NACA 64(3)-418 (naca643418-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64(3)-418 (naca643418-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.71 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca643418-il-1000000.txt Download as CSV file: xf-naca643418-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0159 0.09241 0.08912 -0.0574 1.0000 0.0185
-19.500 -1.0241 0.08761 0.08423 -0.0598 1.0000 0.0186
-19.250 -1.0306 0.08315 0.07968 -0.0620 1.0000 0.0187
-19.000 -1.0362 0.07884 0.07526 -0.0642 1.0000 0.0189
-18.750 -1.0415 0.07481 0.07114 -0.0659 1.0000 0.0190
-18.500 -1.0431 0.07127 0.06752 -0.0676 1.0000 0.0191
-18.250 -1.0449 0.06777 0.06392 -0.0691 1.0000 0.0193
-18.000 -1.0454 0.06452 0.06058 -0.0705 1.0000 0.0195
-17.750 -1.0453 0.06149 0.05746 -0.0716 1.0000 0.0196
-17.500 -1.0427 0.05874 0.05463 -0.0727 1.0000 0.0197
-17.250 -1.0399 0.05605 0.05186 -0.0737 1.0000 0.0198
-17.000 -1.0443 0.05296 0.04868 -0.0741 1.0000 0.0201
-16.750 -1.0428 0.05042 0.04609 -0.0746 1.0000 0.0204
-16.500 -1.0396 0.04806 0.04370 -0.0751 1.0000 0.0206
-16.250 -1.0336 0.04601 0.04161 -0.0756 1.0000 0.0208
-16.000 -1.0282 0.04397 0.03951 -0.0759 1.0000 0.0210
-15.750 -1.0213 0.04210 0.03760 -0.0762 1.0000 0.0213
-15.500 -1.0139 0.04033 0.03579 -0.0763 1.0000 0.0215
-15.250 -1.0063 0.03863 0.03404 -0.0764 1.0000 0.0218
-15.000 -0.9983 0.03705 0.03241 -0.0764 1.0000 0.0219
-14.750 -0.9909 0.03545 0.03076 -0.0762 1.0000 0.0222
-14.500 -0.9806 0.03411 0.02936 -0.0761 1.0000 0.0225
-14.250 -0.9703 0.03281 0.02801 -0.0759 1.0000 0.0228
-14.000 -0.9601 0.03154 0.02669 -0.0755 1.0000 0.0230
-13.750 -0.9510 0.03023 0.02533 -0.0750 1.0000 0.0231
-13.500 -0.9447 0.02877 0.02383 -0.0742 1.0000 0.0235
-13.250 -0.9409 0.02719 0.02223 -0.0733 1.0000 0.0239
-13.000 -0.9218 0.02574 0.02076 -0.0746 0.9773 0.0243
-12.750 -0.8804 0.02443 0.01941 -0.0801 0.9659 0.0248
-12.500 -0.8349 0.02320 0.01813 -0.0862 0.9531 0.0254
-12.250 -0.7935 0.02217 0.01699 -0.0912 0.9316 0.0261
-12.000 -0.7736 0.02135 0.01601 -0.0917 0.9044 0.0266
-11.750 -0.7587 0.02076 0.01531 -0.0908 0.8841 0.0269
-11.500 -0.7518 0.01978 0.01422 -0.0891 0.8665 0.0274
-11.250 -0.7455 0.01880 0.01314 -0.0873 0.8520 0.0278
-11.000 -0.7360 0.01797 0.01225 -0.0857 0.8398 0.0282
-10.750 -0.7241 0.01730 0.01152 -0.0843 0.8295 0.0288
-10.500 -0.7118 0.01668 0.01084 -0.0828 0.8194 0.0294
-10.250 -0.6998 0.01608 0.01018 -0.0811 0.8104 0.0300
-10.000 -0.6879 0.01555 0.00958 -0.0793 0.8012 0.0306
-9.750 -0.6783 0.01510 0.00906 -0.0770 0.7927 0.0310
-9.500 -0.6655 0.01463 0.00853 -0.0752 0.7844 0.0317
-9.250 -0.6506 0.01410 0.00795 -0.0737 0.7769 0.0328
-9.000 -0.6307 0.01371 0.00753 -0.0728 0.7699 0.0339
-8.750 -0.6095 0.01338 0.00716 -0.0721 0.7627 0.0349
-8.500 -0.5867 0.01310 0.00682 -0.0716 0.7562 0.0359
-8.250 -0.5656 0.01266 0.00636 -0.0709 0.7494 0.0377
-8.000 -0.5426 0.01235 0.00602 -0.0704 0.7425 0.0394
-7.750 -0.5178 0.01210 0.00573 -0.0702 0.7364 0.0412
-7.500 -0.4941 0.01175 0.00537 -0.0699 0.7298 0.0441
-7.250 -0.4692 0.01152 0.00510 -0.0696 0.7232 0.0472
-7.000 -0.4441 0.01119 0.00479 -0.0695 0.7174 0.0520
-6.750 -0.4187 0.01090 0.00451 -0.0693 0.7109 0.0583
-6.500 -0.3934 0.01063 0.00424 -0.0692 0.7044 0.0676
-6.250 -0.3672 0.01032 0.00398 -0.0692 0.6985 0.0804
-6.000 -0.3415 0.00997 0.00371 -0.0692 0.6921 0.0989
-5.750 -0.3159 0.00963 0.00344 -0.0692 0.6860 0.1251
-5.500 -0.2897 0.00920 0.00317 -0.0694 0.6806 0.1618
-5.250 -0.2640 0.00871 0.00287 -0.0696 0.6746 0.2121
-5.000 -0.2391 0.00807 0.00251 -0.0697 0.6686 0.2887
-4.750 -0.2134 0.00729 0.00216 -0.0701 0.6637 0.3898
-4.500 -0.1851 0.00706 0.00207 -0.0705 0.6581 0.4443
-4.250 -0.1562 0.00701 0.00201 -0.0708 0.6524 0.4637
-4.000 -0.1268 0.00696 0.00197 -0.0711 0.6476 0.4763
-3.750 -0.0972 0.00695 0.00193 -0.0715 0.6423 0.4861
-3.500 -0.0680 0.00693 0.00189 -0.0718 0.6371 0.4944
-3.250 -0.0387 0.00697 0.00187 -0.0721 0.6320 0.5029
-3.000 -0.0091 0.00692 0.00186 -0.0725 0.6275 0.5121
-2.750 0.0204 0.00695 0.00184 -0.0729 0.6226 0.5184
-2.500 0.0495 0.00695 0.00183 -0.0732 0.6177 0.5258
-2.250 0.0790 0.00700 0.00185 -0.0735 0.6133 0.5350
-2.000 0.1086 0.00699 0.00186 -0.0739 0.6090 0.5430
-1.750 0.1380 0.00700 0.00186 -0.0742 0.6043 0.5478
-1.500 0.1672 0.00704 0.00185 -0.0746 0.5996 0.5508
-1.250 0.1967 0.00707 0.00185 -0.0749 0.5957 0.5539
-1.000 0.2265 0.00708 0.00184 -0.0753 0.5921 0.5570
-0.750 0.2558 0.00706 0.00184 -0.0757 0.5882 0.5611
-0.500 0.2849 0.00708 0.00185 -0.0760 0.5843 0.5643
-0.250 0.3139 0.00714 0.00187 -0.0763 0.5799 0.5673
0.000 0.3437 0.00715 0.00189 -0.0767 0.5772 0.5705
0.250 0.3733 0.00717 0.00190 -0.0771 0.5740 0.5734
0.500 0.4027 0.00718 0.00192 -0.0775 0.5707 0.5768
0.750 0.4318 0.00720 0.00195 -0.0778 0.5674 0.5806
1.000 0.4607 0.00727 0.00200 -0.0781 0.5638 0.5842
1.250 0.4901 0.00731 0.00205 -0.0785 0.5609 0.5879
1.500 0.5196 0.00733 0.00208 -0.0789 0.5581 0.5914
1.750 0.5489 0.00735 0.00212 -0.0792 0.5549 0.5953
2.000 0.5779 0.00737 0.00217 -0.0796 0.5515 0.5997
2.250 0.6067 0.00744 0.00224 -0.0798 0.5477 0.6041
2.500 0.6356 0.00752 0.00231 -0.0801 0.5443 0.6084
2.750 0.6649 0.00755 0.00237 -0.0805 0.5418 0.6124
3.000 0.6941 0.00756 0.00244 -0.0808 0.5392 0.6177
3.250 0.7230 0.00760 0.00251 -0.0811 0.5358 0.6230
3.500 0.7513 0.00769 0.00258 -0.0813 0.5304 0.6279
3.750 0.7798 0.00773 0.00265 -0.0815 0.5249 0.6330
4.000 0.8085 0.00774 0.00271 -0.0818 0.5192 0.6385
4.250 0.8360 0.00784 0.00280 -0.0818 0.5117 0.6441
4.500 0.8648 0.00788 0.00287 -0.0821 0.5070 0.6490
4.750 0.8932 0.00792 0.00296 -0.0823 0.5013 0.6551
5.000 0.9202 0.00804 0.00307 -0.0823 0.4933 0.6612
5.250 0.9485 0.00809 0.00316 -0.0825 0.4848 0.6668
5.500 0.9752 0.00821 0.00328 -0.0824 0.4761 0.6730
5.750 1.0033 0.00827 0.00340 -0.0825 0.4688 0.6794
6.000 1.0297 0.00842 0.00354 -0.0824 0.4584 0.6855
6.250 1.0562 0.00854 0.00368 -0.0823 0.4457 0.6920
6.500 1.0812 0.00874 0.00386 -0.0820 0.4267 0.6988
6.750 1.1001 0.00927 0.00417 -0.0806 0.3773 0.7050
7.000 1.1114 0.01017 0.00478 -0.0781 0.3166 0.7119
7.250 1.1203 0.01114 0.00545 -0.0753 0.2577 0.7192
7.500 1.1282 0.01204 0.00610 -0.0722 0.2097 0.7263
7.750 1.1345 0.01278 0.00669 -0.0688 0.1746 0.7343
8.000 1.1394 0.01347 0.00725 -0.0652 0.1494 0.7422
8.250 1.1454 0.01417 0.00789 -0.0619 0.1285 0.7503
8.500 1.1523 0.01491 0.00856 -0.0589 0.1112 0.7589
8.750 1.1601 0.01566 0.00927 -0.0562 0.0970 0.7672
9.000 1.1683 0.01645 0.01004 -0.0538 0.0850 0.7763
9.250 1.1764 0.01730 0.01088 -0.0515 0.0746 0.7852
9.500 1.1847 0.01821 0.01178 -0.0494 0.0654 0.7951
9.750 1.1927 0.01917 0.01274 -0.0473 0.0572 0.8051
10.250 1.2091 0.02123 0.01484 -0.0436 0.0453 0.8283
10.500 1.2179 0.02228 0.01593 -0.0419 0.0410 0.8415
10.750 1.2271 0.02332 0.01703 -0.0404 0.0379 0.8569
11.000 1.2343 0.02450 0.01826 -0.0387 0.0351 0.8752
11.250 1.2430 0.02556 0.01941 -0.0371 0.0332 0.8958
11.500 1.2492 0.02668 0.02062 -0.0352 0.0314 0.9252
11.750 1.2606 0.02795 0.02200 -0.0348 0.0296 1.0000
12.000 1.2716 0.02923 0.02330 -0.0340 0.0282 1.0000
12.250 1.2803 0.03069 0.02477 -0.0332 0.0267 1.0000
12.500 1.2882 0.03226 0.02637 -0.0323 0.0254 1.0000
12.750 1.2988 0.03365 0.02780 -0.0318 0.0243 1.0000
13.000 1.3076 0.03521 0.02938 -0.0311 0.0232 1.0000
13.250 1.3124 0.03715 0.03134 -0.0304 0.0221 1.0000
13.500 1.3224 0.03870 0.03294 -0.0299 0.0213 1.0000
13.750 1.3319 0.04032 0.03460 -0.0296 0.0205 1.0000
14.000 1.3395 0.04216 0.03647 -0.0292 0.0197 1.0000
14.250 1.3435 0.04437 0.03870 -0.0287 0.0189 1.0000
14.500 1.3505 0.04636 0.04074 -0.0285 0.0183 1.0000
14.750 1.3587 0.04825 0.04269 -0.0283 0.0180 1.0000
15.000 1.3659 0.05030 0.04479 -0.0282 0.0175 1.0000
15.250 1.3730 0.05236 0.04689 -0.0281 0.0169 1.0000
15.500 1.3784 0.05466 0.04923 -0.0281 0.0165 1.0000
15.750 1.3817 0.05725 0.05186 -0.0282 0.0161 1.0000
16.000 1.3814 0.06030 0.05498 -0.0283 0.0157 1.0000
16.250 1.3866 0.06279 0.05753 -0.0286 0.0155 1.0000
16.500 1.3932 0.06512 0.05993 -0.0289 0.0153 1.0000
16.750 1.3968 0.06788 0.06276 -0.0293 0.0151 1.0000
17.000 1.4016 0.07053 0.06547 -0.0297 0.0149 1.0000
17.250 1.4044 0.07349 0.06849 -0.0303 0.0147 1.0000
17.500 1.4081 0.07634 0.07141 -0.0309 0.0145 1.0000
17.750 1.4097 0.07954 0.07468 -0.0317 0.0143 1.0000
18.000 1.4120 0.08269 0.07789 -0.0325 0.0141 1.0000
18.250 1.4134 0.08602 0.08129 -0.0334 0.0140 1.0000
18.500 1.4133 0.08961 0.08494 -0.0345 0.0138 1.0000
18.750 1.4127 0.09329 0.08870 -0.0357 0.0136 1.0000
19.000 1.4108 0.09726 0.09274 -0.0370 0.0136 1.0000
19.250 1.4052 0.10182 0.09737 -0.0387 0.0133 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64(3)-418 (naca643418-il)