NACA 1412 (naca1412-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1412 (naca1412-il) Reynolds number: 50,000 Max Cl/Cd: 31.15 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1412-il-50000-n5.txt Download as CSV file: xf-naca1412-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1412
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 -0.6491 0.09164 0.08382 -0.0263 1.0000 0.0810
-10.750 -0.7098 0.07546 0.06759 -0.0390 1.0000 0.0789
-10.500 -0.7844 0.06482 0.05664 -0.0434 1.0000 0.0766
-10.250 -0.7911 0.06154 0.05324 -0.0426 1.0000 0.0777
-9.750 -0.8008 0.05474 0.04598 -0.0403 1.0000 0.0799
-9.500 -0.8019 0.05135 0.04227 -0.0388 1.0000 0.0811
-9.250 -0.7994 0.04821 0.03879 -0.0372 1.0000 0.0829
-9.000 -0.7949 0.04525 0.03537 -0.0355 1.0000 0.0854
-8.750 -0.7860 0.04263 0.03235 -0.0339 1.0000 0.0880
-8.500 -0.7699 0.04091 0.03062 -0.0327 1.0000 0.0906
-8.250 -0.7543 0.03902 0.02854 -0.0314 1.0000 0.0933
-8.000 -0.7383 0.03709 0.02631 -0.0299 1.0000 0.0966
-7.750 -0.7217 0.03528 0.02415 -0.0285 1.0000 0.1010
-7.500 -0.7033 0.03402 0.02296 -0.0273 1.0000 0.1054
-7.250 -0.6846 0.03262 0.02140 -0.0259 1.0000 0.1108
-7.000 -0.6650 0.03120 0.01981 -0.0246 1.0000 0.1161
-6.750 -0.6463 0.03011 0.01873 -0.0233 1.0000 0.1233
-6.500 -0.6271 0.02900 0.01756 -0.0220 1.0000 0.1322
-6.250 -0.6076 0.02799 0.01644 -0.0206 1.0000 0.1431
-6.000 -0.5890 0.02704 0.01557 -0.0192 1.0000 0.1557
-5.750 -0.5700 0.02615 0.01469 -0.0179 1.0000 0.1712
-5.500 -0.5510 0.02533 0.01391 -0.0166 1.0000 0.1905
-5.250 -0.5325 0.02455 0.01326 -0.0152 1.0000 0.2122
-5.000 -0.5133 0.02384 0.01261 -0.0140 1.0000 0.2388
-4.750 -0.4939 0.02318 0.01204 -0.0127 1.0000 0.2688
-4.500 -0.4745 0.02256 0.01156 -0.0115 1.0000 0.3015
-4.250 -0.4549 0.02199 0.01114 -0.0102 1.0000 0.3362
-4.000 -0.4357 0.02148 0.01078 -0.0089 1.0000 0.3737
-3.750 -0.4167 0.02104 0.01048 -0.0074 1.0000 0.4147
-3.500 -0.3978 0.02064 0.01028 -0.0059 1.0000 0.4578
-3.250 -0.3789 0.02030 0.01012 -0.0042 1.0000 0.5039
-3.000 -0.3600 0.02002 0.01003 -0.0025 1.0000 0.5524
-2.750 -0.3411 0.01981 0.01001 -0.0006 1.0000 0.6023
-2.500 -0.3222 0.01967 0.01005 0.0014 1.0000 0.6532
-2.250 -0.3033 0.01961 0.01015 0.0036 1.0000 0.7046
-2.000 -0.2839 0.01963 0.01030 0.0057 1.0000 0.7569
-1.750 -0.2554 0.01977 0.01052 0.0061 0.9967 0.8124
-1.500 -0.2068 0.02006 0.01079 0.0028 0.9880 0.8674
-1.250 -0.1493 0.02038 0.01100 -0.0027 0.9802 0.9144
-1.000 -0.0843 0.02064 0.01113 -0.0100 0.9730 0.9517
-0.750 -0.0159 0.02077 0.01113 -0.0183 0.9651 0.9798
-0.500 0.0536 0.02078 0.01103 -0.0272 0.9574 1.0000
-0.250 0.0954 0.02070 0.01086 -0.0308 0.9421 1.0000
0.000 0.1386 0.02062 0.01072 -0.0345 0.9274 1.0000
0.250 0.1777 0.02052 0.01057 -0.0371 0.9112 1.0000
0.500 0.2129 0.02043 0.01045 -0.0388 0.8937 1.0000
0.750 0.2458 0.02035 0.01035 -0.0399 0.8754 1.0000
1.000 0.2772 0.02028 0.01026 -0.0405 0.8568 1.0000
1.250 0.3076 0.02021 0.01018 -0.0408 0.8380 1.0000
1.500 0.3371 0.02014 0.01009 -0.0408 0.8191 1.0000
1.750 0.3659 0.02008 0.01001 -0.0405 0.8001 1.0000
2.000 0.3912 0.02009 0.01001 -0.0396 0.7794 1.0000
2.250 0.4157 0.02013 0.01003 -0.0386 0.7582 1.0000
2.500 0.4408 0.02016 0.01005 -0.0375 0.7377 1.0000
2.750 0.4662 0.02020 0.01005 -0.0364 0.7175 1.0000
3.000 0.4884 0.02035 0.01019 -0.0350 0.6951 1.0000
3.250 0.5122 0.02049 0.01031 -0.0337 0.6730 1.0000
3.500 0.5363 0.02062 0.01040 -0.0324 0.6511 1.0000
3.750 0.5583 0.02084 0.01062 -0.0309 0.6269 1.0000
4.000 0.5817 0.02103 0.01076 -0.0295 0.6038 1.0000
4.250 0.6033 0.02130 0.01103 -0.0280 0.5785 1.0000
4.500 0.6261 0.02155 0.01122 -0.0265 0.5543 1.0000
4.750 0.6470 0.02188 0.01157 -0.0250 0.5275 1.0000
5.000 0.6683 0.02221 0.01186 -0.0234 0.5006 1.0000
5.250 0.6891 0.02257 0.01215 -0.0217 0.4728 1.0000
5.500 0.7088 0.02299 0.01255 -0.0201 0.4425 1.0000
5.750 0.7280 0.02345 0.01298 -0.0184 0.4115 1.0000
6.000 0.7467 0.02397 0.01344 -0.0166 0.3797 1.0000
6.250 0.7646 0.02456 0.01395 -0.0149 0.3470 1.0000
6.500 0.7816 0.02524 0.01453 -0.0131 0.3136 1.0000
6.750 0.7977 0.02604 0.01518 -0.0113 0.2804 1.0000
7.000 0.8132 0.02696 0.01597 -0.0096 0.2478 1.0000
7.250 0.8281 0.02800 0.01686 -0.0078 0.2185 1.0000
7.750 0.8578 0.03033 0.01899 -0.0047 0.1720 1.0000
8.000 0.8732 0.03160 0.02023 -0.0032 0.1542 1.0000
8.250 0.8884 0.03292 0.02151 -0.0017 0.1404 1.0000
8.500 0.9038 0.03427 0.02284 -0.0003 0.1292 1.0000
8.750 0.9214 0.03570 0.02441 0.0010 0.1198 1.0000
9.000 0.9379 0.03715 0.02582 0.0022 0.1127 1.0000
9.250 0.9550 0.03866 0.02751 0.0034 0.1056 1.0000
9.500 0.9725 0.04019 0.02895 0.0044 0.1007 1.0000
9.750 0.9911 0.04210 0.03117 0.0055 0.0965 1.0000
10.000 1.0071 0.04397 0.03325 0.0066 0.0925 1.0000
10.250 1.0230 0.04567 0.03497 0.0076 0.0890 1.0000
10.500 1.0356 0.04784 0.03733 0.0088 0.0859 1.0000
10.750 1.0426 0.05034 0.04020 0.0104 0.0832 1.0000
11.000 1.0483 0.05299 0.04314 0.0120 0.0813 1.0000
11.250 1.0502 0.05558 0.04597 0.0138 0.0797 1.0000
11.500 1.0515 0.05811 0.04869 0.0155 0.0780 1.0000
11.750 1.0560 0.06049 0.05114 0.0167 0.0763 1.0000
12.000 1.0505 0.06367 0.05447 0.0179 0.0750 1.0000
12.250 1.0301 0.06792 0.05907 0.0188 0.0745 1.0000
12.500 1.0061 0.07302 0.06447 0.0182 0.0741 1.0000
12.750 0.9779 0.07931 0.07101 0.0160 0.0741 1.0000
13.000 0.9449 0.08725 0.07917 0.0119 0.0743 1.0000
13.250 0.9069 0.09739 0.08944 0.0057 0.0748 1.0000
13.500 0.8669 0.10976 0.10191 -0.0021 0.0752 1.0000
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Polar data table (+)
Polar graphs
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