1.3401 0.04902 0.04299 -0.0303 0.0133 1.0000
14.500 1.3457 0.05127 0.04531 -0.0302 0.0131 1.0000
14.750 1.3505 0.05368 0.04780 -0.0302 0.0129 1.0000
15.000 1.3550 0.05618 0.05037 -0.0303 0.0127 1.0000
15.250 1.3587 0.05882 0.05310 -0.0305 0.0126 1.0000
15.500 1.3616 0.06161 0.05597 -0.0307 0.0124 1.0000
15.750 1.3634 0.06464 0.05907 -0.0312 0.0123 1.0000
16.000 1.3638 0.06789 0.06240 -0.0317 0.0121 1.0000
16.250 1.3631 0.07135 0.06594 -0.0324 0.0120 1.0000
16.500 1.3644 0.07465 0.06934 -0.0331 0.0119 1.0000
16.750 1.3656 0.07802 0.07283 -0.0340 0.0118 1.0000
17.000 1.3655 0.08166 0.07659 -0.0350 0.0118 1.0000
17.250 1.3652 0.08538 0.08042 -0.0361 0.0116 1.0000
17.500 1.3644 0.08926 0.08443 -0.0374 0.0115 1.0000
17.750 1.3626 0.09338 0.08866 -0.0389 0.0114 1.0000
18.000 1.3602 0.09767 0.09308 -0.0406 0.0113 1.0000
18.250 1.3576 0.10209 0.09761 -0.0424 0.0112 1.0000
18.500 1.3538 0.10676 0.10241 -0.0445 0.0111 1.0000
18.750 1.3499 0.11156 0.10733 -0.0467 0.0110 1.0000
19.000 1.3449 0.11662 0.11252 -0.0492 0.0109 1.0000
19.250 1.3395 0.12187 0.11789 -0.0520 0.0108 1.0000
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