NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il) Reynolds number: 100,000 Max Cl/Cd: 37.59 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20404-il-100000.txt Download as CSV file: xf-sc20404-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0404 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6590 0.09820 0.09340 0.0134 1.0000 0.0634
-8.000 -0.6580 0.09420 0.08946 0.0097 1.0000 0.0658
-7.750 -0.6533 0.08894 0.08422 -0.0021 1.0000 0.0679
-7.500 -0.6456 0.08415 0.07917 -0.0151 1.0000 0.0688
-7.250 -0.6386 0.07854 0.07382 -0.0079 1.0000 0.0717
-7.000 -0.6278 0.07441 0.06967 -0.0094 1.0000 0.0761
-6.750 -0.6103 0.06929 0.06400 -0.0231 1.0000 0.0823
-6.500 -0.6007 0.06406 0.05910 -0.0190 1.0000 0.0862
-6.250 -0.5818 0.05910 0.05380 -0.0249 1.0000 0.0968
-5.250 -0.5085 0.04398 0.03819 -0.0301 1.0000 0.1894
-5.000 -0.4906 0.04072 0.03505 -0.0291 1.0000 0.2209
-4.500 -0.3871 0.02764 0.01929 -0.0360 1.0000 0.0645
-4.250 -0.3540 0.02473 0.01561 -0.0355 1.0000 0.0546
-4.000 -0.3248 0.02188 0.01243 -0.0353 1.0000 0.0529
-3.750 -0.2961 0.01979 0.01002 -0.0349 1.0000 0.0578
-3.500 -0.2688 0.01806 0.00823 -0.0344 1.0000 0.0652
-3.250 -0.2415 0.01639 0.00649 -0.0336 1.0000 0.0697
-3.000 -0.2139 0.01471 0.00493 -0.0335 1.0000 0.0860
-2.750 -0.2002 0.01086 0.00420 -0.0301 1.0000 0.7505
-2.500 -0.2015 0.01070 0.00409 -0.0209 1.0000 0.8671
-2.250 -0.1971 0.01019 0.00359 -0.0134 1.0000 0.9506
-2.000 -0.1540 0.00987 0.00296 -0.0163 1.0000 1.0000
-1.750 -0.1276 0.00974 0.00262 -0.0169 1.0000 1.0000
-1.500 -0.0993 0.00966 0.00235 -0.0177 1.0000 1.0000
-1.250 -0.0703 0.00961 0.00215 -0.0186 1.0000 1.0000
-1.000 -0.0412 0.00958 0.00201 -0.0194 1.0000 1.0000
-0.750 -0.0122 0.00957 0.00188 -0.0201 1.0000 1.0000
-0.500 0.0166 0.00957 0.00183 -0.0207 1.0000 1.0000
-0.250 0.0451 0.00959 0.00182 -0.0212 1.0000 1.0000
0.000 0.0734 0.00963 0.00185 -0.0216 1.0000 1.0000
0.250 0.1015 0.00967 0.00193 -0.0219 1.0000 1.0000
0.500 0.1293 0.00973 0.00206 -0.0222 1.0000 1.0000
0.750 0.1570 0.00980 0.00226 -0.0224 1.0000 1.0000
1.000 0.1845 0.00988 0.00247 -0.0226 1.0000 1.0000
1.250 0.2119 0.00997 0.00274 -0.0227 1.0000 1.0000
1.500 0.2391 0.01009 0.00307 -0.0228 1.0000 1.0000
1.750 0.2663 0.01021 0.00348 -0.0228 1.0000 1.0000
2.000 0.2936 0.01036 0.00405 -0.0227 1.0000 1.0000
2.250 0.3618 0.01597 0.00621 -0.0282 0.0699 1.0000
2.500 0.3888 0.01778 0.00801 -0.0275 0.0638 1.0000
2.750 0.4181 0.01969 0.01008 -0.0269 0.0615 1.0000
3.000 0.4467 0.02178 0.01226 -0.0266 0.0556 1.0000
3.250 0.4578 0.01218 0.00351 -0.0231 0.0527 1.0000
3.500 0.4871 0.01397 0.00604 -0.0217 0.0596 1.0000
3.750 0.5140 0.01713 0.00981 -0.0203 0.0783 1.0000
4.500 0.6005 0.03009 0.02500 -0.0196 0.1743 1.0000
4.750 0.6580 0.04894 0.04356 -0.0244 0.1395 1.0000
5.000 0.6766 0.05281 0.04763 -0.0245 0.1226 1.0000
5.500 0.7109 0.06110 0.05623 -0.0261 0.0957 1.0000
5.750 0.7267 0.06560 0.06098 -0.0284 0.0843 1.0000
6.000 0.7389 0.07062 0.06609 -0.0300 0.0775 1.0000
6.250 0.7528 0.07480 0.07041 -0.0321 0.0700 1.0000
6.500 0.7603 0.08228 0.07747 -0.0283 0.0669 1.0000
6.750 0.7708 0.08542 0.08116 -0.0369 0.0653 1.0000
7.000 0.7796 0.09051 0.08635 -0.0440 0.0620 1.0000
7.250 0.7853 0.09536 0.09123 -0.0481 0.0595 1.0000
7.500 0.7900 0.09989 0.09576 -0.0506 0.0573 1.0000
7.750 0.7992 0.10657 0.10228 -0.0388 0.0539 1.0000
8.000 0.8012 0.11099 0.10678 -0.0445 0.0537 1.0000
8.250 0.8003 0.11537 0.11117 -0.0511 0.0535 1.0000
8.500 0.7981 0.11944 0.11519 -0.0571 0.0533 1.0000
8.750 0.7961 0.12318 0.11887 -0.0624 0.0528 1.0000
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Polar data table (+)
Polar graphs
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