NACA 64(3)-418 (naca643418-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64(3)-418 (naca643418-il) Reynolds number: 500,000 Max Cl/Cd: 93.49 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca643418-il-500000-n5.txt Download as CSV file: xf-naca643418-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(3)-418
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
------ -------- --------- --------- -------- -------- --------
-19.750 -0.9013 0.10980 0.10610 -0.0499 1.0000 0.0183
-19.500 -0.9157 0.10343 0.09960 -0.0535 1.0000 0.0184
-19.250 -0.9278 0.09756 0.09360 -0.0567 1.0000 0.0185
-19.000 -0.9385 0.09205 0.08797 -0.0597 1.0000 0.0187
-18.750 -0.9477 0.08701 0.08281 -0.0622 1.0000 0.0188
-18.500 -0.9537 0.08252 0.07821 -0.0645 1.0000 0.0189
-18.250 -0.9597 0.07814 0.07371 -0.0666 1.0000 0.0191
-18.000 -0.9641 0.07414 0.06959 -0.0685 1.0000 0.0192
-17.750 -0.9666 0.07047 0.06581 -0.0701 1.0000 0.0195
-17.500 -0.9685 0.06703 0.06226 -0.0715 1.0000 0.0196
-17.250 -0.9685 0.06386 0.05897 -0.0728 1.0000 0.0197
-17.000 -0.9687 0.06086 0.05590 -0.0738 1.0000 0.0199
-16.750 -0.9677 0.05807 0.05305 -0.0746 1.0000 0.0201
-16.500 -0.9662 0.05537 0.05031 -0.0755 1.0000 0.0203
-16.250 -0.9626 0.05296 0.04784 -0.0762 1.0000 0.0205
-16.000 -0.9587 0.05065 0.04547 -0.0767 1.0000 0.0207
-15.750 -0.9541 0.04845 0.04322 -0.0772 1.0000 0.0210
-15.500 -0.9488 0.04641 0.04112 -0.0775 1.0000 0.0212
-15.250 -0.9429 0.04447 0.03912 -0.0777 1.0000 0.0215
-15.000 -0.9368 0.04262 0.03721 -0.0778 1.0000 0.0216
-14.750 -0.9306 0.04085 0.03537 -0.0777 1.0000 0.0219
-14.500 -0.9236 0.03920 0.03367 -0.0776 1.0000 0.0222
-14.250 -0.9164 0.03764 0.03204 -0.0773 1.0000 0.0225
-14.000 -0.9089 0.03614 0.03048 -0.0770 1.0000 0.0227
-13.750 -0.9005 0.03475 0.02903 -0.0766 1.0000 0.0231
-13.500 -0.8924 0.03340 0.02762 -0.0761 1.0000 0.0233
-13.000 -0.8492 0.03014 0.02430 -0.0808 0.9607 0.0242
-12.750 -0.8106 0.02864 0.02272 -0.0862 0.9428 0.0249
-12.500 -0.7768 0.02729 0.02126 -0.0903 0.9218 0.0254
-12.250 -0.7560 0.02624 0.02008 -0.0915 0.8989 0.0259
-12.000 -0.7431 0.02526 0.01897 -0.0910 0.8798 0.0264
-11.750 -0.7306 0.02440 0.01799 -0.0902 0.8644 0.0268
-11.500 -0.7201 0.02347 0.01695 -0.0891 0.8508 0.0273
-11.250 -0.7103 0.02252 0.01594 -0.0880 0.8379 0.0277
-11.000 -0.6992 0.02167 0.01502 -0.0868 0.8269 0.0282
-10.500 -0.6743 0.02018 0.01339 -0.0845 0.8060 0.0296
-10.000 -0.6489 0.01881 0.01185 -0.0820 0.7873 0.0309
-9.750 -0.6364 0.01817 0.01113 -0.0805 0.7788 0.0314
-9.500 -0.6264 0.01745 0.01037 -0.0787 0.7705 0.0323
-9.250 -0.6167 0.01690 0.00976 -0.0766 0.7623 0.0330
-9.000 -0.6040 0.01644 0.00925 -0.0749 0.7554 0.0340
-8.750 -0.5864 0.01602 0.00878 -0.0738 0.7480 0.0352
-8.250 -0.5482 0.01520 0.00787 -0.0720 0.7343 0.0381
-8.000 -0.5272 0.01485 0.00747 -0.0713 0.7271 0.0400
-7.750 -0.5052 0.01453 0.00709 -0.0707 0.7207 0.0418
-7.500 -0.4829 0.01416 0.00671 -0.0702 0.7142 0.0445
-7.250 -0.4595 0.01388 0.00638 -0.0698 0.7079 0.0475
-7.000 -0.4362 0.01355 0.00604 -0.0695 0.7023 0.0516
-6.750 -0.4119 0.01323 0.00572 -0.0692 0.6963 0.0571
-6.500 -0.3875 0.01294 0.00542 -0.0690 0.6903 0.0638
-6.250 -0.3628 0.01264 0.00512 -0.0688 0.6849 0.0727
-6.000 -0.3376 0.01232 0.00484 -0.0687 0.6792 0.0842
-5.750 -0.3125 0.01199 0.00456 -0.0686 0.6734 0.1004
-5.500 -0.2874 0.01165 0.00427 -0.0685 0.6682 0.1217
-5.250 -0.2620 0.01124 0.00398 -0.0686 0.6628 0.1524
-5.000 -0.2368 0.01079 0.00367 -0.0687 0.6571 0.1931
-4.750 -0.2121 0.01022 0.00331 -0.0688 0.6516 0.2527
-4.500 -0.1871 0.00954 0.00294 -0.0690 0.6465 0.3326
-4.250 -0.1610 0.00901 0.00273 -0.0693 0.6410 0.4145
-4.000 -0.1327 0.00891 0.00266 -0.0696 0.6360 0.4481
-3.750 -0.1040 0.00886 0.00261 -0.0698 0.6315 0.4687
-3.500 -0.0750 0.00882 0.00257 -0.0702 0.6269 0.4843
-3.250 -0.0461 0.00878 0.00254 -0.0704 0.6221 0.4952
-3.000 -0.0172 0.00878 0.00251 -0.0707 0.6176 0.5068
-2.750 0.0118 0.00881 0.00252 -0.0710 0.6135 0.5223
-2.500 0.0409 0.00881 0.00253 -0.0713 0.6093 0.5330
-2.250 0.0702 0.00882 0.00249 -0.0716 0.6049 0.5373
-2.000 0.0992 0.00882 0.00246 -0.0719 0.6008 0.5403
-1.750 0.1280 0.00883 0.00244 -0.0721 0.5971 0.5442
-1.500 0.1574 0.00883 0.00243 -0.0725 0.5934 0.5482
-1.250 0.1866 0.00884 0.00242 -0.0728 0.5895 0.5515
-1.000 0.2158 0.00886 0.00240 -0.0731 0.5856 0.5541
-0.750 0.2447 0.00889 0.00239 -0.0734 0.5818 0.5568
-0.500 0.2737 0.00890 0.00240 -0.0737 0.5783 0.5598
-0.250 0.3029 0.00891 0.00242 -0.0740 0.5749 0.5628
0.000 0.3320 0.00893 0.00244 -0.0743 0.5715 0.5658
0.250 0.3610 0.00896 0.00246 -0.0746 0.5683 0.5690
0.500 0.3899 0.00901 0.00248 -0.0749 0.5652 0.5722
0.750 0.4188 0.00907 0.00251 -0.0752 0.5624 0.5751
1.000 0.4479 0.00908 0.00257 -0.0755 0.5597 0.5783
1.250 0.4770 0.00910 0.00263 -0.0758 0.5569 0.5818
1.500 0.5059 0.00914 0.00269 -0.0761 0.5540 0.5856
1.750 0.5348 0.00920 0.00275 -0.0764 0.5511 0.5894
2.250 0.5920 0.00933 0.00289 -0.0769 0.5456 0.5972
2.500 0.6209 0.00937 0.00298 -0.0772 0.5429 0.6016
2.750 0.6496 0.00942 0.00307 -0.0775 0.5393 0.6061
3.000 0.6782 0.00948 0.00316 -0.0777 0.5353 0.6104
3.250 0.7065 0.00955 0.00325 -0.0779 0.5319 0.6145
3.500 0.7347 0.00963 0.00336 -0.0781 0.5290 0.6191
3.750 0.7631 0.00971 0.00348 -0.0783 0.5262 0.6240
4.000 0.7916 0.00977 0.00360 -0.0785 0.5224 0.6289
4.250 0.8189 0.00983 0.00369 -0.0785 0.5154 0.6335
4.500 0.8459 0.00992 0.00381 -0.0785 0.5075 0.6388
4.750 0.8726 0.01000 0.00391 -0.0784 0.4978 0.6442
5.000 0.8992 0.01011 0.00404 -0.0783 0.4883 0.6494
5.250 0.9257 0.01021 0.00418 -0.0781 0.4801 0.6548
5.500 0.9520 0.01033 0.00434 -0.0780 0.4709 0.6608
5.750 0.9768 0.01050 0.00449 -0.0776 0.4557 0.6668
6.000 1.0003 0.01070 0.00468 -0.0769 0.4331 0.6729
6.250 1.0203 0.01106 0.00493 -0.0758 0.3970 0.6795
6.500 1.0332 0.01176 0.00539 -0.0735 0.3492 0.6859
6.750 1.0445 0.01253 0.00598 -0.0710 0.3057 0.6920
7.000 1.0531 0.01336 0.00662 -0.0681 0.2635 0.6988
7.250 1.0581 0.01413 0.00723 -0.0646 0.2275 0.7053
7.500 1.0622 0.01492 0.00791 -0.0610 0.1985 0.7120
7.750 1.0682 0.01572 0.00863 -0.0579 0.1734 0.7195
8.000 1.0742 0.01659 0.00941 -0.0550 0.1520 0.7265
8.250 1.0801 0.01750 0.01027 -0.0523 0.1316 0.7343
8.500 1.0862 0.01849 0.01120 -0.0498 0.1143 0.7422
8.750 1.0926 0.01952 0.01220 -0.0476 0.0995 0.7501
9.000 1.1002 0.02057 0.01323 -0.0456 0.0873 0.7591
9.250 1.1077 0.02166 0.01432 -0.0437 0.0765 0.7678
9.500 1.1156 0.02279 0.01545 -0.0420 0.0672 0.7773
9.750 1.1235 0.02396 0.01663 -0.0404 0.0591 0.7869
10.000 1.1321 0.02515 0.01784 -0.0389 0.0528 0.7972
10.250 1.1411 0.02631 0.01905 -0.0375 0.0478 0.8076
10.500 1.1498 0.02754 0.02033 -0.0363 0.0436 0.8190
10.750 1.1575 0.02886 0.02170 -0.0349 0.0399 0.8325
11.000 1.1665 0.03009 0.02301 -0.0337 0.0371 0.8474
11.250 1.1736 0.03145 0.02443 -0.0324 0.0347 0.8657
11.750 1.1878 0.03404 0.02722 -0.0296 0.0311 0.9142
12.250 1.2089 0.03704 0.03035 -0.0291 0.0280 1.0000
12.500 1.2179 0.03868 0.03202 -0.0287 0.0267 1.0000
12.750 1.2261 0.04043 0.03379 -0.0282 0.0256 1.0000
13.000 1.2356 0.04211 0.03552 -0.0279 0.0246 1.0000
13.250 1.2443 0.04387 0.03733 -0.0276 0.0236 1.0000
13.500 1.2521 0.04576 0.03926 -0.0274 0.0227 1.0000
13.750 1.2591 0.04777 0.04130 -0.0271 0.0219 1.0000
14.000 1.2675 0.04968 0.04327 -0.0270 0.0212 1.0000
14.250 1.2755 0.05166 0.04530 -0.0270 0.0204 1.0000
14.500 1.2825 0.05379 0.04748 -0.0269 0.0197 1.0000
14.750 1.2891 0.05598 0.04972 -0.0270 0.0193 1.0000
15.000 1.2939 0.05844 0.05222 -0.0271 0.0188 1.0000
15.250 1.3009 0.06068 0.05453 -0.0272 0.0181 1.0000
15.500 1.3068 0.06307 0.05699 -0.0275 0.0176 1.0000
15.750 1.3128 0.06550 0.05948 -0.0278 0.0172 1.0000
16.000 1.3180 0.06807 0.06211 -0.0282 0.0167 1.0000
16.250 1.3224 0.07076 0.06486 -0.0286 0.0163 1.0000
16.500 1.3256 0.07368 0.06783 -0.0292 0.0159 1.0000
16.750 1.3283 0.07668 0.07089 -0.0298 0.0156 1.0000
17.000 1.3318 0.07964 0.07393 -0.0305 0.0154 1.0000
17.250 1.3352 0.08265 0.07702 -0.0312 0.0151 1.0000
17.500 1.3375 0.08587 0.08034 -0.0321 0.0148 1.0000
17.750 1.3395 0.08916 0.08371 -0.0331 0.0146 1.0000
18.000 1.3408 0.09260 0.08723 -0.0342 0.0143 1.0000
18.250 1.3420 0.09610 0.09081 -0.0354 0.0141 1.0000
18.500 1.3424 0.09976 0.09455 -0.0367 0.0139 1.0000
18.750 1.3421 0.10359 0.09846 -0.0381 0.0137 1.0000
19.000 1.3415 0.10750 0.10246 -0.0397 0.0136 1.0000
19.250 1.3394 0.11168 0.10671 -0.0415 0.0134 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64(3)-418 (naca643418-il)