NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il) Reynolds number: 200,000 Max Cl/Cd: 36.85 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20406-il-200000-n5.txt Download as CSV file: xf-sc20406-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0406 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6885 0.08694 0.08346 0.0052 1.0000 0.0137
-8.750 -0.6936 0.08032 0.07688 -0.0003 1.0000 0.0134
-8.500 -0.6990 0.07089 0.06747 -0.0116 1.0000 0.0130
-8.250 -0.7017 0.06152 0.05791 -0.0192 1.0000 0.0126
-8.000 -0.6997 0.05260 0.04867 -0.0239 1.0000 0.0123
-7.750 -0.6890 0.04704 0.04280 -0.0262 1.0000 0.0125
-7.500 -0.6717 0.04468 0.04023 -0.0273 1.0000 0.0135
-7.250 -0.6541 0.04033 0.03554 -0.0287 1.0000 0.0144
-7.000 -0.6350 0.03458 0.02924 -0.0299 1.0000 0.0143
-6.750 -0.6126 0.02921 0.02321 -0.0307 1.0000 0.0141
-6.500 -0.5876 0.02523 0.01862 -0.0311 1.0000 0.0140
-6.250 -0.5613 0.02240 0.01532 -0.0313 1.0000 0.0141
-6.000 -0.5347 0.02024 0.01281 -0.0313 1.0000 0.0144
-5.750 -0.5080 0.01851 0.01082 -0.0313 1.0000 0.0149
-5.500 -0.4811 0.01709 0.00920 -0.0312 1.0000 0.0156
-5.250 -0.4541 0.01589 0.00782 -0.0312 1.0000 0.0167
-5.000 -0.4267 0.01493 0.00672 -0.0313 1.0000 0.0178
-4.750 -0.3992 0.01400 0.00576 -0.0316 1.0000 0.0213
-4.500 -0.3715 0.01345 0.00515 -0.0317 1.0000 0.0268
-4.250 -0.3433 0.01269 0.00436 -0.0320 1.0000 0.0366
-4.000 -0.3153 0.01221 0.00384 -0.0322 1.0000 0.0492
-3.750 -0.2876 0.01181 0.00347 -0.0324 1.0000 0.0656
-3.500 -0.2597 0.01133 0.00309 -0.0328 1.0000 0.0913
-3.250 -0.2315 0.01078 0.00273 -0.0332 1.0000 0.1366
-3.000 -0.2030 0.00999 0.00240 -0.0341 1.0000 0.2532
-2.750 -0.1743 0.00885 0.00217 -0.0352 1.0000 0.4855
-2.500 -0.1477 0.00848 0.00218 -0.0349 1.0000 0.5974
-2.250 -0.1219 0.00831 0.00220 -0.0344 1.0000 0.6568
-2.000 -0.0967 0.00821 0.00224 -0.0336 1.0000 0.7049
-1.750 -0.0718 0.00815 0.00226 -0.0327 1.0000 0.7403
-1.500 -0.0475 0.00812 0.00231 -0.0317 1.0000 0.7699
-1.250 -0.0236 0.00810 0.00236 -0.0307 1.0000 0.7963
-1.000 0.0002 0.00808 0.00241 -0.0296 1.0000 0.8148
-0.750 0.0249 0.00807 0.00243 -0.0289 1.0000 0.8283
-0.500 0.0498 0.00806 0.00247 -0.0283 1.0000 0.8404
-0.250 0.0745 0.00807 0.00253 -0.0276 1.0000 0.8522
0.000 0.0993 0.00808 0.00261 -0.0270 1.0000 0.8640
0.250 0.1237 0.00810 0.00271 -0.0264 1.0000 0.8763
0.500 0.1708 0.00800 0.00269 -0.0304 0.9827 0.8849
0.750 0.2144 0.00788 0.00263 -0.0334 0.9491 0.8942
1.000 0.2503 0.00779 0.00256 -0.0343 0.8970 0.9051
1.250 0.2753 0.00782 0.00250 -0.0327 0.8209 0.9186
1.500 0.2944 0.00810 0.00240 -0.0298 0.7020 0.9349
1.750 0.3135 0.00892 0.00238 -0.0276 0.4975 0.9564
2.000 0.3390 0.01008 0.00261 -0.0278 0.2686 1.0000
2.250 0.3664 0.01099 0.00295 -0.0284 0.1380 1.0000
2.500 0.3949 0.01156 0.00334 -0.0289 0.0904 1.0000
2.750 0.4234 0.01206 0.00372 -0.0293 0.0630 1.0000
3.000 0.4518 0.01252 0.00409 -0.0297 0.0433 1.0000
3.250 0.4801 0.01303 0.00460 -0.0299 0.0313 1.0000
3.500 0.5078 0.01381 0.00538 -0.0300 0.0229 1.0000
3.750 0.5355 0.01457 0.00630 -0.0300 0.0203 1.0000
4.000 0.5626 0.01549 0.00732 -0.0299 0.0187 1.0000
4.250 0.5895 0.01654 0.00847 -0.0297 0.0178 1.0000
4.500 0.6163 0.01777 0.00982 -0.0295 0.0171 1.0000
4.750 0.6429 0.01897 0.01114 -0.0293 0.0159 1.0000
5.000 0.6689 0.02069 0.01311 -0.0291 0.0145 1.0000
5.250 0.6952 0.02250 0.01526 -0.0288 0.0139 1.0000
5.500 0.7205 0.02497 0.01817 -0.0282 0.0134 1.0000
5.750 0.7441 0.02823 0.02198 -0.0275 0.0131 1.0000
6.000 0.7651 0.03249 0.02686 -0.0267 0.0130 1.0000
6.250 0.7828 0.03775 0.03271 -0.0258 0.0130 1.0000
6.500 0.7976 0.04359 0.03907 -0.0252 0.0132 1.0000
6.750 0.8096 0.04962 0.04551 -0.0251 0.0134 1.0000
7.000 0.8189 0.05571 0.05193 -0.0255 0.0137 1.0000
7.250 0.8253 0.06181 0.05829 -0.0265 0.0139 1.0000
7.500 0.8285 0.06794 0.06463 -0.0282 0.0142 1.0000
7.750 0.8285 0.07408 0.07090 -0.0306 0.0144 1.0000
8.000 0.8258 0.08033 0.07726 -0.0339 0.0146 1.0000
8.250 0.7144 0.07578 0.07291 -0.0285 0.0145 1.0000
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Polar data table (+)
Polar graphs
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