NASA SC(2)-0606 AIRFOIL (sc20606-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: NASA SC(2)-0606 AIRFOIL (sc20606-il) Reynolds number: 500,000 Max Cl/Cd: 72.36 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20606-il-500000.txt Download as CSV file: xf-sc20606-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0606 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6102 0.08437 0.08207 -0.0131 1.0000 0.0180
-9.000 -0.6139 0.07975 0.07748 -0.0158 1.0000 0.0183
-8.750 -0.6185 0.07440 0.07217 -0.0203 1.0000 0.0185
-8.500 -0.6188 0.06658 0.06432 -0.0306 1.0000 0.0186
-8.250 -0.6156 0.06022 0.05785 -0.0360 1.0000 0.0191
-8.000 -0.6054 0.05408 0.05151 -0.0400 1.0000 0.0204
-7.750 -0.5849 0.05059 0.04773 -0.0417 1.0000 0.0216
-6.500 -0.4734 0.02297 0.01801 -0.0541 1.0000 0.0228
-6.250 -0.4392 0.01737 0.01185 -0.0559 1.0000 0.0175
-6.000 -0.4092 0.01517 0.00936 -0.0564 1.0000 0.0176
-5.750 -0.3805 0.01388 0.00790 -0.0568 1.0000 0.0184
-5.500 -0.3515 0.01284 0.00675 -0.0571 1.0000 0.0194
-5.250 -0.3227 0.01208 0.00591 -0.0575 1.0000 0.0206
-5.000 -0.2944 0.01159 0.00536 -0.0577 1.0000 0.0220
-4.750 -0.2597 0.01027 0.00395 -0.0597 1.0000 0.0258
-4.500 -0.2302 0.00987 0.00349 -0.0602 1.0000 0.0309
-4.250 -0.1994 0.00937 0.00298 -0.0610 1.0000 0.0438
-4.000 -0.1688 0.00893 0.00263 -0.0619 1.0000 0.0699
-3.750 -0.1341 0.00816 0.00234 -0.0641 1.0000 0.1857
-3.500 -0.0905 0.00677 0.00209 -0.0690 1.0000 0.5004
-3.250 -0.0597 0.00654 0.00210 -0.0698 1.0000 0.5877
-3.000 -0.0307 0.00645 0.00213 -0.0701 1.0000 0.6341
-2.750 -0.0024 0.00644 0.00216 -0.0702 1.0000 0.6609
-2.500 0.0256 0.00645 0.00219 -0.0702 1.0000 0.6833
-2.250 0.0532 0.00646 0.00227 -0.0701 1.0000 0.7072
-2.000 0.0805 0.00651 0.00237 -0.0699 1.0000 0.7288
-1.750 0.1077 0.00656 0.00247 -0.0697 1.0000 0.7443
-1.500 0.1348 0.00662 0.00258 -0.0694 1.0000 0.7583
-1.250 0.1617 0.00669 0.00269 -0.0692 1.0000 0.7713
-1.000 0.1890 0.00677 0.00281 -0.0691 1.0000 0.7824
-0.750 0.2158 0.00682 0.00294 -0.0688 1.0000 0.7911
-0.500 0.2429 0.00690 0.00308 -0.0687 1.0000 0.7995
-0.250 0.2792 0.00684 0.00309 -0.0706 0.9965 0.8072
0.000 0.3362 0.00643 0.00276 -0.0768 0.9829 0.8127
0.250 0.3764 0.00620 0.00264 -0.0792 0.9687 0.8187
0.500 0.4262 0.00589 0.00234 -0.0834 0.9146 0.8245
0.750 0.4441 0.00718 0.00237 -0.0803 0.5967 0.8300
1.000 0.4627 0.00904 0.00277 -0.0792 0.2404 0.8372
1.250 0.4863 0.01000 0.00311 -0.0786 0.0850 0.8431
1.500 0.5129 0.01050 0.00347 -0.0783 0.0507 0.8503
1.750 0.5390 0.01091 0.00388 -0.0778 0.0344 0.8565
2.000 0.5651 0.01153 0.00454 -0.0773 0.0265 0.8638
2.250 0.5909 0.01198 0.00507 -0.0767 0.0234 0.8701
2.500 0.6168 0.01259 0.00574 -0.0761 0.0211 0.8773
2.750 0.6401 0.01388 0.00715 -0.0749 0.0195 0.8837
3.000 0.6644 0.01556 0.00898 -0.0739 0.0187 0.8909
3.250 0.6899 0.01599 0.00953 -0.0732 0.0178 0.8978
3.500 0.7156 0.01729 0.01100 -0.0724 0.0173 0.9056
3.750 0.7395 0.01890 0.01288 -0.0711 0.0168 0.9129
4.000 0.7636 0.02138 0.01573 -0.0697 0.0167 0.9208
4.250 0.7844 0.02528 0.02001 -0.0676 0.0197 0.9293
12.500 0.7011 0.16656 0.16484 -0.0808 0.0124 1.0000
12.750 0.7018 0.16971 0.16799 -0.0821 0.0123 1.0000
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Polar data table (+)
Polar graphs
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