NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-209 (naca65209-il) Reynolds number: 500,000 Max Cl/Cd: 61.19 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65209-il-500000-n5.txt Download as CSV file: xf-naca65209-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-209
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5759 0.08054 0.07830 -0.0276 1.0000 0.0052
-9.500 -0.5872 0.07333 0.07116 -0.0333 1.0000 0.0052
-9.250 -0.6048 0.06598 0.06380 -0.0403 1.0000 0.0051
-9.000 -0.6236 0.06139 0.05915 -0.0418 1.0000 0.0051
-8.750 -0.6373 0.05584 0.05347 -0.0428 1.0000 0.0050
-8.500 -0.6506 0.04927 0.04668 -0.0427 1.0000 0.0051
-8.250 -0.6700 0.03981 0.03678 -0.0407 1.0000 0.0052
-8.000 -0.6884 0.02568 0.02155 -0.0378 0.9943 0.0060
-7.750 -0.6584 0.02512 0.02087 -0.0392 0.9893 0.0063
-7.500 -0.6289 0.02371 0.01925 -0.0406 0.9843 0.0070
-7.250 -0.6027 0.02040 0.01544 -0.0413 0.9776 0.0082
-7.000 -0.5718 0.01957 0.01438 -0.0424 0.9720 0.0090
-6.750 -0.5433 0.01800 0.01258 -0.0434 0.9653 0.0100
-6.500 -0.5132 0.01778 0.01232 -0.0445 0.9585 0.0108
-6.250 -0.4841 0.01682 0.01120 -0.0451 0.9512 0.0114
-6.000 -0.4568 0.01608 0.01033 -0.0453 0.9425 0.0124
-5.750 -0.4300 0.01514 0.00923 -0.0453 0.9342 0.0132
-5.500 -0.4046 0.01421 0.00812 -0.0449 0.9251 0.0138
-5.250 -0.3792 0.01353 0.00732 -0.0446 0.9162 0.0142
-5.000 -0.3536 0.01300 0.00668 -0.0442 0.9078 0.0146
-4.750 -0.3302 0.01195 0.00552 -0.0436 0.8986 0.0153
-4.500 -0.3059 0.01123 0.00471 -0.0431 0.8900 0.0162
-4.250 -0.2803 0.01085 0.00428 -0.0428 0.8820 0.0175
-4.000 -0.2542 0.01052 0.00388 -0.0426 0.8738 0.0189
-3.750 -0.2281 0.01016 0.00344 -0.0423 0.8660 0.0203
-3.500 -0.2017 0.00986 0.00307 -0.0421 0.8578 0.0218
-3.250 -0.1750 0.00963 0.00277 -0.0420 0.8504 0.0231
-3.000 -0.1483 0.00933 0.00239 -0.0419 0.8428 0.0258
-2.750 -0.1213 0.00910 0.00212 -0.0418 0.8354 0.0309
-2.500 -0.0942 0.00894 0.00192 -0.0417 0.8278 0.0377
-2.250 -0.0672 0.00867 0.00173 -0.0417 0.8206 0.0637
-2.000 -0.0416 0.00805 0.00150 -0.0418 0.8135 0.1902
-1.750 -0.0183 0.00679 0.00121 -0.0420 0.8061 0.4721
-1.500 0.0061 0.00624 0.00124 -0.0415 0.7991 0.6442
-1.250 0.0329 0.00614 0.00126 -0.0412 0.7921 0.6897
-1.000 0.0598 0.00610 0.00126 -0.0410 0.7855 0.7193
-0.750 0.0873 0.00608 0.00127 -0.0409 0.7786 0.7392
-0.500 0.1151 0.00609 0.00125 -0.0409 0.7719 0.7475
-0.250 0.1432 0.00609 0.00123 -0.0410 0.7653 0.7552
0.000 0.1709 0.00610 0.00124 -0.0409 0.7585 0.7619
0.250 0.1990 0.00612 0.00125 -0.0410 0.7519 0.7695
0.500 0.2267 0.00613 0.00127 -0.0410 0.7451 0.7762
0.750 0.2548 0.00615 0.00130 -0.0411 0.7384 0.7838
1.000 0.2824 0.00617 0.00134 -0.0411 0.7314 0.7908
1.500 0.3370 0.00625 0.00143 -0.0408 0.7051 0.8056
1.750 0.3638 0.00632 0.00147 -0.0406 0.6853 0.8134
2.000 0.3896 0.00643 0.00150 -0.0401 0.6507 0.8211
2.250 0.4130 0.00675 0.00154 -0.0392 0.5732 0.8289
2.500 0.4327 0.00759 0.00176 -0.0379 0.4144 0.8378
2.750 0.4510 0.00879 0.00221 -0.0368 0.2231 0.8465
3.000 0.4719 0.00972 0.00261 -0.0360 0.0876 0.8555
3.250 0.4958 0.01019 0.00290 -0.0355 0.0414 0.8644
3.500 0.5207 0.01047 0.00318 -0.0350 0.0298 0.8734
3.750 0.5461 0.01068 0.00346 -0.0346 0.0256 0.8831
4.000 0.5707 0.01095 0.00376 -0.0340 0.0219 0.8931
4.250 0.5938 0.01140 0.00429 -0.0331 0.0186 0.9036
4.500 0.6177 0.01167 0.00463 -0.0324 0.0179 0.9147
4.750 0.6410 0.01200 0.00504 -0.0315 0.0169 0.9270
5.000 0.6638 0.01239 0.00554 -0.0306 0.0160 0.9403
5.250 0.6875 0.01286 0.00608 -0.0299 0.0151 0.9557
5.750 0.7426 0.01415 0.00752 -0.0305 0.0140 1.0000
6.000 0.7662 0.01488 0.00831 -0.0300 0.0137 1.0000
6.250 0.7902 0.01552 0.00900 -0.0297 0.0131 1.0000
6.500 0.8138 0.01627 0.00983 -0.0292 0.0126 1.0000
6.750 0.8364 0.01735 0.01100 -0.0286 0.0122 1.0000
7.000 0.8586 0.01876 0.01254 -0.0279 0.0118 1.0000
7.250 0.8798 0.02113 0.01512 -0.0271 0.0114 1.0000
7.500 0.9032 0.02221 0.01636 -0.0266 0.0112 1.0000
7.750 0.9259 0.02344 0.01777 -0.0261 0.0110 1.0000
8.000 0.9488 0.02430 0.01879 -0.0256 0.0105 1.0000
8.250 0.9712 0.02518 0.01986 -0.0251 0.0097 1.0000
8.500 0.9935 0.02567 0.02045 -0.0246 0.0088 1.0000
8.750 1.0159 0.02594 0.02078 -0.0243 0.0082 1.0000
9.000 1.0371 0.02646 0.02139 -0.0238 0.0078 1.0000
9.250 1.0573 0.02713 0.02214 -0.0231 0.0075 1.0000
9.500 1.0746 0.02825 0.02340 -0.0222 0.0070 1.0000
9.750 1.0880 0.03049 0.02596 -0.0208 0.0066 1.0000
10.000 1.0962 0.03392 0.02984 -0.0188 0.0061 1.0000
10.250 1.0690 0.04389 0.04066 -0.0137 0.0049 1.0000
10.500 1.0629 0.04797 0.04500 -0.0111 0.0046 1.0000
10.750 1.0372 0.05315 0.05047 -0.0070 0.0045 1.0000
11.000 1.0301 0.05555 0.05299 -0.0051 0.0044 1.0000
11.250 0.9666 0.06601 0.06378 -0.0044 0.0045 1.0000
11.500 0.9142 0.07742 0.07539 -0.0095 0.0047 1.0000
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Polar data table (+)
Polar graphs
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