NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-208 (naca64208-il) Reynolds number: 500,000 Max Cl/Cd: 60.71 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64208-il-500000-n5.txt Download as CSV file: xf-naca64208-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5861 0.08522 0.08300 -0.0145 1.0000 0.0052
-9.250 -0.5943 0.07855 0.07637 -0.0185 1.0000 0.0050
-9.000 -0.6010 0.07241 0.07027 -0.0231 1.0000 0.0049
-8.750 -0.6140 0.06560 0.06346 -0.0303 1.0000 0.0049
-8.500 -0.6266 0.05894 0.05670 -0.0346 1.0000 0.0049
-8.250 -0.6337 0.05238 0.04996 -0.0371 1.0000 0.0049
-8.000 -0.6422 0.04382 0.04109 -0.0385 1.0000 0.0049
-7.750 -0.6452 0.03518 0.03195 -0.0385 1.0000 0.0051
-7.500 -0.6352 0.02999 0.02637 -0.0378 1.0000 0.0053
-7.250 -0.6187 0.02708 0.02315 -0.0372 1.0000 0.0056
-7.000 -0.6032 0.02318 0.01881 -0.0361 1.0000 0.0061
-6.750 -0.5851 0.02022 0.01543 -0.0349 1.0000 0.0066
-6.500 -0.5644 0.01851 0.01344 -0.0340 1.0000 0.0073
-6.250 -0.5339 0.01732 0.01199 -0.0349 0.9958 0.0080
-6.000 -0.5041 0.01510 0.00943 -0.0359 0.9902 0.0088
-5.750 -0.4717 0.01429 0.00853 -0.0373 0.9851 0.0095
-5.500 -0.4398 0.01363 0.00778 -0.0385 0.9787 0.0104
-5.250 -0.4080 0.01292 0.00697 -0.0396 0.9718 0.0115
-5.000 -0.3751 0.01253 0.00648 -0.0409 0.9648 0.0128
-4.750 -0.3443 0.01196 0.00582 -0.0417 0.9556 0.0134
-4.500 -0.3152 0.01083 0.00457 -0.0423 0.9456 0.0148
-4.250 -0.2860 0.01036 0.00404 -0.0428 0.9350 0.0161
-4.000 -0.2580 0.01005 0.00368 -0.0429 0.9236 0.0179
-3.750 -0.2309 0.00968 0.00320 -0.0428 0.9119 0.0194
-3.500 -0.2040 0.00940 0.00283 -0.0426 0.9002 0.0211
-3.250 -0.1772 0.00909 0.00244 -0.0424 0.8887 0.0240
-3.000 -0.1503 0.00885 0.00216 -0.0422 0.8777 0.0293
-2.750 -0.1233 0.00870 0.00194 -0.0420 0.8670 0.0347
-2.500 -0.0964 0.00847 0.00172 -0.0419 0.8562 0.0521
-2.250 -0.0697 0.00805 0.00152 -0.0419 0.8453 0.1206
-2.000 -0.0440 0.00722 0.00127 -0.0421 0.8348 0.3009
-1.750 -0.0181 0.00657 0.00112 -0.0422 0.8248 0.4659
-1.500 0.0086 0.00629 0.00106 -0.0421 0.8146 0.5490
-1.250 0.0347 0.00601 0.00109 -0.0418 0.8041 0.6463
-1.000 0.0612 0.00589 0.00111 -0.0414 0.7939 0.6970
-0.750 0.0882 0.00586 0.00110 -0.0412 0.7842 0.7224
-0.500 0.1159 0.00585 0.00108 -0.0411 0.7741 0.7346
-0.250 0.1436 0.00586 0.00107 -0.0410 0.7640 0.7452
0.000 0.1712 0.00587 0.00107 -0.0409 0.7540 0.7559
0.250 0.1987 0.00589 0.00108 -0.0408 0.7442 0.7668
0.500 0.2264 0.00590 0.00111 -0.0407 0.7344 0.7778
0.750 0.2540 0.00592 0.00114 -0.0406 0.7247 0.7885
1.250 0.3080 0.00602 0.00122 -0.0402 0.6917 0.8112
1.500 0.3343 0.00612 0.00126 -0.0397 0.6639 0.8226
1.750 0.3601 0.00626 0.00131 -0.0393 0.6276 0.8339
2.000 0.3849 0.00652 0.00136 -0.0386 0.5671 0.8455
2.250 0.4096 0.00680 0.00148 -0.0380 0.5071 0.8578
2.500 0.4341 0.00715 0.00162 -0.0374 0.4375 0.8705
2.750 0.4534 0.00832 0.00201 -0.0364 0.2364 0.8844
3.000 0.4744 0.00923 0.00238 -0.0356 0.0997 0.8991
3.250 0.4979 0.00965 0.00264 -0.0348 0.0531 0.9148
3.500 0.5221 0.00989 0.00290 -0.0340 0.0380 0.9321
3.750 0.5477 0.01013 0.00315 -0.0336 0.0305 0.9524
4.000 0.5790 0.01039 0.00345 -0.0345 0.0248 0.9789
4.250 0.6075 0.01070 0.00378 -0.0349 0.0209 1.0000
4.500 0.6337 0.01116 0.00428 -0.0347 0.0179 1.0000
4.750 0.6592 0.01171 0.00490 -0.0344 0.0165 1.0000
5.000 0.6852 0.01216 0.00542 -0.0342 0.0158 1.0000
5.250 0.7106 0.01271 0.00603 -0.0339 0.0149 1.0000
5.500 0.7356 0.01331 0.00670 -0.0336 0.0140 1.0000
5.750 0.7611 0.01379 0.00723 -0.0334 0.0129 1.0000
6.000 0.7860 0.01438 0.00789 -0.0331 0.0121 1.0000
6.250 0.8103 0.01513 0.00870 -0.0326 0.0114 1.0000
6.500 0.8322 0.01644 0.01013 -0.0319 0.0105 1.0000
6.750 0.8561 0.01738 0.01118 -0.0314 0.0098 1.0000
7.000 0.8810 0.01796 0.01186 -0.0311 0.0092 1.0000
7.250 0.9047 0.01898 0.01303 -0.0306 0.0085 1.0000
7.500 0.9281 0.02002 0.01422 -0.0301 0.0079 1.0000
7.750 0.9513 0.02096 0.01532 -0.0296 0.0073 1.0000
8.000 0.9745 0.02176 0.01622 -0.0292 0.0069 1.0000
8.250 0.9963 0.02277 0.01735 -0.0287 0.0064 1.0000
8.500 1.0139 0.02519 0.02010 -0.0277 0.0059 1.0000
8.750 1.0341 0.02677 0.02196 -0.0269 0.0055 1.0000
9.000 1.0489 0.02969 0.02528 -0.0255 0.0050 1.0000
9.250 1.0514 0.03536 0.03159 -0.0231 0.0046 1.0000
9.500 1.0268 0.04658 0.04360 -0.0190 0.0043 1.0000
9.750 1.0089 0.05396 0.05136 -0.0167 0.0042 1.0000
10.000 0.9851 0.05990 0.05755 -0.0145 0.0041 1.0000
10.250 0.9557 0.06533 0.06314 -0.0134 0.0042 1.0000
10.500 0.9218 0.07285 0.07081 -0.0163 0.0043 1.0000
10.750 0.8882 0.08400 0.08207 -0.0246 0.0045 1.0000
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Polar data table (+)
Polar graphs
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