NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-208 (naca64208-il) Reynolds number: 200,000 Max Cl/Cd: 53.3 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64208-il-200000-n5.txt Download as CSV file: xf-naca64208-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-208
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5613 0.08516 0.08164 -0.0162 1.0000 0.0117
-8.750 -0.5645 0.08001 0.07654 -0.0197 1.0000 0.0116
-8.500 -0.5703 0.07420 0.07078 -0.0245 1.0000 0.0116
-8.250 -0.5797 0.06857 0.06516 -0.0299 1.0000 0.0114
-8.000 -0.5845 0.06294 0.05944 -0.0335 1.0000 0.0113
-7.750 -0.5856 0.05763 0.05399 -0.0359 1.0000 0.0114
-7.500 -0.5828 0.05251 0.04868 -0.0373 1.0000 0.0115
-7.250 -0.5751 0.04715 0.04301 -0.0379 1.0000 0.0125
-7.000 -0.5642 0.04250 0.03801 -0.0378 1.0000 0.0130
-6.750 -0.5532 0.03805 0.03319 -0.0374 1.0000 0.0131
-6.500 -0.5400 0.03393 0.02865 -0.0366 1.0000 0.0131
-6.000 -0.5097 0.02602 0.01976 -0.0347 1.0000 0.0138
-5.750 -0.4908 0.02367 0.01712 -0.0338 1.0000 0.0145
-5.500 -0.4703 0.02244 0.01570 -0.0329 1.0000 0.0157
-5.250 -0.4494 0.02150 0.01460 -0.0320 1.0000 0.0177
-5.000 -0.4283 0.01987 0.01269 -0.0308 1.0000 0.0189
-4.750 -0.4004 0.01826 0.01078 -0.0309 0.9974 0.0200
-4.500 -0.3665 0.01706 0.00936 -0.0322 0.9920 0.0213
-4.250 -0.3337 0.01553 0.00774 -0.0337 0.9868 0.0241
-4.000 -0.3008 0.01451 0.00666 -0.0350 0.9806 0.0258
-3.750 -0.2667 0.01365 0.00574 -0.0366 0.9751 0.0282
-3.500 -0.2339 0.01297 0.00493 -0.0379 0.9676 0.0314
-3.250 -0.2009 0.01234 0.00423 -0.0393 0.9602 0.0373
-3.000 -0.1670 0.01188 0.00370 -0.0407 0.9531 0.0461
-2.750 -0.1353 0.01133 0.00323 -0.0418 0.9442 0.0696
-2.500 -0.1054 0.00993 0.00272 -0.0434 0.9360 0.2974
-2.250 -0.0782 0.00895 0.00261 -0.0438 0.9264 0.5372
-2.000 -0.0519 0.00861 0.00268 -0.0432 0.9163 0.6520
-1.750 -0.0272 0.00848 0.00281 -0.0419 0.9062 0.7341
-1.500 -0.0007 0.00844 0.00279 -0.0411 0.8964 0.7709
-1.000 0.0534 0.00838 0.00265 -0.0404 0.8750 0.7969
-0.750 0.0802 0.00836 0.00259 -0.0399 0.8647 0.8082
-0.500 0.1068 0.00834 0.00253 -0.0395 0.8547 0.8200
-0.250 0.1331 0.00833 0.00250 -0.0390 0.8440 0.8319
0.000 0.1591 0.00833 0.00248 -0.0384 0.8334 0.8442
0.250 0.1851 0.00833 0.00248 -0.0378 0.8232 0.8568
0.750 0.2364 0.00835 0.00250 -0.0364 0.8028 0.8828
1.000 0.2622 0.00835 0.00253 -0.0358 0.7924 0.8966
1.250 0.2884 0.00837 0.00256 -0.0353 0.7827 0.9113
1.500 0.3155 0.00838 0.00262 -0.0349 0.7728 0.9264
1.750 0.3446 0.00839 0.00267 -0.0351 0.7620 0.9421
2.000 0.3762 0.00841 0.00273 -0.0358 0.7494 0.9584
2.500 0.4383 0.00852 0.00266 -0.0367 0.6740 1.0000
2.750 0.4606 0.00880 0.00263 -0.0354 0.5985 1.0000
3.000 0.4850 0.00910 0.00274 -0.0347 0.5419 1.0000
3.250 0.5058 0.00980 0.00291 -0.0336 0.4096 1.0000
3.500 0.5206 0.01167 0.00357 -0.0324 0.1527 1.0000
3.750 0.5425 0.01275 0.00416 -0.0319 0.0598 1.0000
4.000 0.5674 0.01335 0.00470 -0.0316 0.0428 1.0000
4.250 0.5925 0.01395 0.00537 -0.0313 0.0361 1.0000
4.500 0.6173 0.01459 0.00609 -0.0309 0.0319 1.0000
4.750 0.6399 0.01558 0.00715 -0.0303 0.0274 1.0000
5.000 0.6644 0.01627 0.00792 -0.0298 0.0253 1.0000
5.250 0.6881 0.01717 0.00892 -0.0292 0.0237 1.0000
5.500 0.7118 0.01823 0.01007 -0.0286 0.0223 1.0000
5.750 0.7357 0.01944 0.01137 -0.0280 0.0211 1.0000
6.000 0.7599 0.02076 0.01281 -0.0274 0.0201 1.0000
6.250 0.7839 0.02189 0.01406 -0.0270 0.0184 1.0000
6.500 0.8060 0.02446 0.01682 -0.0264 0.0167 1.0000
6.750 0.8299 0.02613 0.01879 -0.0257 0.0162 1.0000
7.000 0.8524 0.02839 0.02143 -0.0249 0.0155 1.0000
7.250 0.8731 0.03091 0.02438 -0.0238 0.0145 1.0000
7.500 0.8930 0.03290 0.02671 -0.0230 0.0129 1.0000
7.750 0.9104 0.03530 0.02943 -0.0220 0.0120 1.0000
8.000 0.9244 0.03834 0.03284 -0.0208 0.0115 1.0000
8.250 0.9356 0.04149 0.03638 -0.0196 0.0111 1.0000
8.500 0.9421 0.04520 0.04045 -0.0182 0.0108 1.0000
8.750 0.9433 0.04942 0.04501 -0.0168 0.0106 1.0000
9.000 0.9386 0.05407 0.04999 -0.0153 0.0105 1.0000
9.250 0.9296 0.05875 0.05495 -0.0139 0.0105 1.0000
9.500 0.9144 0.06311 0.05952 -0.0123 0.0106 1.0000
9.750 0.8959 0.06780 0.06438 -0.0121 0.0107 1.0000
10.000 0.8744 0.07406 0.07080 -0.0144 0.0108 1.0000
10.250 0.8437 0.08548 0.08232 -0.0220 0.0114 1.0000
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Polar data table (+)
Polar graphs
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