NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66-209 (naca66209-il) Reynolds number: 100,000 Max Cl/Cd: 40.56 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66209-il-100000-n5.txt Download as CSV file: xf-naca66209-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-209
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5180 0.09237 0.08741 -0.0376 1.0000 0.0425
-9.250 -0.5113 0.08857 0.08358 -0.0368 1.0000 0.0350
-8.750 -0.5346 0.07603 0.07107 -0.0466 1.0000 0.0263
-8.500 -0.5462 0.07272 0.06778 -0.0460 1.0000 0.0259
-8.250 -0.5571 0.06925 0.06433 -0.0451 1.0000 0.0257
-8.000 -0.5664 0.06616 0.06117 -0.0434 1.0000 0.0252
-7.750 -0.5765 0.06311 0.05805 -0.0411 1.0000 0.0249
-7.500 -0.5858 0.06027 0.05513 -0.0382 1.0000 0.0247
-7.250 -0.5936 0.05748 0.05220 -0.0351 1.0000 0.0250
-7.000 -0.5991 0.05457 0.04905 -0.0319 1.0000 0.0258
-6.750 -0.6006 0.05179 0.04608 -0.0290 1.0000 0.0258
-6.500 -0.5846 0.04836 0.04216 -0.0289 0.9963 0.0270
-6.250 -0.5653 0.04395 0.03735 -0.0299 0.9913 0.0268
-6.000 -0.5430 0.03985 0.03276 -0.0307 0.9869 0.0267
-5.750 -0.5201 0.03651 0.02890 -0.0309 0.9824 0.0269
-5.500 -0.4942 0.03386 0.02569 -0.0311 0.9785 0.0275
-5.250 -0.4699 0.03020 0.02167 -0.0319 0.9756 0.0297
-5.000 -0.4452 0.02845 0.01969 -0.0321 0.9713 0.0322
-4.750 -0.4160 0.02637 0.01717 -0.0324 0.9682 0.0329
-4.500 -0.3850 0.02458 0.01507 -0.0329 0.9659 0.0341
-4.250 -0.3564 0.02315 0.01341 -0.0330 0.9630 0.0355
-4.000 -0.3298 0.02226 0.01231 -0.0329 0.9593 0.0393
-3.750 -0.3014 0.02107 0.01103 -0.0331 0.9564 0.0414
-3.500 -0.2730 0.01987 0.00981 -0.0336 0.9538 0.0439
-3.250 -0.2450 0.01908 0.00896 -0.0340 0.9508 0.0475
-3.000 -0.2220 0.01859 0.00834 -0.0333 0.9462 0.0528
-2.750 -0.1953 0.01801 0.00774 -0.0335 0.9429 0.0631
-2.500 -0.1658 0.01747 0.00717 -0.0341 0.9403 0.0783
-2.250 -0.1576 0.01465 0.00711 -0.0312 0.9371 0.6341
-2.000 -0.1502 0.01502 0.00785 -0.0248 0.9313 0.8097
-1.750 -0.1321 0.01550 0.00828 -0.0210 0.9279 0.8643
-1.500 -0.1044 0.01601 0.00869 -0.0189 0.9262 0.9059
-1.250 -0.0570 0.01639 0.00890 -0.0216 0.9265 0.9348
-1.000 -0.0204 0.01639 0.00874 -0.0238 0.9247 0.9404
-0.750 0.0101 0.01640 0.00865 -0.0249 0.9209 0.9453
-0.500 0.0389 0.01641 0.00858 -0.0257 0.9172 0.9507
-0.250 0.0734 0.01642 0.00851 -0.0276 0.9146 0.9543
0.000 0.1112 0.01643 0.00847 -0.0302 0.9125 0.9568
0.250 0.1490 0.01644 0.00846 -0.0327 0.9108 0.9598
0.500 0.1735 0.01652 0.00855 -0.0327 0.9052 0.9658
0.750 0.2101 0.01655 0.00859 -0.0351 0.9019 0.9683
1.000 0.2484 0.01656 0.00863 -0.0377 0.8990 0.9710
1.250 0.2849 0.01657 0.00873 -0.0399 0.8959 0.9743
1.500 0.3152 0.01666 0.00890 -0.0410 0.8900 0.9789
1.750 0.3518 0.01666 0.00901 -0.0432 0.8861 0.9818
2.000 0.3907 0.01662 0.00910 -0.0457 0.8829 0.9842
2.250 0.4205 0.01670 0.00937 -0.0467 0.8751 0.9896
2.500 0.4598 0.01642 0.00927 -0.0486 0.8664 0.9916
2.750 0.5007 0.01479 0.00774 -0.0476 0.8266 0.9902
3.000 0.5263 0.01380 0.00681 -0.0449 0.7650 0.9945
3.250 0.5475 0.01350 0.00556 -0.0410 0.5175 0.9983
3.500 0.5384 0.01589 0.00612 -0.0350 0.1768 1.0000
3.750 0.5436 0.01719 0.00673 -0.0315 0.0748 1.0000
4.000 0.5553 0.01785 0.00734 -0.0287 0.0608 1.0000
4.250 0.5683 0.01840 0.00799 -0.0260 0.0545 1.0000
4.500 0.5799 0.01916 0.00874 -0.0233 0.0479 1.0000
4.750 0.5955 0.01979 0.00953 -0.0212 0.0434 1.0000
5.000 0.6118 0.02066 0.01047 -0.0193 0.0407 1.0000
5.250 0.6301 0.02171 0.01156 -0.0178 0.0385 1.0000
5.500 0.6512 0.02302 0.01287 -0.0168 0.0367 1.0000
5.750 0.6768 0.02510 0.01496 -0.0166 0.0351 1.0000
6.000 0.7024 0.02641 0.01648 -0.0161 0.0331 1.0000
6.250 0.7278 0.02789 0.01827 -0.0156 0.0309 1.0000
6.500 0.7532 0.02998 0.02066 -0.0151 0.0298 1.0000
6.750 0.7765 0.03231 0.02337 -0.0142 0.0291 1.0000
7.000 0.7971 0.03494 0.02641 -0.0129 0.0286 1.0000
7.250 0.8149 0.03775 0.02967 -0.0114 0.0281 1.0000
7.500 0.8305 0.04003 0.03224 -0.0100 0.0262 1.0000
7.750 0.8444 0.04223 0.03462 -0.0090 0.0245 1.0000
8.000 0.8535 0.04568 0.03837 -0.0073 0.0237 1.0000
8.250 0.8596 0.04949 0.04261 -0.0053 0.0235 1.0000
8.500 0.8629 0.05331 0.04680 -0.0032 0.0234 1.0000
8.750 0.8641 0.05700 0.05082 -0.0010 0.0234 1.0000
9.000 0.8623 0.06065 0.05478 0.0012 0.0235 1.0000
9.250 0.8572 0.06425 0.05867 0.0034 0.0237 1.0000
9.500 0.8472 0.06781 0.06248 0.0058 0.0241 1.0000
9.750 0.8255 0.07199 0.06693 0.0082 0.0247 1.0000
10.000 0.8006 0.07730 0.07244 0.0083 0.0255 1.0000
10.250 0.7785 0.08335 0.07861 0.0060 0.0262 1.0000
10.500 0.7590 0.09069 0.08597 0.0013 0.0269 1.0000
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Polar data table (+)
Polar graphs
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