NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: NACA 65-210 (naca65210-il) Reynolds number: 100,000 Max Cl/Cd: 43.04 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65210-il-100000-n5.txt Download as CSV file: xf-naca65210-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-210
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4379 0.09166 0.08687 -0.0289 1.0000 0.0330
-10.000 -0.4450 0.08583 0.08108 -0.0314 1.0000 0.0317
-9.750 -0.4574 0.07865 0.07395 -0.0350 1.0000 0.0302
-9.250 -0.5724 0.07292 0.06783 -0.0452 1.0000 0.0272
-9.000 -0.5839 0.06904 0.06394 -0.0457 1.0000 0.0269
-8.750 -0.5945 0.06535 0.06018 -0.0455 1.0000 0.0267
-8.500 -0.6024 0.06144 0.05615 -0.0452 1.0000 0.0265
-8.250 -0.6075 0.05765 0.05221 -0.0444 1.0000 0.0263
-8.000 -0.6105 0.05390 0.04825 -0.0431 1.0000 0.0262
-7.750 -0.6110 0.05040 0.04451 -0.0415 1.0000 0.0262
-7.500 -0.6101 0.04705 0.04088 -0.0394 1.0000 0.0262
-7.250 -0.6073 0.04398 0.03743 -0.0370 1.0000 0.0266
-7.000 -0.6016 0.04196 0.03495 -0.0343 1.0000 0.0275
-6.750 -0.5995 0.03831 0.03107 -0.0320 1.0000 0.0287
-6.500 -0.5914 0.03607 0.02864 -0.0299 1.0000 0.0297
-6.250 -0.5809 0.03384 0.02611 -0.0277 1.0000 0.0301
-6.000 -0.5565 0.03124 0.02311 -0.0279 0.9963 0.0308
-5.750 -0.5253 0.02880 0.02027 -0.0293 0.9907 0.0319
-5.500 -0.4921 0.02705 0.01818 -0.0309 0.9858 0.0348
-5.250 -0.4600 0.02532 0.01607 -0.0318 0.9800 0.0369
-5.000 -0.4256 0.02365 0.01412 -0.0332 0.9758 0.0380
-4.750 -0.3940 0.02238 0.01265 -0.0339 0.9700 0.0392
-4.500 -0.3623 0.02074 0.01107 -0.0353 0.9655 0.0424
-4.250 -0.3312 0.01983 0.01011 -0.0364 0.9597 0.0470
-4.000 -0.2994 0.01893 0.00911 -0.0374 0.9542 0.0501
-3.750 -0.2675 0.01806 0.00815 -0.0387 0.9490 0.0542
-3.500 -0.2383 0.01747 0.00749 -0.0393 0.9418 0.0635
-3.250 -0.2055 0.01674 0.00675 -0.0407 0.9370 0.0803
-3.000 -0.1844 0.01504 0.00606 -0.0407 0.9286 0.2755
-2.750 -0.1674 0.01378 0.00647 -0.0382 0.9228 0.6616
-2.500 -0.1476 0.01402 0.00683 -0.0354 0.9145 0.7368
-2.250 -0.1254 0.01444 0.00731 -0.0323 0.9090 0.7883
-2.000 -0.1049 0.01468 0.00747 -0.0298 0.9010 0.8144
-1.750 -0.0745 0.01463 0.00727 -0.0302 0.8956 0.8245
-1.500 -0.0473 0.01461 0.00714 -0.0301 0.8888 0.8317
-1.250 -0.0182 0.01455 0.00696 -0.0304 0.8827 0.8398
-1.000 0.0105 0.01452 0.00684 -0.0305 0.8769 0.8470
-0.750 0.0374 0.01449 0.00675 -0.0304 0.8701 0.8549
-0.500 0.0681 0.01444 0.00664 -0.0310 0.8655 0.8621
-0.250 0.0931 0.01446 0.00662 -0.0305 0.8577 0.8702
0.000 0.1227 0.01443 0.00655 -0.0309 0.8526 0.8780
0.250 0.1492 0.01444 0.00657 -0.0307 0.8458 0.8858
0.500 0.1767 0.01444 0.00655 -0.0307 0.8398 0.8949
0.750 0.2065 0.01443 0.00657 -0.0311 0.8345 0.9021
1.000 0.2332 0.01447 0.00663 -0.0310 0.8275 0.9114
1.250 0.2648 0.01444 0.00665 -0.0318 0.8228 0.9195
1.500 0.2931 0.01451 0.00678 -0.0321 0.8155 0.9287
1.750 0.3239 0.01451 0.00684 -0.0328 0.8100 0.9382
2.000 0.3576 0.01455 0.00698 -0.0342 0.8037 0.9461
2.250 0.3912 0.01459 0.00714 -0.0355 0.7973 0.9547
2.500 0.4265 0.01461 0.00728 -0.0372 0.7915 0.9632
2.750 0.4626 0.01465 0.00748 -0.0391 0.7834 0.9712
3.000 0.4989 0.01462 0.00764 -0.0409 0.7739 0.9795
3.250 0.5327 0.01410 0.00717 -0.0409 0.7450 0.9879
3.500 0.5613 0.01338 0.00628 -0.0392 0.6716 0.9997
3.750 0.5737 0.01333 0.00604 -0.0356 0.6017 1.0000
4.000 0.5826 0.01381 0.00587 -0.0316 0.4477 1.0000
4.250 0.5793 0.01603 0.00654 -0.0271 0.1791 1.0000
4.500 0.5909 0.01757 0.00739 -0.0251 0.0784 1.0000
4.750 0.6102 0.01842 0.00821 -0.0238 0.0632 1.0000
5.000 0.6299 0.01927 0.00906 -0.0227 0.0544 1.0000
5.250 0.6499 0.02010 0.00993 -0.0217 0.0480 1.0000
5.500 0.6680 0.02122 0.01111 -0.0204 0.0450 1.0000
5.750 0.6884 0.02225 0.01225 -0.0193 0.0428 1.0000
6.000 0.7101 0.02333 0.01341 -0.0185 0.0398 1.0000
6.250 0.7324 0.02445 0.01454 -0.0179 0.0365 1.0000
6.500 0.7558 0.02609 0.01617 -0.0175 0.0345 1.0000
6.750 0.7822 0.02829 0.01848 -0.0174 0.0333 1.0000
7.000 0.8081 0.03006 0.02050 -0.0170 0.0325 1.0000
7.250 0.8331 0.03215 0.02288 -0.0165 0.0319 1.0000
7.500 0.8556 0.03433 0.02544 -0.0157 0.0308 1.0000
7.750 0.8755 0.03640 0.02789 -0.0147 0.0290 1.0000
8.000 0.8931 0.03886 0.03074 -0.0136 0.0277 1.0000
8.250 0.9077 0.04182 0.03415 -0.0121 0.0272 1.0000
8.500 0.9189 0.04505 0.03781 -0.0105 0.0269 1.0000
8.750 0.9260 0.04854 0.04172 -0.0086 0.0266 1.0000
9.000 0.9291 0.05219 0.04576 -0.0066 0.0265 1.0000
9.250 0.9306 0.05543 0.04929 -0.0049 0.0259 1.0000
9.500 0.9330 0.05807 0.05209 -0.0035 0.0250 1.0000
9.750 0.9320 0.06092 0.05509 -0.0021 0.0243 1.0000
10.000 0.9231 0.06425 0.05855 -0.0004 0.0237 1.0000
10.250 0.9086 0.06780 0.06228 0.0015 0.0235 1.0000
10.500 0.8926 0.07154 0.06620 0.0024 0.0235 1.0000
10.750 0.8746 0.07584 0.07067 0.0022 0.0235 1.0000
11.000 0.8559 0.08074 0.07572 0.0007 0.0235 1.0000
11.250 0.8344 0.08690 0.08206 -0.0028 0.0239 1.0000
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Polar data table (+)
Polar graphs
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