NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-209 (naca65209-il) Reynolds number: 50,000 Max Cl/Cd: 30.36 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65209-il-50000-n5.txt Download as CSV file: xf-naca65209-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-209
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5548 0.08274 0.07588 -0.0363 1.0000 0.0503
-8.500 -0.5592 0.07877 0.07193 -0.0373 1.0000 0.0493
-8.250 -0.5639 0.07463 0.06778 -0.0385 1.0000 0.0484
-8.000 -0.5686 0.07042 0.06351 -0.0395 1.0000 0.0475
-7.750 -0.5714 0.06633 0.05931 -0.0400 1.0000 0.0467
-7.500 -0.5719 0.06240 0.05521 -0.0402 1.0000 0.0464
-7.250 -0.5702 0.05863 0.05117 -0.0399 1.0000 0.0467
-7.000 -0.5663 0.05503 0.04730 -0.0393 1.0000 0.0475
-6.750 -0.5603 0.05158 0.04351 -0.0383 1.0000 0.0484
-6.500 -0.5520 0.04823 0.03978 -0.0370 1.0000 0.0489
-6.250 -0.5412 0.04501 0.03619 -0.0356 1.0000 0.0487
-6.000 -0.5283 0.04193 0.03269 -0.0342 1.0000 0.0486
-5.750 -0.5134 0.03910 0.02945 -0.0326 1.0000 0.0488
-5.500 -0.4967 0.03647 0.02637 -0.0311 1.0000 0.0492
-5.250 -0.4783 0.03430 0.02369 -0.0295 1.0000 0.0509
-5.000 -0.4600 0.03212 0.02124 -0.0282 1.0000 0.0540
-4.750 -0.4406 0.03031 0.01926 -0.0270 1.0000 0.0567
-4.500 -0.4195 0.02862 0.01728 -0.0255 1.0000 0.0583
-4.250 -0.3982 0.02717 0.01563 -0.0239 1.0000 0.0604
-4.000 -0.3773 0.02597 0.01423 -0.0221 1.0000 0.0631
-3.750 -0.3585 0.02489 0.01309 -0.0205 1.0000 0.0689
-3.500 -0.3401 0.02403 0.01211 -0.0189 1.0000 0.0758
-3.250 -0.3217 0.02310 0.01105 -0.0174 1.0000 0.0812
-3.000 -0.3030 0.02225 0.01005 -0.0162 1.0000 0.0893
-2.750 -0.2842 0.02137 0.00920 -0.0152 1.0000 0.1086
-2.500 -0.2665 0.01888 0.00815 -0.0153 1.0000 0.3219
-2.250 -0.2712 0.01800 0.00907 -0.0065 1.0000 0.7393
-2.000 -0.2692 0.01825 0.00944 0.0009 1.0000 0.8398
-1.750 -0.1649 0.01912 0.00975 -0.0080 1.0000 0.9733
-1.500 -0.1248 0.01898 0.00932 -0.0118 1.0000 0.9864
-1.250 -0.0922 0.01888 0.00899 -0.0144 1.0000 1.0000
-1.000 -0.0610 0.01888 0.00877 -0.0167 0.9906 1.0000
-0.750 -0.0296 0.01894 0.00866 -0.0190 0.9810 1.0000
-0.500 0.0006 0.01903 0.00861 -0.0209 0.9719 1.0000
-0.250 0.0320 0.01916 0.00862 -0.0230 0.9634 1.0000
0.000 0.0600 0.01929 0.00864 -0.0243 0.9542 1.0000
0.250 0.0873 0.01945 0.00872 -0.0253 0.9452 1.0000
0.500 0.1208 0.01967 0.00889 -0.0274 0.9381 1.0000
0.750 0.1460 0.01987 0.00905 -0.0279 0.9288 1.0000
1.000 0.1778 0.02012 0.00929 -0.0296 0.9215 1.0000
1.250 0.2068 0.02038 0.00956 -0.0306 0.9133 1.0000
1.500 0.2356 0.02066 0.00987 -0.0316 0.9053 1.0000
1.750 0.2686 0.02095 0.01026 -0.0333 0.8981 1.0000
2.000 0.2953 0.02128 0.01065 -0.0338 0.8893 1.0000
2.250 0.3309 0.02158 0.01108 -0.0357 0.8827 1.0000
2.500 0.3553 0.02193 0.01155 -0.0357 0.8729 1.0000
2.750 0.3855 0.02227 0.01209 -0.0366 0.8645 1.0000
3.000 0.4170 0.02257 0.01261 -0.0376 0.8557 1.0000
3.250 0.4434 0.02292 0.01317 -0.0377 0.8448 1.0000
3.500 0.4728 0.02322 0.01373 -0.0381 0.8339 1.0000
3.750 0.5047 0.02340 0.01430 -0.0386 0.8218 1.0000
4.000 0.5552 0.01983 0.01097 -0.0331 0.7212 1.0000
4.250 0.5708 0.01880 0.00951 -0.0264 0.5403 1.0000
4.500 0.5675 0.02174 0.00989 -0.0210 0.1558 1.0000
4.750 0.5808 0.02365 0.01140 -0.0193 0.1044 1.0000
5.000 0.5975 0.02511 0.01274 -0.0179 0.0853 1.0000
5.250 0.6167 0.02636 0.01409 -0.0167 0.0747 1.0000
5.500 0.6374 0.02781 0.01561 -0.0155 0.0695 1.0000
5.750 0.6640 0.02920 0.01723 -0.0148 0.0646 1.0000
6.000 0.6921 0.03100 0.01895 -0.0148 0.0580 1.0000
6.250 0.7233 0.03273 0.02109 -0.0146 0.0540 1.0000
6.500 0.7538 0.03501 0.02368 -0.0144 0.0520 1.0000
6.750 0.7810 0.03757 0.02659 -0.0139 0.0505 1.0000
7.000 0.8049 0.04038 0.02979 -0.0132 0.0493 1.0000
7.250 0.8252 0.04315 0.03281 -0.0126 0.0471 1.0000
7.500 0.8411 0.04657 0.03655 -0.0117 0.0447 1.0000
7.750 0.8544 0.04973 0.04031 -0.0101 0.0436 1.0000
8.000 0.8650 0.05338 0.04445 -0.0086 0.0434 1.0000
8.250 0.8721 0.05723 0.04882 -0.0071 0.0433 1.0000
8.500 0.8760 0.06119 0.05316 -0.0058 0.0434 1.0000
8.750 0.8765 0.06524 0.05755 -0.0045 0.0436 1.0000
9.000 0.8735 0.06937 0.06197 -0.0033 0.0438 1.0000
9.250 0.8679 0.07350 0.06633 -0.0024 0.0441 1.0000
9.500 0.8592 0.07761 0.07061 -0.0017 0.0443 1.0000
9.750 0.8466 0.08158 0.07470 -0.0011 0.0445 1.0000
10.000 0.8351 0.08584 0.07905 -0.0013 0.0448 1.0000
10.250 0.8231 0.09049 0.08378 -0.0025 0.0450 1.0000
10.500 0.8134 0.09558 0.08891 -0.0043 0.0453 1.0000
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Polar data table (+)
Polar graphs
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