NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-206 (naca65206-il) Reynolds number: 500,000 Max Cl/Cd: 71.17 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65206-il-500000.txt Download as CSV file: xf-naca65206-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5276 0.08792 0.08565 -0.0140 1.0000 0.0103
-8.000 -0.5266 0.08407 0.08182 -0.0164 1.0000 0.0103
-7.750 -0.5282 0.08008 0.07787 -0.0196 1.0000 0.0103
-7.500 -0.5243 0.07531 0.07308 -0.0247 1.0000 0.0103
-7.250 -0.5183 0.07075 0.06848 -0.0280 1.0000 0.0103
-7.000 -0.5107 0.06633 0.06399 -0.0305 1.0000 0.0103
-6.750 -0.5016 0.06195 0.05953 -0.0325 1.0000 0.0103
-6.500 -0.4911 0.05758 0.05505 -0.0339 1.0000 0.0104
-6.250 -0.4793 0.05337 0.05071 -0.0347 1.0000 0.0104
-6.000 -0.4665 0.04912 0.04629 -0.0351 1.0000 0.0104
-5.750 -0.4426 0.02654 0.02367 -0.0356 1.0000 0.0113
-5.500 -0.4324 0.02353 0.02057 -0.0352 1.0000 0.0122
-5.250 -0.4194 0.02116 0.01808 -0.0345 1.0000 0.0133
-5.000 -0.4058 0.01889 0.01564 -0.0333 1.0000 0.0149
-4.750 -0.3821 0.02002 0.01659 -0.0307 1.0000 0.0194
-4.500 -0.3649 0.01792 0.01424 -0.0297 0.9996 0.0196
-4.250 -0.3331 0.01484 0.01082 -0.0316 0.9971 0.0197
-4.000 -0.3005 0.01192 0.00755 -0.0335 0.9948 0.0197
-3.500 -0.2672 0.01684 0.01150 -0.0327 0.9946 0.0175
-3.250 -0.2336 0.01359 0.00784 -0.0331 0.9926 0.0149
-3.000 -0.1999 0.01212 0.00620 -0.0340 0.9896 0.0169
-2.750 -0.1634 0.01227 0.00628 -0.0359 0.9863 0.0198
-2.500 -0.1306 0.01002 0.00393 -0.0370 0.9841 0.0213
-2.250 -0.0942 0.00913 0.00299 -0.0391 0.9820 0.0260
-2.000 -0.0606 0.00874 0.00253 -0.0404 0.9775 0.0304
-1.750 -0.0250 0.00818 0.00190 -0.0422 0.9738 0.0394
-1.500 0.0058 0.00585 0.00150 -0.0444 0.9704 0.6111
-1.250 0.0342 0.00536 0.00157 -0.0444 0.9649 0.7765
-1.000 0.0606 0.00519 0.00164 -0.0435 0.9580 0.8546
-0.750 0.0853 0.00514 0.00166 -0.0423 0.9501 0.8935
-0.500 0.1095 0.00510 0.00164 -0.0409 0.9422 0.9195
-0.250 0.1325 0.00505 0.00160 -0.0395 0.9321 0.9371
0.000 0.1581 0.00501 0.00154 -0.0388 0.9229 0.9510
0.500 0.2198 0.00493 0.00145 -0.0398 0.9050 0.9751
0.750 0.2555 0.00491 0.00142 -0.0416 0.8959 0.9848
1.250 0.3176 0.00489 0.00130 -0.0427 0.8531 1.0000
1.500 0.3396 0.00495 0.00126 -0.0413 0.8220 1.0000
1.750 0.3610 0.00513 0.00119 -0.0397 0.7578 1.0000
2.000 0.3843 0.00540 0.00125 -0.0386 0.6906 1.0000
2.250 0.4042 0.00614 0.00135 -0.0371 0.5276 1.0000
2.500 0.4159 0.00888 0.00210 -0.0355 0.0435 1.0000
2.750 0.4421 0.00936 0.00260 -0.0352 0.0307 1.0000
3.000 0.4671 0.01014 0.00345 -0.0347 0.0243 1.0000
3.250 0.4914 0.01104 0.00443 -0.0340 0.0225 1.0000
3.500 0.5168 0.01175 0.00524 -0.0335 0.0214 1.0000
3.750 0.5424 0.01242 0.00597 -0.0331 0.0191 1.0000
4.000 0.5675 0.01346 0.00708 -0.0325 0.0173 1.0000
4.250 0.5929 0.01495 0.00868 -0.0318 0.0161 1.0000
4.500 0.6191 0.01688 0.01077 -0.0310 0.0159 1.0000
5.000 0.6678 0.02149 0.01593 -0.0296 0.0119 1.0000
5.250 0.6911 0.02501 0.01988 -0.0281 0.0117 1.0000
5.500 0.7148 0.02794 0.02309 -0.0270 0.0141 1.0000
5.750 0.7339 0.03169 0.02718 -0.0258 0.0138 1.0000
6.000 0.7384 0.04070 0.03677 -0.0239 0.0129 1.0000
6.250 0.7535 0.04463 0.04098 -0.0228 0.0129 1.0000
6.500 0.7668 0.04868 0.04531 -0.0218 0.0129 1.0000
6.750 0.7781 0.05288 0.04975 -0.0210 0.0129 1.0000
7.000 0.7877 0.05707 0.05416 -0.0203 0.0128 1.0000
7.250 0.7950 0.06138 0.05867 -0.0197 0.0128 1.0000
7.500 0.7999 0.06573 0.06320 -0.0195 0.0128 1.0000
7.750 0.8022 0.07009 0.06771 -0.0195 0.0128 1.0000
8.000 0.8016 0.07448 0.07221 -0.0198 0.0127 1.0000
8.250 0.7974 0.07886 0.07669 -0.0205 0.0127 1.0000
8.500 0.7871 0.08275 0.08065 -0.0208 0.0127 1.0000
8.750 0.7766 0.08753 0.08547 -0.0236 0.0127 1.0000
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Polar data table (+)
Polar graphs
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