NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-410 (naca65410-il) Reynolds number: 200,000 Max Cl/Cd: 68.73 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65410-il-200000-n5.txt Download as CSV file: xf-naca65410-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4400 0.08851 0.08489 -0.0429 1.0000 0.0146
-9.250 -0.4436 0.08428 0.08071 -0.0447 1.0000 0.0146
-9.000 -0.4500 0.07960 0.07610 -0.0469 1.0000 0.0149
-8.750 -0.4571 0.07562 0.07218 -0.0485 1.0000 0.0144
-8.500 -0.4727 0.07105 0.06770 -0.0508 1.0000 0.0144
-8.250 -0.4962 0.06817 0.06487 -0.0499 1.0000 0.0141
-8.000 -0.4969 0.06210 0.05870 -0.0555 0.9940 0.0138
-7.750 -0.4842 0.05453 0.05085 -0.0629 0.9851 0.0148
-7.500 -0.4693 0.04743 0.04335 -0.0677 0.9770 0.0153
-7.250 -0.4527 0.04175 0.03728 -0.0706 0.9692 0.0153
-7.000 -0.4298 0.03597 0.03097 -0.0734 0.9645 0.0154
-6.750 -0.4096 0.03135 0.02574 -0.0742 0.9564 0.0158
-6.500 -0.3832 0.02733 0.02118 -0.0759 0.9520 0.0165
-6.250 -0.3578 0.02621 0.01995 -0.0766 0.9452 0.0177
-6.000 -0.3282 0.02484 0.01835 -0.0778 0.9402 0.0195
-5.750 -0.2987 0.02255 0.01562 -0.0786 0.9355 0.0206
-5.500 -0.2712 0.02079 0.01350 -0.0786 0.9289 0.0216
-5.250 -0.2399 0.01969 0.01209 -0.0794 0.9244 0.0229
-5.000 -0.2139 0.01805 0.01036 -0.0795 0.9179 0.0252
-4.750 -0.1853 0.01704 0.00923 -0.0798 0.9122 0.0265
-4.500 -0.1568 0.01614 0.00823 -0.0801 0.9066 0.0280
-4.250 -0.1301 0.01543 0.00744 -0.0800 0.8997 0.0301
-3.750 -0.0756 0.01419 0.00605 -0.0800 0.8870 0.0337
-3.500 -0.0484 0.01339 0.00518 -0.0802 0.8814 0.0365
-3.250 -0.0220 0.01296 0.00470 -0.0802 0.8742 0.0398
-3.000 0.0060 0.01264 0.00428 -0.0803 0.8682 0.0451
-2.750 0.0331 0.01225 0.00386 -0.0803 0.8616 0.0523
-2.500 0.0605 0.01187 0.00350 -0.0804 0.8553 0.0735
-2.250 0.0837 0.01001 0.00312 -0.0812 0.8492 0.4573
-2.000 0.1067 0.00957 0.00333 -0.0801 0.8424 0.6485
-1.750 0.1314 0.00957 0.00346 -0.0789 0.8370 0.7159
-1.500 0.1558 0.00963 0.00356 -0.0778 0.8301 0.7509
-1.250 0.1815 0.00967 0.00358 -0.0770 0.8247 0.7712
-1.000 0.2085 0.00969 0.00354 -0.0768 0.8183 0.7825
-0.750 0.2355 0.00968 0.00349 -0.0766 0.8123 0.7888
-0.250 0.2902 0.00970 0.00343 -0.0764 0.8007 0.8027
0.000 0.3184 0.00972 0.00339 -0.0765 0.7955 0.8103
0.250 0.3447 0.00974 0.00343 -0.0762 0.7892 0.8167
0.500 0.3723 0.00977 0.00344 -0.0761 0.7835 0.8246
0.750 0.3990 0.00979 0.00347 -0.0758 0.7782 0.8311
1.000 0.4260 0.00984 0.00354 -0.0757 0.7719 0.8393
1.250 0.4524 0.00986 0.00358 -0.0754 0.7667 0.8463
1.500 0.4791 0.00992 0.00368 -0.0752 0.7604 0.8546
1.750 0.5048 0.00996 0.00376 -0.0747 0.7546 0.8620
2.000 0.5312 0.01001 0.00387 -0.0744 0.7491 0.8707
2.250 0.5564 0.01006 0.00400 -0.0738 0.7425 0.8795
2.500 0.5824 0.01010 0.00408 -0.0733 0.7367 0.8881
2.750 0.6071 0.01012 0.00418 -0.0725 0.7251 0.8982
3.000 0.6311 0.01009 0.00416 -0.0714 0.7089 0.9088
3.250 0.6537 0.01005 0.00413 -0.0701 0.6848 0.9204
3.500 0.6760 0.01003 0.00404 -0.0685 0.6500 0.9333
3.750 0.6969 0.01014 0.00398 -0.0668 0.5871 0.9488
4.000 0.7174 0.01068 0.00401 -0.0654 0.4686 0.9696
4.250 0.7287 0.01229 0.00463 -0.0634 0.2790 1.0000
4.500 0.7399 0.01397 0.00547 -0.0615 0.1196 1.0000
4.750 0.7580 0.01507 0.00619 -0.0604 0.0550 1.0000
5.000 0.7807 0.01572 0.00684 -0.0599 0.0434 1.0000
5.250 0.8030 0.01639 0.00751 -0.0593 0.0366 1.0000
5.500 0.8250 0.01707 0.00825 -0.0586 0.0326 1.0000
5.750 0.8467 0.01775 0.00903 -0.0578 0.0302 1.0000
6.000 0.8673 0.01853 0.00987 -0.0569 0.0281 1.0000
6.250 0.8867 0.01943 0.01085 -0.0558 0.0264 1.0000
6.500 0.9042 0.02062 0.01206 -0.0544 0.0251 1.0000
6.750 0.9225 0.02201 0.01350 -0.0532 0.0238 1.0000
7.000 0.9449 0.02282 0.01441 -0.0526 0.0227 1.0000
7.250 0.9671 0.02389 0.01558 -0.0519 0.0215 1.0000
7.500 0.9901 0.02518 0.01701 -0.0514 0.0207 1.0000
7.750 1.0139 0.02660 0.01856 -0.0509 0.0199 1.0000
8.000 1.0377 0.02815 0.02026 -0.0506 0.0192 1.0000
8.250 1.0608 0.02981 0.02210 -0.0501 0.0186 1.0000
8.500 1.0815 0.03125 0.02367 -0.0495 0.0177 1.0000
8.750 1.1009 0.03349 0.02602 -0.0490 0.0167 1.0000
9.000 1.1181 0.03588 0.02877 -0.0479 0.0161 1.0000
9.250 1.1331 0.03825 0.03152 -0.0464 0.0157 1.0000
9.500 1.1441 0.04109 0.03477 -0.0444 0.0153 1.0000
9.750 1.1503 0.04427 0.03837 -0.0421 0.0149 1.0000
10.000 1.1524 0.04742 0.04191 -0.0394 0.0143 1.0000
10.250 1.1503 0.05025 0.04504 -0.0365 0.0137 1.0000
10.500 1.1457 0.05259 0.04761 -0.0334 0.0132 1.0000
10.750 1.1369 0.05541 0.05067 -0.0305 0.0129 1.0000
11.000 1.1276 0.05819 0.05364 -0.0283 0.0126 1.0000
11.250 1.1133 0.06182 0.05751 -0.0264 0.0125 1.0000
11.500 1.0963 0.06603 0.06194 -0.0253 0.0124 1.0000
11.750 1.0759 0.07105 0.06719 -0.0252 0.0124 1.0000
12.000 1.0529 0.07694 0.07329 -0.0264 0.0124 1.0000
12.250 1.0239 0.08465 0.08123 -0.0293 0.0126 1.0000
12.500 0.9907 0.09463 0.09141 -0.0348 0.0128 1.0000
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Polar data table (+)
Polar graphs
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