NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(2)-415 (naca642415-il) Reynolds number: 200,000 Max Cl/Cd: 69.96 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca642415-il-200000-n5.txt Download as CSV file: xf-naca642415-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6515 0.07983 0.07556 -0.0630 1.0000 0.0234
-13.750 -0.6824 0.07109 0.06664 -0.0689 1.0000 0.0233
-13.500 -0.7122 0.06368 0.05902 -0.0734 1.0000 0.0233
-13.250 -0.7357 0.05794 0.05307 -0.0763 1.0000 0.0233
-13.000 -0.7577 0.05297 0.04785 -0.0782 1.0000 0.0234
-12.750 -0.7769 0.04877 0.04338 -0.0790 1.0000 0.0235
-12.500 -0.7917 0.04536 0.03972 -0.0789 1.0000 0.0237
-12.250 -0.7986 0.04280 0.03701 -0.0781 1.0000 0.0238
-12.000 -0.8003 0.04088 0.03501 -0.0769 1.0000 0.0241
-11.750 -0.8024 0.03925 0.03330 -0.0752 1.0000 0.0243
-11.500 -0.8073 0.03783 0.03179 -0.0725 1.0000 0.0244
-11.250 -0.8161 0.03687 0.03079 -0.0687 1.0000 0.0247
-11.000 -0.8028 0.03537 0.02917 -0.0689 0.9914 0.0252
-10.750 -0.7785 0.03361 0.02721 -0.0710 0.9818 0.0260
-10.500 -0.7528 0.03175 0.02510 -0.0730 0.9732 0.0269
-10.250 -0.7276 0.02992 0.02297 -0.0744 0.9636 0.0278
-10.000 -0.7004 0.02829 0.02104 -0.0758 0.9549 0.0284
-9.750 -0.6713 0.02687 0.01958 -0.0773 0.9469 0.0291
-9.500 -0.6439 0.02579 0.01844 -0.0783 0.9374 0.0299
-9.000 -0.5900 0.02390 0.01631 -0.0798 0.9181 0.0322
-8.750 -0.5643 0.02299 0.01525 -0.0801 0.9086 0.0333
-8.500 -0.5407 0.02205 0.01422 -0.0799 0.8986 0.0342
-8.250 -0.5191 0.02122 0.01336 -0.0795 0.8885 0.0351
-8.000 -0.4966 0.02053 0.01262 -0.0791 0.8793 0.0363
-7.750 -0.4757 0.01992 0.01195 -0.0783 0.8691 0.0377
-7.500 -0.4533 0.01936 0.01126 -0.0778 0.8606 0.0395
-7.250 -0.4328 0.01870 0.01055 -0.0770 0.8510 0.0411
-7.000 -0.4114 0.01809 0.00990 -0.0763 0.8428 0.0428
-6.750 -0.3895 0.01757 0.00932 -0.0757 0.8338 0.0448
-6.500 -0.3663 0.01711 0.00875 -0.0752 0.8264 0.0474
-6.250 -0.3442 0.01655 0.00819 -0.0747 0.8177 0.0505
-6.000 -0.3203 0.01612 0.00767 -0.0743 0.8107 0.0543
-5.750 -0.2966 0.01566 0.00718 -0.0740 0.8024 0.0589
-5.500 -0.2720 0.01525 0.00671 -0.0737 0.7954 0.0660
-5.250 -0.2475 0.01480 0.00629 -0.0735 0.7879 0.0770
-5.000 -0.2229 0.01433 0.00586 -0.0733 0.7809 0.0962
-4.750 -0.1984 0.01377 0.00545 -0.0733 0.7743 0.1345
-4.500 -0.1747 0.01304 0.00501 -0.0733 0.7668 0.2054
-4.250 -0.1519 0.01203 0.00451 -0.0734 0.7607 0.3345
-4.000 -0.1272 0.01153 0.00448 -0.0733 0.7533 0.4521
-3.750 -0.0997 0.01145 0.00442 -0.0733 0.7470 0.4930
-3.500 -0.0719 0.01143 0.00436 -0.0733 0.7412 0.5222
-3.250 -0.0443 0.01144 0.00439 -0.0731 0.7346 0.5465
-3.000 -0.0165 0.01149 0.00441 -0.0730 0.7289 0.5700
-2.750 0.0109 0.01159 0.00451 -0.0727 0.7228 0.5932
-2.500 0.0387 0.01165 0.00453 -0.0726 0.7163 0.6081
-2.250 0.0668 0.01164 0.00446 -0.0726 0.7109 0.6132
-2.000 0.0951 0.01163 0.00440 -0.0727 0.7046 0.6193
-1.750 0.1237 0.01163 0.00432 -0.0729 0.6988 0.6253
-1.500 0.1520 0.01163 0.00426 -0.0730 0.6941 0.6296
-1.250 0.1803 0.01162 0.00424 -0.0731 0.6883 0.6344
-1.000 0.2090 0.01163 0.00418 -0.0734 0.6828 0.6395
-0.750 0.2375 0.01163 0.00413 -0.0735 0.6783 0.6436
-0.500 0.2656 0.01165 0.00415 -0.0736 0.6729 0.6478
-0.250 0.2940 0.01167 0.00416 -0.0738 0.6674 0.6531
0.000 0.3228 0.01170 0.00413 -0.0740 0.6626 0.6588
0.250 0.3508 0.01173 0.00418 -0.0741 0.6579 0.6629
0.500 0.3789 0.01177 0.00424 -0.0742 0.6529 0.6679
0.750 0.4075 0.01182 0.00427 -0.0744 0.6484 0.6736
1.000 0.4359 0.01188 0.00431 -0.0745 0.6447 0.6784
1.500 0.4919 0.01201 0.00453 -0.0748 0.6353 0.6903
1.750 0.5200 0.01207 0.00461 -0.0749 0.6309 0.6960
2.000 0.5482 0.01216 0.00471 -0.0749 0.6274 0.7018
2.250 0.5762 0.01225 0.00487 -0.0751 0.6229 0.7085
2.500 0.6038 0.01233 0.00502 -0.0751 0.6185 0.7140
2.750 0.6316 0.01242 0.00515 -0.0751 0.6143 0.7204
3.000 0.6599 0.01252 0.00526 -0.0753 0.6096 0.7275
3.250 0.6864 0.01260 0.00546 -0.0751 0.6037 0.7336
3.500 0.7140 0.01270 0.00562 -0.0751 0.5989 0.7412
3.750 0.7418 0.01281 0.00576 -0.0751 0.5949 0.7481
4.000 0.7681 0.01292 0.00600 -0.0749 0.5888 0.7556
4.250 0.7949 0.01298 0.00611 -0.0746 0.5808 0.7632
4.500 0.8198 0.01303 0.00624 -0.0740 0.5692 0.7703
4.750 0.8452 0.01308 0.00632 -0.0735 0.5553 0.7787
5.000 0.8692 0.01314 0.00644 -0.0727 0.5414 0.7861
5.250 0.8937 0.01323 0.00656 -0.0721 0.5255 0.7953
5.500 0.9156 0.01333 0.00670 -0.0709 0.5041 0.8035
5.750 0.9378 0.01350 0.00686 -0.0698 0.4799 0.8130
6.000 0.9585 0.01370 0.00708 -0.0685 0.4527 0.8220
6.250 0.9768 0.01403 0.00732 -0.0669 0.4075 0.8319
6.500 0.9851 0.01484 0.00776 -0.0637 0.3375 0.8436
6.750 0.9896 0.01587 0.00849 -0.0601 0.2728 0.8557
7.000 0.9934 0.01691 0.00927 -0.0565 0.2185 0.8697
7.250 0.9970 0.01783 0.01002 -0.0529 0.1765 0.8863
7.750 1.0017 0.01950 0.01147 -0.0453 0.1167 0.9437
8.000 1.0121 0.02048 0.01236 -0.0436 0.0940 1.0000
8.250 1.0226 0.02157 0.01335 -0.0421 0.0770 1.0000
8.500 1.0333 0.02267 0.01439 -0.0406 0.0651 1.0000
8.750 1.0447 0.02376 0.01546 -0.0393 0.0571 1.0000
9.000 1.0556 0.02491 0.01662 -0.0381 0.0510 1.0000
9.250 1.0658 0.02614 0.01784 -0.0368 0.0463 1.0000
9.500 1.0769 0.02735 0.01909 -0.0357 0.0429 1.0000
9.750 1.0870 0.02867 0.02042 -0.0346 0.0397 1.0000
10.000 1.0959 0.03010 0.02189 -0.0336 0.0376 1.0000
10.250 1.1064 0.03147 0.02334 -0.0327 0.0354 1.0000
10.500 1.1157 0.03295 0.02487 -0.0318 0.0336 1.0000
10.750 1.1224 0.03469 0.02662 -0.0308 0.0322 1.0000
11.000 1.1318 0.03624 0.02826 -0.0300 0.0306 1.0000
11.250 1.1409 0.03786 0.02994 -0.0293 0.0293 1.0000
11.500 1.1493 0.03957 0.03172 -0.0287 0.0280 1.0000
11.750 1.1561 0.04145 0.03364 -0.0281 0.0271 1.0000
12.000 1.1621 0.04345 0.03568 -0.0274 0.0264 1.0000
12.250 1.1705 0.04528 0.03762 -0.0269 0.0256 1.0000
12.500 1.1786 0.04717 0.03960 -0.0264 0.0249 1.0000
12.750 1.1864 0.04912 0.04163 -0.0260 0.0242 1.0000
13.000 1.1941 0.05112 0.04371 -0.0256 0.0236 1.0000
13.250 1.2015 0.05319 0.04584 -0.0254 0.0230 1.0000
13.500 1.2086 0.05531 0.04802 -0.0251 0.0226 1.0000
13.750 1.2153 0.05753 0.05026 -0.0249 0.0221 1.0000
14.000 1.2233 0.05971 0.05257 -0.0247 0.0217 1.0000
14.250 1.2305 0.06201 0.05502 -0.0246 0.0211 1.0000
14.500 1.2368 0.06444 0.05761 -0.0247 0.0206 1.0000
14.750 1.2423 0.06701 0.06031 -0.0248 0.0201 1.0000
15.000 1.2470 0.06971 0.06313 -0.0251 0.0197 1.0000
15.250 1.2512 0.07253 0.06606 -0.0255 0.0194 1.0000
15.500 1.2545 0.07549 0.06914 -0.0260 0.0191 1.0000
15.750 1.2572 0.07858 0.07233 -0.0266 0.0188 1.0000
16.000 1.2593 0.08180 0.07566 -0.0274 0.0186 1.0000
16.250 1.2609 0.08516 0.07912 -0.0282 0.0184 1.0000
16.500 1.2621 0.08863 0.08270 -0.0291 0.0182 1.0000
16.750 1.2593 0.09280 0.08704 -0.0305 0.0181 1.0000
17.000 1.2531 0.09767 0.09214 -0.0323 0.0179 1.0000
17.250 1.2449 0.10300 0.09770 -0.0345 0.0178 1.0000
17.500 1.2349 0.10881 0.10375 -0.0372 0.0177 1.0000
17.750 1.2226 0.11521 0.11038 -0.0405 0.0176 1.0000
18.000 1.2083 0.12224 0.11764 -0.0444 0.0176 1.0000
18.250 1.1922 0.12997 0.12560 -0.0490 0.0176 1.0000
18.500 1.1723 0.13893 0.13480 -0.0547 0.0175 1.0000
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Polar data table (+)
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