NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(2)-415 (naca662415-il) Reynolds number: 50,000 Max Cl/Cd: 21.4 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca662415-il-50000-n5.txt Download as CSV file: xf-naca662415-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4990 0.11083 0.10404 -0.0509 1.0000 0.0635
-10.750 -0.5158 0.10632 0.09960 -0.0515 0.9999 0.0624
-10.500 -0.5316 0.09729 0.09056 -0.0589 0.9954 0.0605
-10.250 -0.6031 0.08672 0.07967 -0.0667 0.9870 0.0574
-10.000 -0.6131 0.08316 0.07602 -0.0669 0.9823 0.0571
-9.750 -0.6270 0.08001 0.07275 -0.0660 0.9769 0.0568
-9.500 -0.6396 0.07668 0.06926 -0.0649 0.9716 0.0567
-9.250 -0.6506 0.07330 0.06566 -0.0635 0.9659 0.0566
-9.000 -0.6584 0.06981 0.06185 -0.0622 0.9611 0.0567
-8.750 -0.6701 0.06698 0.05871 -0.0591 0.9559 0.0569
-8.250 -0.6636 0.06102 0.05222 -0.0566 0.9491 0.0584
-8.000 -0.6614 0.05865 0.04962 -0.0542 0.9451 0.0589
-7.750 -0.6565 0.05617 0.04680 -0.0521 0.9412 0.0592
-7.500 -0.6466 0.05362 0.04388 -0.0506 0.9381 0.0594
-7.250 -0.6325 0.05124 0.04113 -0.0495 0.9357 0.0598
-7.000 -0.6144 0.04912 0.03867 -0.0490 0.9338 0.0607
-6.750 -0.6034 0.04755 0.03686 -0.0469 0.9310 0.0624
-6.500 -0.5893 0.04597 0.03497 -0.0451 0.9280 0.0641
-6.250 -0.5704 0.04438 0.03299 -0.0440 0.9253 0.0658
-6.000 -0.5474 0.04289 0.03115 -0.0434 0.9231 0.0670
-5.750 -0.5217 0.04162 0.02954 -0.0430 0.9213 0.0682
-5.500 -0.4952 0.04039 0.02830 -0.0431 0.9200 0.0709
-5.250 -0.4677 0.03955 0.02738 -0.0432 0.9186 0.0748
-5.000 -0.4398 0.03886 0.02655 -0.0429 0.9171 0.0781
-4.750 -0.4202 0.03834 0.02586 -0.0412 0.9146 0.0805
-4.500 -0.4017 0.03771 0.02521 -0.0397 0.9120 0.0843
-4.250 -0.3843 0.03718 0.02464 -0.0382 0.9096 0.0900
-4.000 -0.3664 0.03673 0.02404 -0.0367 0.9074 0.0957
-3.750 -0.3489 0.03609 0.02343 -0.0355 0.9052 0.1021
-3.500 -0.3287 0.03550 0.02283 -0.0348 0.9030 0.1144
-3.250 -0.3136 0.03475 0.02225 -0.0334 0.9005 0.1386
-3.000 -0.3103 0.03330 0.02155 -0.0304 0.8975 0.2304
-2.750 -0.3208 0.03271 0.02345 -0.0202 0.8945 0.6842
-2.500 -0.3145 0.03394 0.02457 -0.0138 0.8911 0.7728
-2.250 -0.2986 0.03568 0.02617 -0.0077 0.8887 0.8319
-2.000 -0.1766 0.03916 0.02913 -0.0186 0.8913 0.9120
-1.750 -0.1359 0.03920 0.02891 -0.0220 0.8893 0.9171
-1.500 -0.1068 0.03925 0.02875 -0.0233 0.8869 0.9238
-1.250 -0.0812 0.03926 0.02858 -0.0239 0.8839 0.9294
-1.000 -0.0617 0.03924 0.02843 -0.0236 0.8801 0.9351
-0.750 -0.0435 0.03925 0.02833 -0.0229 0.8762 0.9409
-0.500 -0.0108 0.03934 0.02829 -0.0250 0.8733 0.9445
-0.250 0.0199 0.03948 0.02830 -0.0267 0.8705 0.9485
0.000 0.0341 0.03954 0.02829 -0.0254 0.8660 0.9535
0.250 0.0578 0.03964 0.02833 -0.0259 0.8617 0.9571
0.500 0.0841 0.03979 0.02841 -0.0268 0.8577 0.9606
0.750 0.1120 0.04000 0.02856 -0.0278 0.8544 0.9640
1.000 0.1319 0.04016 0.02869 -0.0278 0.8491 0.9674
1.250 0.1545 0.04034 0.02886 -0.0281 0.8439 0.9708
1.500 0.1829 0.04058 0.02907 -0.0292 0.8397 0.9737
1.750 0.2084 0.04084 0.02934 -0.0300 0.8348 0.9770
2.000 0.2298 0.04108 0.02960 -0.0302 0.8284 0.9806
2.250 0.2601 0.04137 0.02991 -0.0317 0.8238 0.9837
2.500 0.2831 0.04167 0.03025 -0.0321 0.8178 0.9870
2.750 0.3065 0.04197 0.03060 -0.0326 0.8110 0.9906
3.000 0.3410 0.04229 0.03099 -0.0348 0.8066 0.9938
3.250 0.3583 0.04268 0.03145 -0.0344 0.7983 0.9990
3.500 0.3808 0.04291 0.03176 -0.0343 0.7922 1.0000
3.750 0.3841 0.04309 0.03199 -0.0310 0.7832 1.0000
4.000 0.4024 0.04322 0.03220 -0.0299 0.7764 1.0000
4.500 0.4266 0.04344 0.03256 -0.0258 0.7598 1.0000
4.750 0.4259 0.04354 0.03274 -0.0218 0.7487 1.0000
5.000 0.4545 0.04353 0.03285 -0.0221 0.7428 1.0000
5.250 0.4529 0.04362 0.03299 -0.0180 0.7305 1.0000
5.500 0.4621 0.04375 0.03321 -0.0156 0.7196 1.0000
5.750 0.4925 0.04370 0.03332 -0.0161 0.7126 1.0000
6.000 0.5031 0.04395 0.03368 -0.0141 0.7000 1.0000
6.250 0.5204 0.04415 0.03401 -0.0131 0.6880 1.0000
6.500 0.5469 0.04413 0.03419 -0.0131 0.6777 1.0000
7.000 0.5957 0.04395 0.03440 -0.0123 0.6527 1.0000
7.500 0.6413 0.04357 0.03450 -0.0108 0.6229 1.0000
8.000 0.6889 0.03859 0.02984 -0.0042 0.5390 1.0000
8.250 0.7244 0.03561 0.02670 -0.0012 0.4481 1.0000
8.500 0.7481 0.03495 0.02502 0.0018 0.2951 1.0000
8.750 0.7415 0.03737 0.02658 0.0047 0.1896 1.0000
9.000 0.7397 0.03984 0.02847 0.0067 0.1325 1.0000
9.250 0.7445 0.04195 0.03028 0.0081 0.1092 1.0000
9.750 0.7653 0.04537 0.03366 0.0102 0.0875 1.0000
10.000 0.7792 0.04689 0.03519 0.0111 0.0809 1.0000
10.250 0.7983 0.04814 0.03654 0.0118 0.0754 1.0000
10.500 0.8219 0.04930 0.03766 0.0122 0.0706 1.0000
10.750 0.8549 0.05012 0.03873 0.0122 0.0652 1.0000
11.000 0.8965 0.05105 0.03970 0.0115 0.0613 1.0000
11.250 0.9376 0.05261 0.04147 0.0106 0.0577 1.0000
11.500 0.9669 0.05459 0.04374 0.0102 0.0547 1.0000
11.750 0.9947 0.05696 0.04636 0.0099 0.0531 1.0000
12.000 1.0162 0.05955 0.04916 0.0098 0.0517 1.0000
12.250 1.0369 0.06251 0.05222 0.0095 0.0502 1.0000
12.500 1.0346 0.06554 0.05569 0.0113 0.0495 1.0000
12.750 1.0285 0.06879 0.05934 0.0129 0.0488 1.0000
13.000 1.0196 0.07234 0.06324 0.0143 0.0483 1.0000
13.250 1.0077 0.07617 0.06739 0.0154 0.0480 1.0000
13.500 0.9930 0.08035 0.07188 0.0162 0.0478 1.0000
13.750 0.9759 0.08489 0.07670 0.0164 0.0477 1.0000
14.000 0.9560 0.08995 0.08201 0.0160 0.0478 1.0000
14.250 0.9341 0.09557 0.08786 0.0148 0.0480 1.0000
14.500 0.9099 0.10195 0.09445 0.0125 0.0482 1.0000
14.750 0.8853 0.10912 0.10180 0.0092 0.0485 1.0000
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Polar data table (+)
Polar graphs
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