NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il) Reynolds number: 200,000 Max Cl/Cd: 32.54 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20403-il-200000.txt Download as CSV file: xf-sc20403-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6892 0.12317 0.11962 0.0334 1.0000 0.0201
-9.500 -0.6853 0.11933 0.11580 0.0317 1.0000 0.0207
-9.250 -0.6815 0.11551 0.11200 0.0297 1.0000 0.0212
-9.000 -0.6775 0.11173 0.10824 0.0276 1.0000 0.0217
-8.750 -0.6735 0.10802 0.10455 0.0251 1.0000 0.0223
-8.500 -0.6694 0.10436 0.10092 0.0222 1.0000 0.0227
-8.250 -0.6651 0.10070 0.09729 0.0187 1.0000 0.0230
-8.000 -0.6606 0.09691 0.09346 0.0148 1.0000 0.0233
-7.750 -0.6514 0.09242 0.08899 0.0086 1.0000 0.0234
-7.500 -0.6382 0.08733 0.08387 0.0012 1.0000 0.0236
-7.250 -0.6240 0.08244 0.07892 -0.0044 1.0000 0.0237
-7.000 -0.6090 0.07766 0.07404 -0.0091 1.0000 0.0238
-6.750 -0.5930 0.07298 0.06924 -0.0130 1.0000 0.0239
-6.500 -0.5819 0.06599 0.06216 -0.0168 1.0000 0.0243
-6.250 -0.5751 0.05973 0.05592 -0.0183 1.0000 0.0256
-6.000 -0.5600 0.05554 0.05168 -0.0199 1.0000 0.0271
-5.750 -0.5395 0.05126 0.04725 -0.0224 1.0000 0.0289
-5.500 -0.5152 0.04693 0.04269 -0.0250 1.0000 0.0314
-5.250 -0.4808 0.04416 0.03940 -0.0272 1.0000 0.0359
-5.000 -0.4547 0.03871 0.03352 -0.0297 1.0000 0.0378
-4.750 -0.4331 0.03453 0.02935 -0.0310 1.0000 0.0408
-4.500 -0.3982 0.03505 0.02910 -0.0310 1.0000 0.0496
-4.250 -0.3757 0.02825 0.02240 -0.0333 1.0000 0.0549
-4.000 -0.3456 0.02555 0.01911 -0.0342 1.0000 0.0661
-3.750 -0.3168 0.02311 0.01644 -0.0350 1.0000 0.0806
-3.500 -0.2774 0.01976 0.01227 -0.0320 1.0000 0.0232
-3.250 -0.2475 0.01657 0.00873 -0.0320 1.0000 0.0201
-3.000 -0.2185 0.01457 0.00648 -0.0316 1.0000 0.0189
-2.750 -0.1898 0.01296 0.00476 -0.0313 1.0000 0.0199
-2.500 -0.1614 0.01187 0.00367 -0.0315 1.0000 0.0310
-2.250 -0.1309 0.01067 0.00238 -0.0319 1.0000 0.0423
-2.000 -0.1189 0.00726 0.00209 -0.0282 1.0000 0.8534
-1.750 -0.1134 0.00692 0.00185 -0.0219 1.0000 0.9329
-1.500 -0.0878 0.00666 0.00149 -0.0211 1.0000 1.0000
-1.250 -0.0577 0.00663 0.00132 -0.0219 1.0000 1.0000
-1.000 -0.0282 0.00662 0.00117 -0.0226 1.0000 1.0000
-0.750 0.0008 0.00662 0.00109 -0.0231 1.0000 1.0000
-0.500 0.0295 0.00663 0.00105 -0.0235 1.0000 1.0000
-0.250 0.0579 0.00665 0.00105 -0.0238 1.0000 1.0000
0.000 0.0860 0.00667 0.00109 -0.0240 1.0000 1.0000
0.250 0.1139 0.00670 0.00117 -0.0242 1.0000 1.0000
0.500 0.1417 0.00674 0.00129 -0.0243 1.0000 1.0000
0.750 0.1694 0.00678 0.00148 -0.0243 1.0000 1.0000
1.000 0.1970 0.00684 0.00169 -0.0243 1.0000 1.0000
1.250 0.2245 0.00690 0.00199 -0.0243 1.0000 1.0000
1.500 0.2776 0.01181 0.00361 -0.0291 0.0319 1.0000
1.750 0.3044 0.01314 0.00492 -0.0288 0.0220 1.0000
2.000 0.3325 0.01434 0.00621 -0.0284 0.0184 1.0000
2.250 0.3611 0.01624 0.00832 -0.0277 0.0188 1.0000
2.500 0.3901 0.01872 0.01111 -0.0270 0.0210 1.0000
3.000 0.4566 0.02504 0.01856 -0.0236 0.0667 1.0000
3.250 0.4834 0.02759 0.02144 -0.0234 0.0551 1.0000
3.500 0.5078 0.03082 0.02493 -0.0235 0.0504 1.0000
3.750 0.5361 0.03341 0.02814 -0.0231 0.0416 1.0000
4.000 0.5586 0.03670 0.03155 -0.0233 0.0378 1.0000
4.250 0.5754 0.04403 0.03900 -0.0243 0.0357 1.0000
4.500 0.6102 0.04464 0.04029 -0.0237 0.0318 1.0000
4.750 0.6346 0.04862 0.04455 -0.0245 0.0291 1.0000
5.000 0.6560 0.05272 0.04884 -0.0255 0.0270 1.0000
5.250 0.6735 0.05683 0.05308 -0.0265 0.0253 1.0000
5.500 0.6843 0.06185 0.05810 -0.0270 0.0240 1.0000
5.750 0.6911 0.07035 0.06668 -0.0293 0.0231 1.0000
6.000 0.7083 0.07489 0.07140 -0.0313 0.0230 1.0000
6.250 0.7250 0.07947 0.07613 -0.0339 0.0229 1.0000
6.500 0.7412 0.08405 0.08084 -0.0372 0.0227 1.0000
6.750 0.7569 0.08876 0.08565 -0.0420 0.0225 1.0000
7.000 0.7710 0.09357 0.09053 -0.0480 0.0221 1.0000
7.250 0.7814 0.09840 0.09538 -0.0543 0.0217 1.0000
7.500 0.7858 0.10285 0.09981 -0.0593 0.0214 1.0000
7.750 0.7881 0.10705 0.10407 -0.0629 0.0210 1.0000
8.000 0.7906 0.11118 0.10817 -0.0658 0.0206 1.0000
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Polar data table (+)
Polar graphs
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