NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il) Reynolds number: 100,000 Max Cl/Cd: 21.77 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20403-il-100000-n5.txt Download as CSV file: xf-sc20403-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6766 0.10928 0.10439 0.0212 1.0000 0.0275
-8.500 -0.6723 0.10512 0.10025 0.0206 1.0000 0.0281
-8.250 -0.6685 0.10115 0.09631 0.0193 1.0000 0.0287
-8.000 -0.6649 0.09723 0.09242 0.0175 1.0000 0.0292
-7.750 -0.6612 0.09323 0.08846 0.0150 1.0000 0.0297
-7.500 -0.6544 0.08881 0.08407 0.0111 1.0000 0.0303
-7.250 -0.6452 0.08403 0.07930 0.0061 1.0000 0.0310
-7.000 -0.6338 0.07905 0.07429 0.0008 1.0000 0.0317
-6.750 -0.6202 0.07399 0.06918 -0.0044 1.0000 0.0325
-6.500 -0.6043 0.06891 0.06401 -0.0093 1.0000 0.0335
-6.250 -0.5859 0.06383 0.05880 -0.0138 1.0000 0.0345
-6.000 -0.5512 0.06042 0.05472 -0.0213 1.0000 0.0389
-5.750 -0.5292 0.05612 0.05013 -0.0234 1.0000 0.0390
-5.500 -0.5169 0.04827 0.04251 -0.0235 1.0000 0.0209
-5.250 -0.4895 0.04311 0.03699 -0.0260 1.0000 0.0175
-4.750 -0.4279 0.03600 0.02894 -0.0276 1.0000 0.0133
-4.500 -0.4000 0.03170 0.02419 -0.0290 1.0000 0.0128
-4.250 -0.3704 0.02815 0.02014 -0.0299 1.0000 0.0125
-4.000 -0.3404 0.02509 0.01656 -0.0304 1.0000 0.0123
-3.750 -0.3106 0.02244 0.01342 -0.0305 1.0000 0.0122
-3.500 -0.2816 0.02007 0.01033 -0.0302 1.0000 0.0116
-3.250 -0.2535 0.01849 0.00849 -0.0298 1.0000 0.0141
-3.000 -0.2264 0.01682 0.00672 -0.0299 1.0000 0.0214
-2.750 -0.1985 0.01536 0.00512 -0.0296 1.0000 0.0241
-2.500 -0.1696 0.01407 0.00365 -0.0297 1.0000 0.0314
-2.250 -0.1451 0.01058 0.00277 -0.0301 1.0000 0.6326
-2.000 -0.1442 0.00993 0.00279 -0.0219 1.0000 0.8663
-1.750 -0.1241 0.00939 0.00223 -0.0188 1.0000 1.0000
-1.500 -0.0953 0.00934 0.00191 -0.0193 1.0000 1.0000
-1.250 -0.0668 0.00931 0.00169 -0.0198 1.0000 1.0000
-1.000 -0.0384 0.00929 0.00147 -0.0201 1.0000 1.0000
-0.750 -0.0104 0.00928 0.00135 -0.0204 1.0000 1.0000
-0.500 0.0175 0.00929 0.00129 -0.0206 1.0000 1.0000
-0.250 0.0451 0.00930 0.00128 -0.0208 1.0000 1.0000
0.000 0.0727 0.00932 0.00131 -0.0209 1.0000 1.0000
0.250 0.1001 0.00935 0.00141 -0.0210 1.0000 1.0000
0.500 0.1274 0.00940 0.00155 -0.0210 1.0000 1.0000
0.750 0.1546 0.00945 0.00180 -0.0210 1.0000 1.0000
1.000 0.1818 0.00951 0.00204 -0.0209 1.0000 1.0000
1.250 0.2088 0.00959 0.00238 -0.0208 1.0000 1.0000
1.500 0.2682 0.01347 0.00321 -0.0267 0.0550 1.0000
1.750 0.2950 0.01482 0.00453 -0.0263 0.0258 1.0000
2.000 0.3219 0.01606 0.00597 -0.0256 0.0224 1.0000
2.250 0.3491 0.01749 0.00752 -0.0251 0.0183 1.0000
2.500 0.3761 0.01923 0.00939 -0.0249 0.0120 1.0000
2.750 0.4047 0.02120 0.01169 -0.0243 0.0112 1.0000
3.000 0.4332 0.02368 0.01492 -0.0237 0.0118 1.0000
3.250 0.4615 0.02640 0.01814 -0.0232 0.0120 1.0000
3.500 0.4890 0.02947 0.02172 -0.0227 0.0122 1.0000
3.750 0.5153 0.03296 0.02568 -0.0224 0.0126 1.0000
4.000 0.5392 0.03726 0.03040 -0.0225 0.0131 1.0000
4.500 0.5974 0.04396 0.03803 -0.0216 0.0176 1.0000
4.750 0.6217 0.04878 0.04321 -0.0222 0.0210 1.0000
5.250 0.6562 0.06049 0.05510 -0.0232 0.0384 1.0000
5.500 0.6880 0.06354 0.05876 -0.0269 0.0332 1.0000
5.750 0.7064 0.06839 0.06378 -0.0295 0.0322 1.0000
6.000 0.7226 0.07329 0.06882 -0.0325 0.0312 1.0000
6.250 0.7368 0.07820 0.07383 -0.0357 0.0303 1.0000
6.500 0.7488 0.08309 0.07879 -0.0391 0.0295 1.0000
6.750 0.7588 0.08793 0.08368 -0.0424 0.0288 1.0000
7.000 0.7670 0.09270 0.08847 -0.0455 0.0282 1.0000
7.250 0.7735 0.09742 0.09320 -0.0480 0.0276 1.0000
7.500 0.7784 0.10216 0.09794 -0.0495 0.0270 1.0000
7.750 0.7800 0.10771 0.10347 -0.0484 0.0263 1.0000
8.000 0.7797 0.11418 0.11002 -0.0500 0.0259 1.0000
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Polar data table (+)
Polar graphs
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