NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il) Reynolds number: 100,000 Max Cl/Cd: 23.96 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20503-il-100000-n5.txt Download as CSV file: xf-sc20503-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0503 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5411 0.08861 0.08394 0.0054 1.0000 0.0312
-8.250 -0.5413 0.08454 0.07990 0.0041 1.0000 0.0318
-8.000 -0.5421 0.08044 0.07585 0.0026 1.0000 0.0323
-7.750 -0.5435 0.07634 0.07178 0.0010 1.0000 0.0327
-7.500 -0.5445 0.07201 0.06750 -0.0015 1.0000 0.0332
-7.250 -0.5420 0.06705 0.06255 -0.0058 1.0000 0.0337
-7.000 -0.5367 0.06170 0.05719 -0.0106 1.0000 0.0342
-6.750 -0.5285 0.05627 0.05169 -0.0151 1.0000 0.0351
-6.500 -0.5085 0.05150 0.04647 -0.0242 1.0000 0.0388
-6.250 -0.4924 0.04680 0.04150 -0.0267 1.0000 0.0390
-6.000 -0.4810 0.04002 0.03468 -0.0284 1.0000 0.0398
-5.750 -0.4673 0.03443 0.02915 -0.0278 1.0000 0.0212
-5.500 -0.4452 0.02928 0.02369 -0.0302 1.0000 0.0181
-5.000 -0.4039 0.03653 0.02950 -0.0337 1.0000 0.0134
-4.750 -0.3758 0.03185 0.02440 -0.0355 1.0000 0.0128
-4.500 -0.3457 0.02825 0.02030 -0.0366 1.0000 0.0124
-4.250 -0.3153 0.02517 0.01670 -0.0373 1.0000 0.0122
-4.000 -0.2852 0.02252 0.01353 -0.0375 1.0000 0.0120
-3.750 -0.2558 0.02016 0.01048 -0.0374 1.0000 0.0116
-3.500 -0.2277 0.01831 0.00835 -0.0371 1.0000 0.0149
-3.250 -0.2004 0.01691 0.00684 -0.0371 1.0000 0.0219
-3.000 -0.1723 0.01543 0.00524 -0.0369 1.0000 0.0244
-2.750 -0.1431 0.01411 0.00375 -0.0371 1.0000 0.0319
-2.500 -0.1125 0.01143 0.00256 -0.0389 1.0000 0.3890
-2.250 -0.1132 0.01008 0.00287 -0.0305 1.0000 0.8516
-2.000 -0.1025 0.00944 0.00232 -0.0251 1.0000 1.0000
-1.750 -0.0731 0.00940 0.00201 -0.0258 1.0000 1.0000
-1.500 -0.0440 0.00938 0.00178 -0.0264 1.0000 1.0000
-1.250 -0.0153 0.00937 0.00157 -0.0268 1.0000 1.0000
-1.000 0.0131 0.00938 0.00146 -0.0272 1.0000 1.0000
-0.750 0.0413 0.00939 0.00140 -0.0275 1.0000 1.0000
-0.500 0.0692 0.00941 0.00140 -0.0278 1.0000 1.0000
-0.250 0.0969 0.00945 0.00145 -0.0279 1.0000 1.0000
0.000 0.1246 0.00949 0.00156 -0.0281 1.0000 1.0000
0.250 0.1520 0.00954 0.00171 -0.0282 1.0000 1.0000
0.500 0.1795 0.00961 0.00198 -0.0282 1.0000 1.0000
0.750 0.2068 0.00968 0.00224 -0.0282 1.0000 1.0000
1.000 0.2341 0.00977 0.00261 -0.0281 1.0000 1.0000
1.250 0.3004 0.01410 0.00372 -0.0353 0.0374 1.0000
1.500 0.3271 0.01532 0.00509 -0.0348 0.0248 1.0000
1.750 0.3537 0.01672 0.00664 -0.0341 0.0220 1.0000
2.000 0.3810 0.01807 0.00809 -0.0337 0.0163 1.0000
2.250 0.4085 0.01997 0.01018 -0.0333 0.0116 1.0000
2.500 0.4372 0.02210 0.01265 -0.0327 0.0112 1.0000
2.750 0.4656 0.02466 0.01598 -0.0321 0.0119 1.0000
3.000 0.4935 0.02744 0.01925 -0.0315 0.0121 1.0000
3.250 0.5204 0.03059 0.02288 -0.0310 0.0123 1.0000
3.500 0.5458 0.03423 0.02699 -0.0307 0.0127 1.0000
4.000 0.6012 0.04032 0.03397 -0.0294 0.0159 1.0000
4.250 0.6277 0.04503 0.03914 -0.0292 0.0194 1.0000
4.500 0.6452 0.05181 0.04582 -0.0289 0.0392 1.0000
5.000 0.6957 0.05925 0.05428 -0.0315 0.0335 1.0000
5.250 0.7149 0.06390 0.05915 -0.0333 0.0322 1.0000
5.500 0.7321 0.06864 0.06406 -0.0355 0.0310 1.0000
5.750 0.7471 0.07344 0.06899 -0.0379 0.0299 1.0000
6.000 0.7600 0.07825 0.07390 -0.0404 0.0290 1.0000
6.250 0.7706 0.08305 0.07876 -0.0427 0.0282 1.0000
6.500 0.7789 0.08783 0.08359 -0.0446 0.0275 1.0000
6.750 0.7844 0.09278 0.08855 -0.0454 0.0269 1.0000
7.000 0.7833 0.09957 0.09530 -0.0448 0.0260 1.0000
7.250 0.7889 0.10503 0.10074 -0.0478 0.0259 1.0000
7.750 0.7996 0.11451 0.11041 -0.0552 0.0258 1.0000
8.000 0.8024 0.11899 0.11487 -0.0590 0.0258 1.0000
8.250 0.8053 0.12335 0.11920 -0.0621 0.0258 1.0000
8.500 0.8079 0.12761 0.12343 -0.0651 0.0257 1.0000
8.750 0.8107 0.13179 0.12759 -0.0678 0.0257 1.0000
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Polar data table (+)
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