NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(1)-412 (naca651412-il) Reynolds number: 100,000 Max Cl/Cd: 51.57 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651412-il-100000-n5.txt Download as CSV file: xf-naca651412-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-412
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4401 0.09480 0.08962 -0.0522 1.0000 0.0326
-10.250 -0.4461 0.08945 0.08432 -0.0549 1.0000 0.0326
-10.000 -0.4523 0.08428 0.07922 -0.0574 1.0000 0.0324
-9.750 -0.4621 0.07882 0.07381 -0.0604 1.0000 0.0322
-9.500 -0.4763 0.07421 0.06924 -0.0623 1.0000 0.0318
-9.250 -0.4962 0.07052 0.06559 -0.0626 1.0000 0.0316
-9.000 -0.5208 0.06821 0.06334 -0.0602 1.0000 0.0311
-8.750 -0.5495 0.06663 0.06180 -0.0560 1.0000 0.0310
-8.500 -0.5626 0.06283 0.05786 -0.0562 0.9956 0.0310
-8.250 -0.5557 0.05701 0.05169 -0.0608 0.9860 0.0313
-8.000 -0.5459 0.05175 0.04598 -0.0639 0.9768 0.0318
-7.750 -0.5319 0.04727 0.04108 -0.0658 0.9685 0.0318
-7.500 -0.5120 0.04292 0.03621 -0.0678 0.9625 0.0319
-7.250 -0.4930 0.03941 0.03220 -0.0686 0.9547 0.0322
-7.000 -0.4648 0.03651 0.02858 -0.0703 0.9502 0.0333
-6.750 -0.4442 0.03359 0.02543 -0.0708 0.9430 0.0347
-6.500 -0.4152 0.03141 0.02298 -0.0721 0.9383 0.0360
-6.250 -0.3829 0.02928 0.02051 -0.0736 0.9349 0.0369
-6.000 -0.3588 0.02769 0.01864 -0.0733 0.9276 0.0379
-5.750 -0.3277 0.02626 0.01697 -0.0742 0.9231 0.0401
-5.500 -0.2938 0.02495 0.01540 -0.0754 0.9199 0.0425
-5.250 -0.2697 0.02391 0.01418 -0.0748 0.9123 0.0436
-5.000 -0.2400 0.02252 0.01276 -0.0753 0.9079 0.0451
-4.750 -0.2109 0.02151 0.01178 -0.0759 0.9035 0.0478
-4.500 -0.1875 0.02087 0.01111 -0.0754 0.8962 0.0517
-4.250 -0.1581 0.02015 0.01027 -0.0758 0.8917 0.0551
-4.000 -0.1343 0.01943 0.00952 -0.0755 0.8853 0.0588
-3.750 -0.1079 0.01891 0.00892 -0.0755 0.8794 0.0657
-3.500 -0.0782 0.01826 0.00826 -0.0761 0.8754 0.0792
-3.250 -0.0567 0.01758 0.00779 -0.0754 0.8680 0.1169
-3.000 -0.0416 0.01540 0.00759 -0.0744 0.8625 0.5413
-2.750 -0.0194 0.01551 0.00794 -0.0724 0.8571 0.6546
-2.500 -0.0017 0.01596 0.00851 -0.0690 0.8506 0.7180
-2.250 0.0179 0.01645 0.00901 -0.0655 0.8463 0.7619
-2.000 0.0385 0.01664 0.00913 -0.0635 0.8400 0.7781
-1.750 0.0648 0.01662 0.00899 -0.0631 0.8346 0.7849
-1.500 0.0955 0.01652 0.00873 -0.0638 0.8309 0.7921
-1.250 0.1188 0.01656 0.00870 -0.0630 0.8248 0.7978
-1.000 0.1461 0.01653 0.00857 -0.0631 0.8196 0.8049
-0.750 0.1754 0.01646 0.00842 -0.0633 0.8158 0.8104
-0.500 0.1991 0.01652 0.00844 -0.0628 0.8099 0.8170
-0.250 0.2256 0.01653 0.00839 -0.0627 0.8047 0.8237
0.000 0.2542 0.01649 0.00831 -0.0628 0.8010 0.8295
0.250 0.2789 0.01657 0.00836 -0.0625 0.7953 0.8372
0.500 0.3031 0.01662 0.00842 -0.0619 0.7900 0.8432
0.750 0.3323 0.01660 0.00837 -0.0622 0.7863 0.8506
1.000 0.3558 0.01669 0.00849 -0.0615 0.7808 0.8572
1.250 0.3804 0.01679 0.00860 -0.0611 0.7754 0.8654
1.500 0.4082 0.01678 0.00862 -0.0611 0.7716 0.8721
1.750 0.4327 0.01689 0.00876 -0.0607 0.7664 0.8808
2.000 0.4555 0.01701 0.00896 -0.0598 0.7607 0.8890
2.250 0.4837 0.01702 0.00901 -0.0599 0.7567 0.8978
2.500 0.5082 0.01712 0.00920 -0.0594 0.7517 0.9071
2.750 0.5317 0.01726 0.00944 -0.0588 0.7457 0.9174
3.000 0.5611 0.01726 0.00952 -0.0592 0.7417 0.9276
3.250 0.5872 0.01739 0.00977 -0.0591 0.7358 0.9395
3.500 0.6174 0.01746 0.00996 -0.0598 0.7295 0.9506
3.750 0.6554 0.01734 0.00998 -0.0617 0.7251 0.9601
4.000 0.6870 0.01753 0.01034 -0.0630 0.7161 0.9748
4.250 0.7260 0.01732 0.01028 -0.0650 0.7076 0.9901
4.500 0.7528 0.01702 0.01007 -0.0644 0.6916 1.0000
4.750 0.7757 0.01632 0.00935 -0.0624 0.6584 1.0000
5.000 0.7960 0.01577 0.00866 -0.0599 0.6059 1.0000
5.250 0.8143 0.01579 0.00860 -0.0579 0.5480 1.0000
5.500 0.8294 0.01621 0.00849 -0.0553 0.4332 1.0000
5.750 0.8266 0.01803 0.00922 -0.0509 0.2688 1.0000
6.000 0.8256 0.02011 0.01040 -0.0473 0.1315 1.0000
6.250 0.8344 0.02161 0.01147 -0.0450 0.0791 1.0000
6.500 0.8483 0.02269 0.01247 -0.0433 0.0630 1.0000
6.750 0.8611 0.02374 0.01350 -0.0414 0.0548 1.0000
7.000 0.8755 0.02471 0.01457 -0.0397 0.0502 1.0000
7.250 0.8885 0.02581 0.01570 -0.0380 0.0464 1.0000
7.500 0.9009 0.02701 0.01695 -0.0362 0.0432 1.0000
7.750 0.9158 0.02813 0.01817 -0.0348 0.0405 1.0000
8.000 0.9311 0.02939 0.01951 -0.0334 0.0386 1.0000
8.250 0.9484 0.03073 0.02088 -0.0324 0.0370 1.0000
8.500 0.9691 0.03233 0.02246 -0.0318 0.0353 1.0000
8.750 0.9954 0.03399 0.02420 -0.0319 0.0336 1.0000
9.000 1.0206 0.03547 0.02590 -0.0317 0.0319 1.0000
9.250 1.0490 0.03736 0.02798 -0.0321 0.0307 1.0000
9.500 1.0765 0.03951 0.03035 -0.0324 0.0298 1.0000
9.750 1.1003 0.04184 0.03293 -0.0323 0.0290 1.0000
10.000 1.1195 0.04430 0.03567 -0.0317 0.0285 1.0000
10.250 1.1338 0.04688 0.03857 -0.0306 0.0281 1.0000
10.500 1.1431 0.04939 0.04134 -0.0290 0.0276 1.0000
10.750 1.1491 0.05187 0.04403 -0.0273 0.0270 1.0000
11.000 1.1527 0.05479 0.04714 -0.0257 0.0264 1.0000
11.250 1.1494 0.05832 0.05091 -0.0236 0.0259 1.0000
11.500 1.1388 0.06101 0.05396 -0.0209 0.0257 1.0000
11.750 1.1270 0.06419 0.05746 -0.0187 0.0255 1.0000
12.000 1.1139 0.06782 0.06138 -0.0171 0.0254 1.0000
12.250 1.0988 0.07183 0.06567 -0.0161 0.0254 1.0000
12.500 1.0817 0.07627 0.07036 -0.0158 0.0254 1.0000
12.750 1.0633 0.08113 0.07546 -0.0162 0.0254 1.0000
13.000 1.0438 0.08649 0.08103 -0.0174 0.0254 1.0000
13.250 1.0231 0.09246 0.08720 -0.0195 0.0255 1.0000
13.500 1.0023 0.09902 0.09394 -0.0226 0.0256 1.0000
13.750 0.9811 0.10631 0.10137 -0.0265 0.0257 1.0000
14.000 0.9607 0.11439 0.10958 -0.0314 0.0259 1.0000
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Polar data table (+)
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