NACA 1412 (naca1412-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1412 (naca1412-il) Reynolds number: 100,000 Max Cl/Cd: 44.07 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1412-il-100000.txt Download as CSV file: xf-naca1412-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7131 0.07555 0.07014 -0.0405 1.0000 0.0995
-10.250 -0.7225 0.07035 0.06491 -0.0414 1.0000 0.0980
-10.000 -0.7491 0.06473 0.05918 -0.0416 1.0000 0.0962
-9.750 -0.7792 0.05833 0.05251 -0.0411 1.0000 0.0941
-9.500 -0.7976 0.05289 0.04670 -0.0395 1.0000 0.0932
-9.250 -0.8037 0.04875 0.04221 -0.0375 1.0000 0.0937
-9.000 -0.8042 0.04510 0.03819 -0.0354 1.0000 0.0946
-8.750 -0.8011 0.04172 0.03440 -0.0331 1.0000 0.0954
-8.500 -0.7942 0.03869 0.03095 -0.0308 1.0000 0.0964
-8.250 -0.7844 0.03626 0.02807 -0.0285 1.0000 0.0985
-8.000 -0.7728 0.03437 0.02565 -0.0261 1.0000 0.1005
-7.750 -0.7556 0.03177 0.02298 -0.0249 1.0000 0.1029
-7.500 -0.7370 0.03013 0.02124 -0.0235 1.0000 0.1054
-7.250 -0.7180 0.02874 0.01969 -0.0221 1.0000 0.1090
-7.000 -0.6993 0.02747 0.01809 -0.0204 1.0000 0.1134
-6.750 -0.6788 0.02583 0.01643 -0.0193 1.0000 0.1176
-6.500 -0.6579 0.02469 0.01527 -0.0180 1.0000 0.1228
-6.250 -0.6372 0.02360 0.01395 -0.0166 1.0000 0.1294
-6.000 -0.6166 0.02252 0.01305 -0.0155 1.0000 0.1384
-5.750 -0.5962 0.02150 0.01205 -0.0142 1.0000 0.1495
-5.500 -0.5758 0.02055 0.01116 -0.0129 1.0000 0.1639
-5.250 -0.5560 0.01973 0.01045 -0.0115 1.0000 0.1833
-5.000 -0.5362 0.01896 0.00980 -0.0103 1.0000 0.2081
-4.750 -0.5162 0.01831 0.00927 -0.0090 1.0000 0.2378
-4.500 -0.4964 0.01769 0.00888 -0.0079 1.0000 0.2717
-4.250 -0.4763 0.01715 0.00856 -0.0067 1.0000 0.3108
-4.000 -0.4559 0.01666 0.00831 -0.0056 1.0000 0.3547
-3.750 -0.4350 0.01623 0.00811 -0.0046 1.0000 0.4022
-3.500 -0.4139 0.01585 0.00798 -0.0036 1.0000 0.4520
-3.250 -0.3927 0.01553 0.00792 -0.0024 1.0000 0.5038
-3.000 -0.3718 0.01528 0.00792 -0.0012 1.0000 0.5582
-2.750 -0.3512 0.01510 0.00799 0.0002 1.0000 0.6146
-2.500 -0.3315 0.01500 0.00815 0.0019 1.0000 0.6711
-2.250 -0.3127 0.01499 0.00834 0.0039 1.0000 0.7291
-2.000 -0.2958 0.01508 0.00863 0.0066 1.0000 0.7850
-1.750 -0.2796 0.01528 0.00898 0.0094 1.0000 0.8424
-1.500 -0.2488 0.01568 0.00943 0.0096 0.9971 0.9014
-1.250 -0.1819 0.01628 0.00995 0.0026 0.9909 0.9512
-1.000 -0.0985 0.01681 0.01032 -0.0082 0.9873 0.9817
-0.750 -0.0100 0.01707 0.01045 -0.0205 0.9846 1.0000
-0.500 0.0466 0.01700 0.01028 -0.0274 0.9724 1.0000
-0.250 0.1020 0.01688 0.01011 -0.0336 0.9598 1.0000
0.000 0.1566 0.01672 0.00990 -0.0394 0.9466 1.0000
0.250 0.2111 0.01648 0.00964 -0.0449 0.9332 1.0000
0.500 0.2607 0.01617 0.00932 -0.0491 0.9183 1.0000
0.750 0.3044 0.01582 0.00897 -0.0519 0.9016 1.0000
1.000 0.3417 0.01548 0.00863 -0.0532 0.8834 1.0000
1.250 0.3736 0.01516 0.00829 -0.0534 0.8646 1.0000
1.500 0.3975 0.01500 0.00810 -0.0521 0.8425 1.0000
1.750 0.4213 0.01484 0.00791 -0.0506 0.8208 1.0000
2.000 0.4453 0.01470 0.00771 -0.0491 0.8001 1.0000
2.250 0.4667 0.01468 0.00765 -0.0473 0.7767 1.0000
2.500 0.4890 0.01466 0.00756 -0.0456 0.7539 1.0000
2.750 0.5114 0.01468 0.00750 -0.0439 0.7311 1.0000
3.000 0.5331 0.01477 0.00754 -0.0422 0.7069 1.0000
3.250 0.5562 0.01486 0.00752 -0.0406 0.6846 1.0000
3.500 0.5775 0.01503 0.00765 -0.0390 0.6593 1.0000
3.750 0.6002 0.01517 0.00768 -0.0374 0.6358 1.0000
4.000 0.6214 0.01537 0.00784 -0.0358 0.6092 1.0000
4.250 0.6432 0.01558 0.00795 -0.0342 0.5834 1.0000
4.500 0.6646 0.01581 0.00811 -0.0325 0.5566 1.0000
4.750 0.6856 0.01608 0.00831 -0.0309 0.5288 1.0000
5.000 0.7065 0.01637 0.00851 -0.0293 0.5007 1.0000
5.250 0.7269 0.01668 0.00871 -0.0276 0.4709 1.0000
5.500 0.7464 0.01700 0.00896 -0.0257 0.4378 1.0000
5.750 0.7650 0.01736 0.00922 -0.0239 0.4009 1.0000
6.000 0.7830 0.01779 0.00949 -0.0219 0.3624 1.0000
6.250 0.8005 0.01834 0.00989 -0.0200 0.3216 1.0000
6.500 0.8171 0.01906 0.01038 -0.0181 0.2815 1.0000
6.750 0.8334 0.01994 0.01106 -0.0162 0.2412 1.0000
7.000 0.8491 0.02100 0.01187 -0.0143 0.2062 1.0000
7.250 0.8652 0.02218 0.01285 -0.0125 0.1769 1.0000
7.500 0.8821 0.02347 0.01393 -0.0109 0.1552 1.0000
7.750 0.9013 0.02478 0.01515 -0.0095 0.1395 1.0000
8.000 0.9227 0.02627 0.01643 -0.0086 0.1284 1.0000
8.250 0.9440 0.02742 0.01775 -0.0074 0.1197 1.0000
8.500 0.9672 0.02901 0.01923 -0.0069 0.1129 1.0000
8.750 0.9891 0.03040 0.02084 -0.0059 0.1076 1.0000
9.000 1.0124 0.03194 0.02240 -0.0053 0.1035 1.0000
9.250 1.0363 0.03417 0.02462 -0.0050 0.0998 1.0000
9.500 1.0535 0.03579 0.02663 -0.0035 0.0966 1.0000
9.750 1.0716 0.03765 0.02874 -0.0022 0.0936 1.0000
10.000 1.0893 0.03971 0.03098 -0.0011 0.0914 1.0000
10.250 1.1076 0.04195 0.03330 -0.0003 0.0889 1.0000
10.500 1.1188 0.04512 0.03673 0.0012 0.0870 1.0000
10.750 1.1212 0.04766 0.03977 0.0039 0.0856 1.0000
11.000 1.1210 0.05082 0.04336 0.0065 0.0848 1.0000
11.250 1.1155 0.05423 0.04717 0.0092 0.0841 1.0000
11.500 1.1039 0.05780 0.05111 0.0120 0.0836 1.0000
11.750 1.0846 0.06140 0.05500 0.0152 0.0834 1.0000
12.000 1.0593 0.06544 0.05930 0.0177 0.0835 1.0000
12.250 1.0298 0.07040 0.06450 0.0184 0.0840 1.0000
12.500 0.9970 0.07656 0.07086 0.0171 0.0849 1.0000
12.750 0.9639 0.08402 0.07846 0.0139 0.0859 1.0000
13.000 0.9351 0.09232 0.08686 0.0098 0.0868 1.0000
13.250 0.9158 0.10047 0.09505 0.0063 0.0876 1.0000
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Polar data table (+)
Polar graphs
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