NASA SC(2)-0402 AIRFOIL (sc20402-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: NASA SC(2)-0402 AIRFOIL (sc20402-il) Reynolds number: 100,000 Max Cl/Cd: 16.94 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20402-il-100000-n5.txt Download as CSV file: xf-sc20402-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0402 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.6430 0.09175 0.08723 0.0023 1.0000 0.0289
-7.250 -0.6472 0.08552 0.08108 0.0080 1.0000 0.0306
-7.000 -0.6375 0.08106 0.07660 0.0061 1.0000 0.0320
-6.750 -0.6240 0.07644 0.07193 0.0022 1.0000 0.0334
-6.500 -0.6074 0.07167 0.06708 -0.0024 1.0000 0.0352
-6.250 -0.5873 0.06680 0.06208 -0.0074 1.0000 0.0374
-6.000 -0.5502 0.06310 0.05788 -0.0160 1.0000 0.0414
-5.750 -0.5013 0.04176 0.03647 -0.0174 1.0000 0.0442
-5.500 -0.4850 0.03713 0.03173 -0.0190 1.0000 0.0469
-5.250 -0.4536 0.03336 0.02724 -0.0236 1.0000 0.0552
-5.000 -0.4397 0.02805 0.02205 -0.0242 1.0000 0.0578
-4.750 -0.4140 0.02435 0.01790 -0.0264 1.0000 0.0694
-4.250 -0.3707 0.03200 0.02426 -0.0281 1.0000 0.0233
-4.000 -0.3363 0.02930 0.02087 -0.0279 1.0000 0.0172
-3.750 -0.3076 0.02635 0.01759 -0.0285 1.0000 0.0147
-3.500 -0.2777 0.02360 0.01440 -0.0289 1.0000 0.0134
-3.250 -0.2480 0.02133 0.01172 -0.0289 1.0000 0.0124
-3.000 -0.2189 0.01938 0.00943 -0.0287 1.0000 0.0115
-2.750 -0.1906 0.01771 0.00752 -0.0283 1.0000 0.0109
-2.500 -0.1630 0.01630 0.00597 -0.0278 1.0000 0.0107
-2.250 -0.1357 0.01519 0.00478 -0.0276 1.0000 0.0110
-2.000 -0.1083 0.01434 0.00387 -0.0275 1.0000 0.0120
-1.250 -0.0459 0.00905 0.00123 -0.0211 1.0000 1.0000
-1.000 -0.0182 0.00905 0.00100 -0.0211 1.0000 1.0000
-0.750 0.0093 0.00904 0.00086 -0.0211 1.0000 1.0000
-0.500 0.0367 0.00905 0.00080 -0.0211 1.0000 1.0000
-0.250 0.0640 0.00906 0.00082 -0.0211 1.0000 1.0000
0.000 0.0912 0.00909 0.00091 -0.0211 1.0000 1.0000
0.250 0.1183 0.00912 0.00108 -0.0210 1.0000 1.0000
0.500 0.1455 0.00916 0.00136 -0.0208 1.0000 1.0000
1.000 0.2212 0.01442 0.00397 -0.0238 0.0119 1.0000
1.250 0.2480 0.01528 0.00489 -0.0234 0.0109 1.0000
1.500 0.2748 0.01643 0.00611 -0.0230 0.0107 1.0000
1.750 0.3024 0.01785 0.00767 -0.0225 0.0109 1.0000
2.000 0.3307 0.01955 0.00959 -0.0220 0.0115 1.0000
2.250 0.3594 0.02149 0.01185 -0.0214 0.0123 1.0000
2.500 0.3881 0.02371 0.01446 -0.0209 0.0133 1.0000
2.750 0.4162 0.02635 0.01753 -0.0206 0.0146 1.0000
3.000 0.4427 0.02952 0.02102 -0.0205 0.0169 1.0000
3.250 0.4754 0.03163 0.02379 -0.0192 0.0227 1.0000
4.250 0.5873 0.04656 0.04036 -0.0195 0.0502 1.0000
4.500 0.6111 0.05032 0.04441 -0.0205 0.0458 1.0000
4.750 0.6285 0.05480 0.04895 -0.0211 0.0431 1.0000
5.000 0.6419 0.06194 0.05666 -0.0222 0.0415 1.0000
5.250 0.6777 0.06407 0.05949 -0.0266 0.0376 1.0000
5.500 0.6982 0.06872 0.06433 -0.0297 0.0351 1.0000
5.750 0.7154 0.07341 0.06914 -0.0326 0.0331 1.0000
6.000 0.7291 0.07807 0.07389 -0.0349 0.0314 1.0000
6.250 0.7373 0.08289 0.07873 -0.0353 0.0300 1.0000
6.500 0.7355 0.09073 0.08643 -0.0338 0.0287 1.0000
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Polar data table (+)
Polar graphs
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