NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-206 (naca65206-il) Reynolds number: 500,000 Max Cl/Cd: 56.73 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65206-il-500000-n5.txt Download as CSV file: xf-naca65206-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-206
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.4956 0.15073 0.14856 0.0143 1.0000 0.0046
-13.000 -0.4943 0.14834 0.14616 0.0129 1.0000 0.0046
-9.500 -0.5485 0.10669 0.10436 -0.0023 1.0000 0.0046
-8.000 -0.5433 0.08204 0.07985 -0.0132 1.0000 0.0042
-7.750 -0.5451 0.07828 0.07607 -0.0157 1.0000 0.0042
-7.500 -0.5457 0.07323 0.07104 -0.0210 1.0000 0.0040
-7.250 -0.5408 0.06848 0.06625 -0.0253 1.0000 0.0038
-7.000 -0.5341 0.06360 0.06132 -0.0289 1.0000 0.0037
-6.750 -0.5251 0.05879 0.05642 -0.0318 1.0000 0.0036
-6.500 -0.5141 0.05402 0.05154 -0.0340 1.0000 0.0034
-6.250 -0.5014 0.04914 0.04651 -0.0355 1.0000 0.0033
-6.000 -0.4868 0.04444 0.04162 -0.0363 1.0000 0.0031
-5.750 -0.4710 0.03973 0.03669 -0.0365 1.0000 0.0031
-5.500 -0.4539 0.03525 0.03194 -0.0361 1.0000 0.0030
-5.250 -0.4359 0.03078 0.02717 -0.0352 1.0000 0.0030
-5.000 -0.4042 0.02531 0.02121 -0.0365 0.9961 0.0032
-4.750 -0.3721 0.01998 0.01530 -0.0371 0.9920 0.0038
-4.500 -0.3396 0.01716 0.01211 -0.0378 0.9886 0.0045
-4.250 -0.3083 0.01480 0.00937 -0.0389 0.9852 0.0056
-4.000 -0.2772 0.01300 0.00730 -0.0396 0.9809 0.0059
-3.750 -0.2450 0.01170 0.00583 -0.0405 0.9772 0.0068
-3.500 -0.2146 0.01071 0.00471 -0.0410 0.9714 0.0086
-3.250 -0.1818 0.01054 0.00445 -0.0422 0.9669 0.0103
-3.000 -0.1529 0.00938 0.00318 -0.0427 0.9597 0.0142
-2.750 -0.1218 0.00896 0.00269 -0.0435 0.9535 0.0164
-2.500 -0.0924 0.00863 0.00229 -0.0439 0.9453 0.0189
-2.250 -0.0632 0.00831 0.00189 -0.0443 0.9374 0.0208
-2.000 -0.0346 0.00803 0.00153 -0.0445 0.9290 0.0261
-1.750 -0.0069 0.00785 0.00129 -0.0444 0.9195 0.0354
-1.500 0.0200 0.00729 0.00111 -0.0446 0.9101 0.1549
-1.250 0.0434 0.00569 0.00094 -0.0448 0.9005 0.5951
-1.000 0.0673 0.00527 0.00099 -0.0439 0.8906 0.7387
-0.750 0.0916 0.00512 0.00102 -0.0429 0.8807 0.8020
-0.500 0.1163 0.00506 0.00103 -0.0420 0.8711 0.8388
-0.250 0.1427 0.00506 0.00101 -0.0416 0.8614 0.8521
0.000 0.1691 0.00506 0.00100 -0.0412 0.8510 0.8642
0.250 0.1955 0.00507 0.00100 -0.0408 0.8406 0.8760
0.500 0.2216 0.00508 0.00103 -0.0403 0.8301 0.8879
0.750 0.2474 0.00510 0.00105 -0.0398 0.8192 0.8997
1.000 0.2726 0.00514 0.00106 -0.0390 0.7994 0.9119
1.250 0.2967 0.00523 0.00105 -0.0380 0.7654 0.9246
1.750 0.3394 0.00613 0.00108 -0.0350 0.5329 0.9537
2.000 0.3608 0.00775 0.00144 -0.0348 0.2064 0.9718
2.500 0.4171 0.00895 0.00199 -0.0359 0.0306 1.0000
2.750 0.4440 0.00924 0.00231 -0.0358 0.0243 1.0000
3.000 0.4709 0.00953 0.00269 -0.0357 0.0212 1.0000
3.250 0.4975 0.00986 0.00307 -0.0356 0.0187 1.0000
3.500 0.5237 0.01030 0.00356 -0.0354 0.0167 1.0000
3.750 0.5469 0.01144 0.00484 -0.0346 0.0138 1.0000
4.000 0.5742 0.01156 0.00499 -0.0347 0.0126 1.0000
4.250 0.6000 0.01206 0.00556 -0.0344 0.0107 1.0000
4.500 0.6255 0.01270 0.00627 -0.0340 0.0087 1.0000
4.750 0.6499 0.01363 0.00731 -0.0336 0.0061 1.0000
5.000 0.6757 0.01419 0.00797 -0.0333 0.0053 1.0000
5.250 0.7002 0.01551 0.00947 -0.0326 0.0043 1.0000
5.500 0.7246 0.01725 0.01144 -0.0318 0.0037 1.0000
5.750 0.7483 0.01974 0.01428 -0.0308 0.0034 1.0000
6.000 0.7691 0.02459 0.01972 -0.0289 0.0034 1.0000
6.250 0.7863 0.03090 0.02666 -0.0264 0.0035 1.0000
6.500 0.8010 0.03712 0.03339 -0.0242 0.0037 1.0000
6.750 0.8138 0.04277 0.03943 -0.0225 0.0039 1.0000
7.000 0.8246 0.04817 0.04514 -0.0213 0.0041 1.0000
7.250 0.8325 0.05358 0.05082 -0.0205 0.0043 1.0000
7.500 0.8378 0.05881 0.05627 -0.0201 0.0045 1.0000
7.750 0.8411 0.06387 0.06151 -0.0201 0.0044 1.0000
8.000 0.8408 0.06903 0.06681 -0.0207 0.0043 1.0000
8.250 0.8346 0.07419 0.07208 -0.0218 0.0047 1.0000
8.500 0.8255 0.07891 0.07688 -0.0230 0.0045 1.0000
8.750 0.8106 0.08389 0.08190 -0.0259 0.0048 1.0000
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Polar data table (+)
Polar graphs
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