NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il) Reynolds number: 50,000 Max Cl/Cd: 19.06 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20404-il-50000-n5.txt Download as CSV file: xf-sc20404-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6728 0.11786 0.11099 0.0208 1.0000 0.0951
-9.000 -0.6823 0.11545 0.10871 0.0149 1.0000 0.0984
-8.750 -0.6763 0.11044 0.10375 0.0145 1.0000 0.1001
-8.500 -0.6668 0.10595 0.09926 0.0153 1.0000 0.1032
-8.250 -0.6641 0.10208 0.09544 0.0135 1.0000 0.1067
-8.000 -0.6736 0.09832 0.09181 0.0011 1.0000 0.1122
-7.750 -0.6610 0.09352 0.08702 0.0058 1.0000 0.1149
-7.500 -0.5630 0.07388 0.06760 -0.0070 1.0000 0.0543
-7.000 -0.6220 0.07418 0.06742 -0.0119 1.0000 0.0525
-6.750 -0.6062 0.06810 0.06112 -0.0169 1.0000 0.0436
-6.500 -0.5915 0.06290 0.05576 -0.0199 1.0000 0.0410
-6.250 -0.5732 0.05740 0.04999 -0.0233 1.0000 0.0386
-6.000 -0.5504 0.05172 0.04382 -0.0268 1.0000 0.0361
-5.500 -0.4970 0.04305 0.03385 -0.0303 1.0000 0.0337
-5.250 -0.4708 0.03893 0.02920 -0.0314 1.0000 0.0336
-4.750 -0.4176 0.03162 0.02090 -0.0330 1.0000 0.0380
-4.500 -0.3888 0.02936 0.01805 -0.0331 1.0000 0.0451
-4.250 -0.3601 0.02692 0.01509 -0.0325 1.0000 0.0468
-4.000 -0.3347 0.02442 0.01246 -0.0315 1.0000 0.0497
-3.750 -0.3095 0.02267 0.01051 -0.0302 1.0000 0.0540
-3.500 -0.2843 0.02124 0.00876 -0.0290 1.0000 0.0599
-3.250 -0.2578 0.01985 0.00734 -0.0291 1.0000 0.0823
-3.000 -0.2290 0.01785 0.00568 -0.0298 1.0000 0.1456
-2.750 -0.2256 0.01502 0.00571 -0.0236 1.0000 0.7426
-2.500 -0.2266 0.01450 0.00545 -0.0139 1.0000 0.8982
-2.250 -0.1813 0.01391 0.00425 -0.0161 1.0000 1.0000
-2.000 -0.1566 0.01376 0.00374 -0.0162 1.0000 1.0000
-1.750 -0.1305 0.01364 0.00332 -0.0165 1.0000 1.0000
-1.500 -0.1037 0.01355 0.00299 -0.0169 1.0000 1.0000
-1.250 -0.0766 0.01349 0.00273 -0.0172 1.0000 1.0000
-1.000 -0.0494 0.01345 0.00254 -0.0176 1.0000 1.0000
-0.750 -0.0221 0.01343 0.00236 -0.0178 1.0000 1.0000
-0.500 0.0051 0.01343 0.00227 -0.0181 1.0000 1.0000
-0.250 0.0322 0.01345 0.00225 -0.0183 1.0000 1.0000
0.000 0.0592 0.01347 0.00228 -0.0184 1.0000 1.0000
0.250 0.0861 0.01352 0.00236 -0.0185 1.0000 1.0000
0.500 0.1129 0.01358 0.00251 -0.0186 1.0000 1.0000
0.750 0.1396 0.01365 0.00275 -0.0186 1.0000 1.0000
1.000 0.1661 0.01374 0.00299 -0.0186 1.0000 1.0000
1.250 0.1927 0.01384 0.00331 -0.0186 1.0000 1.0000
1.500 0.2191 0.01397 0.00371 -0.0185 1.0000 1.0000
1.750 0.2456 0.01411 0.00419 -0.0185 1.0000 1.0000
2.000 0.2720 0.01427 0.00478 -0.0183 1.0000 1.0000
2.250 0.3439 0.01845 0.00617 -0.0248 0.1169 1.0000
2.500 0.3707 0.02010 0.00769 -0.0245 0.0759 1.0000
2.750 0.3980 0.02151 0.00917 -0.0243 0.0571 1.0000
3.000 0.4277 0.02313 0.01114 -0.0239 0.0514 1.0000
3.250 0.4566 0.02515 0.01339 -0.0233 0.0476 1.0000
3.500 0.4853 0.02792 0.01638 -0.0228 0.0453 1.0000
3.750 0.5148 0.03063 0.01966 -0.0221 0.0442 1.0000
4.000 0.5435 0.03321 0.02293 -0.0216 0.0391 1.0000
4.250 0.5668 0.03616 0.02607 -0.0218 0.0332 1.0000
4.750 0.6155 0.04417 0.03538 -0.0214 0.0329 1.0000
5.000 0.6397 0.04787 0.03962 -0.0212 0.0335 1.0000
5.250 0.6642 0.05260 0.04510 -0.0216 0.0356 1.0000
5.500 0.6847 0.05786 0.05082 -0.0227 0.0378 1.0000
5.750 0.7023 0.06309 0.05636 -0.0242 0.0403 1.0000
6.000 0.7170 0.06819 0.06165 -0.0255 0.0429 1.0000
7.000 0.7798 0.09323 0.08742 -0.0374 0.1120 1.0000
7.250 0.7786 0.09790 0.09213 -0.0452 0.1056 1.0000
7.500 0.7831 0.10246 0.09669 -0.0481 0.1020 1.0000
7.750 0.7924 0.10729 0.10151 -0.0469 0.0989 1.0000
8.000 0.7966 0.11263 0.10680 -0.0483 0.0973 1.0000
8.250 0.7854 0.11589 0.10996 -0.0569 0.0943 1.0000
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Polar data table (+)
Polar graphs
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