NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NACA 65(1)-412 (naca651412-il) Reynolds number: 50,000 Max Cl/Cd: 28.28 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651412-il-50000.txt Download as CSV file: xf-naca651412-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4057 0.12005 0.11281 -0.0311 1.0000 0.2626
-10.250 -0.4127 0.11846 0.11130 -0.0312 1.0000 0.2753
-10.000 -0.4073 0.11537 0.10825 -0.0304 1.0000 0.2902
-9.750 -0.4068 0.11281 0.10576 -0.0297 1.0000 0.3055
-9.500 -0.3812 0.10789 0.10081 -0.0281 1.0000 0.3246
-9.250 -0.3736 0.10490 0.09787 -0.0270 1.0000 0.3415
-9.000 -0.3681 0.10215 0.09517 -0.0258 1.0000 0.3585
-8.750 -0.3665 0.09981 0.09289 -0.0244 1.0000 0.3768
-8.500 -0.3837 0.09909 0.09232 -0.0223 1.0000 0.3955
-8.000 -0.3493 0.09182 0.08506 -0.0195 1.0000 0.4333
-7.750 -0.3627 0.09098 0.08437 -0.0163 1.0000 0.4556
-7.500 -0.3402 0.08708 0.08045 -0.0152 1.0000 0.4756
-5.750 -0.5880 0.05337 0.04607 -0.0341 1.0000 0.1721
-5.500 -0.5694 0.04895 0.04118 -0.0343 1.0000 0.1526
-5.250 -0.5492 0.04519 0.03663 -0.0346 1.0000 0.1392
-5.000 -0.5289 0.04199 0.03305 -0.0344 1.0000 0.1336
-4.750 -0.5067 0.03941 0.02995 -0.0342 1.0000 0.1318
-4.500 -0.4840 0.03724 0.02736 -0.0338 1.0000 0.1320
-4.250 -0.4602 0.03527 0.02495 -0.0333 1.0000 0.1313
-4.000 -0.4366 0.03359 0.02292 -0.0325 1.0000 0.1312
-3.750 -0.4139 0.03217 0.02125 -0.0316 1.0000 0.1336
-3.500 -0.3917 0.03113 0.01996 -0.0305 1.0000 0.1398
-3.250 -0.3709 0.02997 0.01884 -0.0290 1.0000 0.1460
-3.000 -0.3505 0.02915 0.01796 -0.0273 1.0000 0.1528
-2.750 -0.3308 0.02830 0.01713 -0.0258 1.0000 0.1643
-2.500 -0.3103 0.02748 0.01633 -0.0249 1.0000 0.1857
-2.250 -0.1479 0.02880 0.02034 -0.0268 1.0000 1.0000
-2.000 -0.1499 0.02853 0.01992 -0.0240 1.0000 1.0000
-1.750 -0.1520 0.02824 0.01950 -0.0211 1.0000 1.0000
-1.500 -0.1542 0.02791 0.01905 -0.0182 1.0000 1.0000
-1.250 -0.1567 0.02756 0.01858 -0.0153 1.0000 1.0000
-1.000 -0.1591 0.02717 0.01808 -0.0123 1.0000 1.0000
-0.750 -0.1611 0.02676 0.01756 -0.0094 1.0000 1.0000
-0.500 -0.1615 0.02636 0.01704 -0.0066 1.0000 1.0000
-0.250 -0.1562 0.02611 0.01665 -0.0049 1.0000 1.0000
0.000 -0.1434 0.02610 0.01647 -0.0044 1.0000 1.0000
0.250 -0.1257 0.02628 0.01648 -0.0046 1.0000 1.0000
0.500 -0.1054 0.02660 0.01663 -0.0053 1.0000 1.0000
0.750 -0.0838 0.02703 0.01688 -0.0062 1.0000 1.0000
1.000 -0.0616 0.02753 0.01723 -0.0071 1.0000 1.0000
1.250 -0.0392 0.02809 0.01766 -0.0080 1.0000 1.0000
1.500 -0.0168 0.02872 0.01817 -0.0089 1.0000 1.0000
1.750 0.0053 0.02938 0.01872 -0.0097 1.0000 1.0000
2.000 0.0270 0.03010 0.01935 -0.0105 1.0000 1.0000
2.250 0.0485 0.03086 0.02004 -0.0112 1.0000 1.0000
2.500 0.0696 0.03166 0.02079 -0.0119 1.0000 1.0000
2.750 0.0904 0.03251 0.02159 -0.0126 1.0000 1.0000
3.000 0.1107 0.03340 0.02245 -0.0132 1.0000 1.0000
3.250 0.1308 0.03434 0.02338 -0.0138 1.0000 1.0000
3.500 0.1504 0.03533 0.02437 -0.0144 1.0000 1.0000
3.750 0.1696 0.03636 0.02542 -0.0150 1.0000 1.0000
4.000 0.1886 0.03746 0.02654 -0.0156 1.0000 1.0000
4.250 0.2070 0.03860 0.02772 -0.0161 1.0000 1.0000
4.500 0.2250 0.03981 0.02898 -0.0167 1.0000 1.0000
4.750 0.2426 0.04109 0.03033 -0.0174 1.0000 1.0000
5.000 0.2597 0.04244 0.03176 -0.0180 1.0000 1.0000
5.250 0.2764 0.04387 0.03327 -0.0187 1.0000 1.0000
5.500 0.2925 0.04538 0.03488 -0.0194 1.0000 1.0000
5.750 0.4974 0.05046 0.04069 -0.0463 0.8339 1.0000
6.000 0.5298 0.05158 0.04204 -0.0477 0.8108 1.0000
6.250 0.5659 0.05260 0.04333 -0.0493 0.7858 1.0000
6.500 0.6097 0.05323 0.04433 -0.0511 0.7583 1.0000
6.750 0.6595 0.05275 0.04428 -0.0520 0.7233 1.0000
7.000 0.8225 0.02908 0.01911 -0.0301 0.2324 1.0000
7.250 0.8204 0.03184 0.02119 -0.0267 0.1833 1.0000
7.500 0.8413 0.03388 0.02294 -0.0251 0.1551 1.0000
7.750 0.9190 0.03635 0.02521 -0.0298 0.1275 1.0000
8.000 0.9822 0.03959 0.02850 -0.0337 0.1160 1.0000
8.250 1.0202 0.04252 0.03166 -0.0348 0.1099 1.0000
8.500 1.0545 0.04612 0.03551 -0.0355 0.1080 1.0000
8.750 1.0804 0.04988 0.03962 -0.0352 0.1073 1.0000
9.000 1.0992 0.05395 0.04402 -0.0343 0.1063 1.0000
9.250 1.1087 0.05728 0.04786 -0.0322 0.1058 1.0000
9.500 1.1190 0.06129 0.05228 -0.0306 0.1061 1.0000
9.750 1.1108 0.06417 0.05591 -0.0267 0.1087 1.0000
10.000 1.0938 0.06828 0.06060 -0.0230 0.1124 1.0000
10.250 1.0815 0.07268 0.06539 -0.0206 0.1155 1.0000
10.500 1.0815 0.07781 0.07069 -0.0195 0.1187 1.0000
10.750 1.0582 0.08150 0.07467 -0.0167 0.1221 1.0000
11.000 1.0112 0.08572 0.07911 -0.0148 0.1239 1.0000
11.250 0.9667 0.09185 0.08541 -0.0160 0.1261 1.0000
11.500 0.9325 0.09953 0.09315 -0.0192 0.1300 1.0000
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Polar data table (+)
Polar graphs
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