NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-210 (naca64210-il) Reynolds number: 50,000 Max Cl/Cd: 32.19 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64210-il-50000-n5.txt Download as CSV file: xf-naca64210-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-210
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5569 0.09848 0.09133 -0.0223 1.0000 0.0524
-9.750 -0.5592 0.09323 0.08613 -0.0253 1.0000 0.0518
-9.500 -0.5643 0.08737 0.08032 -0.0293 1.0000 0.0514
-9.250 -0.5723 0.08163 0.07462 -0.0334 1.0000 0.0506
-9.000 -0.5847 0.07644 0.06945 -0.0368 1.0000 0.0500
-8.750 -0.5984 0.07200 0.06499 -0.0387 1.0000 0.0494
-8.500 -0.6084 0.06759 0.06047 -0.0400 1.0000 0.0493
-8.250 -0.6147 0.06340 0.05612 -0.0408 1.0000 0.0495
-8.000 -0.6169 0.05941 0.05189 -0.0410 1.0000 0.0500
-7.750 -0.6157 0.05555 0.04773 -0.0409 1.0000 0.0506
-7.500 -0.6111 0.05180 0.04361 -0.0404 1.0000 0.0512
-7.250 -0.6029 0.04822 0.03965 -0.0396 1.0000 0.0513
-7.000 -0.5918 0.04485 0.03587 -0.0387 1.0000 0.0514
-6.750 -0.5782 0.04175 0.03234 -0.0376 1.0000 0.0518
-6.500 -0.5625 0.03891 0.02902 -0.0364 1.0000 0.0524
-6.250 -0.5451 0.03649 0.02609 -0.0350 1.0000 0.0542
-6.000 -0.5272 0.03422 0.02358 -0.0339 1.0000 0.0569
-5.750 -0.5081 0.03236 0.02158 -0.0328 1.0000 0.0597
-5.500 -0.4875 0.03058 0.01959 -0.0314 1.0000 0.0617
-5.250 -0.4664 0.02899 0.01780 -0.0299 1.0000 0.0642
-5.000 -0.4458 0.02776 0.01630 -0.0283 1.0000 0.0686
-4.750 -0.4279 0.02653 0.01514 -0.0267 1.0000 0.0742
-4.500 -0.4097 0.02551 0.01399 -0.0248 1.0000 0.0793
-4.250 -0.3931 0.02449 0.01290 -0.0230 1.0000 0.0848
-4.000 -0.3766 0.02365 0.01199 -0.0214 1.0000 0.0960
-3.750 -0.3601 0.02265 0.01096 -0.0200 1.0000 0.1096
-3.500 -0.3428 0.02148 0.00995 -0.0191 1.0000 0.1342
-3.250 -0.3301 0.01887 0.00900 -0.0185 1.0000 0.3639
-3.000 -0.3224 0.01845 0.00949 -0.0137 1.0000 0.6063
-2.750 -0.3143 0.01872 0.00997 -0.0086 0.9994 0.7017
-2.500 -0.3029 0.01961 0.01110 -0.0015 0.9879 0.8014
-2.250 -0.2806 0.02010 0.01146 0.0021 0.9786 0.8540
-2.000 -0.2434 0.02008 0.01114 0.0001 0.9701 0.8701
-1.750 -0.2029 0.02006 0.01085 -0.0028 0.9623 0.8840
-1.500 -0.1643 0.02001 0.01055 -0.0055 0.9536 0.8972
-1.250 -0.1230 0.01998 0.01032 -0.0087 0.9459 0.9103
-1.000 -0.0797 0.01997 0.01013 -0.0123 0.9383 0.9231
-0.750 -0.0333 0.01996 0.00996 -0.0166 0.9313 0.9348
-0.500 0.0153 0.01995 0.00983 -0.0213 0.9245 0.9458
-0.250 0.0654 0.01994 0.00972 -0.0264 0.9181 0.9567
0.000 0.1144 0.01993 0.00965 -0.0313 0.9108 0.9678
0.250 0.1658 0.01990 0.00959 -0.0367 0.9045 0.9782
0.500 0.2131 0.01988 0.00958 -0.0414 0.8963 0.9905
0.750 0.2514 0.01992 0.00963 -0.0444 0.8875 1.0000
1.000 0.2782 0.02000 0.00972 -0.0450 0.8778 1.0000
1.250 0.2956 0.02018 0.00994 -0.0440 0.8657 1.0000
1.500 0.3139 0.02041 0.01018 -0.0430 0.8544 1.0000
1.750 0.3368 0.02063 0.01043 -0.0427 0.8448 1.0000
2.000 0.3618 0.02088 0.01073 -0.0428 0.8356 1.0000
2.250 0.3831 0.02121 0.01114 -0.0422 0.8250 1.0000
2.500 0.4101 0.02149 0.01151 -0.0424 0.8163 1.0000
2.750 0.4363 0.02179 0.01191 -0.0424 0.8067 1.0000
3.000 0.4598 0.02214 0.01242 -0.0420 0.7956 1.0000
3.250 0.4865 0.02243 0.01285 -0.0420 0.7852 1.0000
3.500 0.5167 0.02261 0.01322 -0.0421 0.7757 1.0000
3.750 0.5408 0.02293 0.01374 -0.0415 0.7630 1.0000
4.000 0.5680 0.02300 0.01407 -0.0408 0.7483 1.0000
4.250 0.5958 0.02234 0.01361 -0.0384 0.7198 1.0000
4.500 0.6177 0.02072 0.01195 -0.0328 0.6551 1.0000
4.750 0.6345 0.02006 0.01113 -0.0283 0.5728 1.0000
5.000 0.6496 0.02018 0.01090 -0.0246 0.4289 1.0000
5.250 0.6504 0.02269 0.01165 -0.0208 0.1882 1.0000
5.500 0.6603 0.02492 0.01325 -0.0191 0.1223 1.0000
5.750 0.6749 0.02659 0.01474 -0.0177 0.1003 1.0000
6.000 0.6923 0.02803 0.01622 -0.0163 0.0887 1.0000
6.250 0.7118 0.02940 0.01768 -0.0152 0.0786 1.0000
6.500 0.7337 0.03094 0.01925 -0.0144 0.0715 1.0000
6.750 0.7620 0.03248 0.02100 -0.0138 0.0661 1.0000
7.000 0.7889 0.03427 0.02274 -0.0137 0.0606 1.0000
7.250 0.8182 0.03626 0.02505 -0.0134 0.0566 1.0000
7.500 0.8460 0.03869 0.02780 -0.0131 0.0543 1.0000
7.750 0.8703 0.04131 0.03080 -0.0126 0.0526 1.0000
8.000 0.8908 0.04388 0.03362 -0.0120 0.0503 1.0000
8.250 0.9088 0.04708 0.03688 -0.0117 0.0479 1.0000
8.500 0.9209 0.05004 0.04048 -0.0102 0.0466 1.0000
8.750 0.9303 0.05356 0.04451 -0.0088 0.0460 1.0000
9.000 0.9356 0.05731 0.04872 -0.0074 0.0457 1.0000
9.250 0.9369 0.06117 0.05298 -0.0061 0.0456 1.0000
9.500 0.9337 0.06513 0.05729 -0.0048 0.0456 1.0000
9.750 0.9261 0.06913 0.06159 -0.0037 0.0456 1.0000
10.000 0.9136 0.07302 0.06571 -0.0026 0.0458 1.0000
10.250 0.8977 0.07705 0.06992 -0.0020 0.0459 1.0000
10.500 0.8806 0.08154 0.07455 -0.0027 0.0462 1.0000
10.750 0.8629 0.08667 0.07979 -0.0047 0.0464 1.0000
11.000 0.8460 0.09244 0.08564 -0.0077 0.0467 1.0000
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Polar data table (+)
Polar graphs
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