NASA SC(2)-0402 AIRFOIL (sc20402-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0402 AIRFOIL (sc20402-il) Reynolds number: 200,000 Max Cl/Cd: 20.14 at α=0.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20402-il-200000.txt Download as CSV file: xf-sc20402-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6845 0.10555 0.10223 0.0276 1.0000 0.0166
-8.250 -0.6806 0.10146 0.09815 0.0271 1.0000 0.0172
-8.000 -0.6767 0.09761 0.09431 0.0255 1.0000 0.0177
-7.750 -0.6721 0.09372 0.09046 0.0232 1.0000 0.0182
-7.500 -0.6640 0.08945 0.08620 0.0194 1.0000 0.0187
-7.250 -0.6534 0.08488 0.08164 0.0146 1.0000 0.0193
-7.000 -0.6402 0.08008 0.07682 0.0092 1.0000 0.0200
-6.750 -0.6246 0.07513 0.07183 0.0037 1.0000 0.0208
-6.500 -0.6065 0.07011 0.06675 -0.0018 1.0000 0.0217
-6.250 -0.5859 0.06508 0.06161 -0.0071 1.0000 0.0227
-6.000 -0.5625 0.06011 0.05650 -0.0119 1.0000 0.0241
-5.750 -0.5336 0.05546 0.05159 -0.0166 1.0000 0.0261
-5.500 -0.4949 0.05314 0.04847 -0.0203 1.0000 0.0277
-5.250 -0.4725 0.04661 0.04167 -0.0236 1.0000 0.0286
-5.000 -0.4567 0.04129 0.03643 -0.0252 1.0000 0.0314
-4.750 -0.4300 0.03779 0.03271 -0.0269 1.0000 0.0358
-4.500 -0.3935 0.03546 0.02963 -0.0284 1.0000 0.0417
-4.250 -0.3717 0.03087 0.02515 -0.0300 1.0000 0.0473
-4.000 -0.3416 0.02786 0.02176 -0.0312 1.0000 0.0578
-3.750 -0.3130 0.02522 0.01886 -0.0322 1.0000 0.0720
-3.500 -0.2844 0.02287 0.01625 -0.0333 1.0000 0.0968
-2.750 -0.1860 0.01697 0.00896 -0.0307 1.0000 0.0417
-2.500 -0.1567 0.01485 0.00672 -0.0299 1.0000 0.0261
-2.250 -0.1282 0.01303 0.00481 -0.0294 1.0000 0.0215
-2.000 -0.0989 0.01152 0.00327 -0.0291 1.0000 0.0173
-1.750 -0.0695 0.01057 0.00224 -0.0293 1.0000 0.0170
-1.500 -0.0400 0.00989 0.00133 -0.0294 1.0000 0.0218
-1.250 -0.0355 0.00642 0.00103 -0.0237 1.0000 1.0000
-1.000 -0.0073 0.00642 0.00082 -0.0237 1.0000 1.0000
-0.750 0.0205 0.00642 0.00073 -0.0238 1.0000 1.0000
-0.500 0.0482 0.00643 0.00069 -0.0238 1.0000 1.0000
-0.250 0.0758 0.00644 0.00072 -0.0239 1.0000 1.0000
0.000 0.1032 0.00647 0.00080 -0.0239 1.0000 1.0000
0.250 0.1307 0.00649 0.00096 -0.0238 1.0000 1.0000
0.500 0.1734 0.01021 0.00170 -0.0269 0.0188 1.0000
0.750 0.2014 0.01101 0.00270 -0.0266 0.0167 1.0000
1.000 0.2291 0.01218 0.00390 -0.0260 0.0189 1.0000
1.250 0.2568 0.01366 0.00543 -0.0253 0.0225 1.0000
1.500 0.2847 0.01601 0.00782 -0.0248 0.0283 1.0000
1.750 0.3180 0.01720 0.00945 -0.0229 0.0617 1.0000
2.000 0.3604 0.01930 0.01252 -0.0200 0.1637 1.0000
2.250 0.3859 0.02138 0.01466 -0.0201 0.1251 1.0000
2.500 0.4103 0.02390 0.01714 -0.0203 0.0948 1.0000
2.750 0.4363 0.02589 0.01944 -0.0204 0.0702 1.0000
3.000 0.4622 0.02849 0.02229 -0.0205 0.0566 1.0000
3.250 0.4895 0.03118 0.02541 -0.0204 0.0463 1.0000
4.500 0.6008 0.05271 0.04802 -0.0235 0.0276 1.0000
4.750 0.6376 0.05426 0.05044 -0.0246 0.0256 1.0000
5.000 0.6639 0.05854 0.05498 -0.0268 0.0236 1.0000
5.250 0.6863 0.06321 0.05984 -0.0295 0.0222 1.0000
5.500 0.7065 0.06802 0.06479 -0.0326 0.0210 1.0000
5.750 0.7247 0.07290 0.06978 -0.0361 0.0200 1.0000
6.000 0.7407 0.07780 0.07476 -0.0398 0.0192 1.0000
6.250 0.7545 0.08268 0.07971 -0.0436 0.0185 1.0000
6.500 0.7660 0.08752 0.08458 -0.0473 0.0178 1.0000
6.750 0.7753 0.09228 0.08937 -0.0506 0.0173 1.0000
7.000 0.7821 0.09699 0.09409 -0.0531 0.0167 1.0000
7.250 0.7854 0.10193 0.09903 -0.0534 0.0160 1.0000
7.500 0.7854 0.10808 0.10518 -0.0544 0.0155 1.0000
7.750 0.6724 0.09993 0.09709 -0.0511 0.0189 1.0000
8.000 0.6717 0.10416 0.10130 -0.0523 0.0186 1.0000
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Polar data table (+)
Polar graphs
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