NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il) Reynolds number: 50,000 Max Cl/Cd: 18.02 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20403-il-50000-n5.txt Download as CSV file: xf-sc20403-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0403 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6841 0.11733 0.11043 0.0252 1.0000 0.0749
-8.750 -0.6885 0.11479 0.10799 0.0200 1.0000 0.0775
-8.500 -0.6919 0.11187 0.10516 0.0141 1.0000 0.0780
-8.250 -0.6791 0.10578 0.09908 0.0181 1.0000 0.0805
-8.000 -0.6732 0.10171 0.09504 0.0175 1.0000 0.0832
-7.750 -0.6688 0.09771 0.09108 0.0144 1.0000 0.0862
-7.500 -0.6659 0.09356 0.08694 -0.0004 1.0000 0.0914
-7.250 -0.6559 0.08838 0.08181 0.0034 1.0000 0.0935
-7.000 -0.6456 0.08389 0.07732 0.0016 1.0000 0.0960
-6.750 -0.6338 0.07922 0.07261 -0.0024 1.0000 0.0992
-6.500 -0.6064 0.07168 0.06480 -0.0090 1.0000 0.0464
-6.250 -0.5862 0.06612 0.05903 -0.0131 1.0000 0.0351
-6.000 -0.5677 0.06105 0.05379 -0.0163 1.0000 0.0321
-5.750 -0.5452 0.05590 0.04835 -0.0199 1.0000 0.0300
-5.500 -0.5209 0.05115 0.04324 -0.0227 1.0000 0.0293
-5.250 -0.4969 0.04706 0.03881 -0.0248 1.0000 0.0313
-5.000 -0.4699 0.04310 0.03440 -0.0268 1.0000 0.0335
-4.750 -0.4409 0.03933 0.03008 -0.0284 1.0000 0.0351
-4.500 -0.4112 0.03573 0.02593 -0.0294 1.0000 0.0353
-4.250 -0.3812 0.03235 0.02200 -0.0300 1.0000 0.0343
-4.000 -0.3510 0.02933 0.01844 -0.0301 1.0000 0.0337
-3.750 -0.3217 0.02673 0.01533 -0.0298 1.0000 0.0337
-3.500 -0.2936 0.02447 0.01226 -0.0288 1.0000 0.0344
-3.250 -0.2672 0.02258 0.01005 -0.0274 1.0000 0.0368
-3.000 -0.2420 0.02085 0.00808 -0.0261 1.0000 0.0412
-2.750 -0.2149 0.01947 0.00657 -0.0260 1.0000 0.0633
-2.500 -0.1849 0.01731 0.00469 -0.0267 1.0000 0.1242
-2.000 -0.1588 0.01336 0.00350 -0.0167 1.0000 1.0000
-1.750 -0.1313 0.01326 0.00296 -0.0170 1.0000 1.0000
-1.500 -0.1038 0.01319 0.00256 -0.0172 1.0000 1.0000
-1.250 -0.0765 0.01314 0.00225 -0.0174 1.0000 1.0000
-1.000 -0.0491 0.01311 0.00194 -0.0175 1.0000 1.0000
-0.750 -0.0219 0.01309 0.00177 -0.0176 1.0000 1.0000
-0.500 0.0052 0.01309 0.00167 -0.0177 1.0000 1.0000
-0.250 0.0322 0.01309 0.00163 -0.0177 1.0000 1.0000
0.000 0.0591 0.01311 0.00167 -0.0177 1.0000 1.0000
0.250 0.0860 0.01314 0.00177 -0.0177 1.0000 1.0000
0.500 0.1127 0.01319 0.00194 -0.0176 1.0000 1.0000
0.750 0.1395 0.01325 0.00226 -0.0175 1.0000 1.0000
1.000 0.1661 0.01332 0.00256 -0.0174 1.0000 1.0000
1.250 0.1926 0.01341 0.00295 -0.0173 1.0000 1.0000
1.500 0.2191 0.01352 0.00345 -0.0170 1.0000 1.0000
1.750 0.2458 0.01364 0.00415 -0.0167 1.0000 1.0000
2.000 0.3064 0.01928 0.00640 -0.0218 0.0647 1.0000
2.250 0.3342 0.02066 0.00800 -0.0215 0.0427 1.0000
2.500 0.3635 0.02252 0.01011 -0.0210 0.0364 1.0000
2.750 0.3932 0.02455 0.01251 -0.0202 0.0339 1.0000
3.000 0.4230 0.02693 0.01570 -0.0194 0.0330 1.0000
3.250 0.4524 0.02955 0.01886 -0.0188 0.0332 1.0000
3.500 0.4814 0.03251 0.02236 -0.0183 0.0338 1.0000
3.750 0.5094 0.03577 0.02615 -0.0180 0.0348 1.0000
4.000 0.5366 0.03917 0.03009 -0.0178 0.0347 1.0000
4.250 0.5629 0.04269 0.03415 -0.0179 0.0333 1.0000
4.500 0.5876 0.04637 0.03828 -0.0184 0.0310 1.0000
4.750 0.6097 0.05015 0.04240 -0.0190 0.0287 1.0000
5.000 0.6322 0.05448 0.04711 -0.0200 0.0288 1.0000
5.250 0.6548 0.05937 0.05237 -0.0217 0.0310 1.0000
5.500 0.6741 0.06435 0.05759 -0.0236 0.0340 1.0000
5.750 0.6949 0.06971 0.06322 -0.0258 0.0454 1.0000
6.250 0.7376 0.08173 0.07569 -0.0331 0.0953 1.0000
6.750 0.7592 0.09247 0.08634 -0.0323 0.0908 1.0000
7.000 0.7647 0.09599 0.09007 -0.0438 0.0840 1.0000
7.250 0.7720 0.10052 0.09460 -0.0459 0.0810 1.0000
7.500 0.7817 0.10605 0.10011 -0.0418 0.0782 1.0000
7.750 0.7854 0.11078 0.10481 -0.0468 0.0773 1.0000
8.000 0.7812 0.11403 0.10799 -0.0553 0.0755 1.0000
8.250 0.7809 0.11779 0.11170 -0.0591 0.0727 1.0000
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Polar data table (+)
Polar graphs
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