NASA SC(2)-0010 AIRFOIL (sc20010-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0010 AIRFOIL (sc20010-il) Reynolds number: 500,000 Max Cl/Cd: 56.59 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20010-il-500000-n5.txt Download as CSV file: xf-sc20010-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0010 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0992 0.09342 0.09043 0.0022 1.0000 0.0127
-15.500 -1.1528 0.07625 0.07292 -0.0093 1.0000 0.0126
-15.250 -1.1800 0.06622 0.06265 -0.0164 1.0000 0.0125
-15.000 -1.2009 0.05879 0.05502 -0.0211 1.0000 0.0125
-14.750 -1.2170 0.05308 0.04912 -0.0240 1.0000 0.0126
-14.500 -1.2291 0.04849 0.04436 -0.0255 1.0000 0.0126
-14.250 -1.2374 0.04473 0.04043 -0.0262 1.0000 0.0127
-14.000 -1.2422 0.04165 0.03721 -0.0262 1.0000 0.0128
-13.750 -1.2444 0.03908 0.03450 -0.0256 1.0000 0.0129
-13.500 -1.2442 0.03692 0.03220 -0.0246 1.0000 0.0130
-13.250 -1.2424 0.03504 0.03019 -0.0231 1.0000 0.0132
-13.000 -1.2393 0.03339 0.02841 -0.0213 1.0000 0.0133
-12.750 -1.2350 0.03193 0.02681 -0.0190 1.0000 0.0134
-12.500 -1.2278 0.03060 0.02535 -0.0169 1.0000 0.0135
-12.250 -1.2164 0.02932 0.02394 -0.0154 1.0000 0.0137
-12.000 -1.2031 0.02809 0.02258 -0.0140 1.0000 0.0138
-11.750 -1.1881 0.02693 0.02129 -0.0127 1.0000 0.0140
-11.500 -1.1718 0.02583 0.02006 -0.0116 1.0000 0.0142
-11.250 -1.1543 0.02478 0.01888 -0.0105 1.0000 0.0144
-11.000 -1.1358 0.02380 0.01777 -0.0096 1.0000 0.0147
-10.750 -1.1164 0.02287 0.01673 -0.0087 1.0000 0.0149
-10.500 -1.0962 0.02199 0.01574 -0.0079 1.0000 0.0151
-10.250 -1.0752 0.02118 0.01482 -0.0071 1.0000 0.0153
-10.000 -1.0538 0.02041 0.01394 -0.0064 1.0000 0.0155
-9.750 -1.0331 0.01949 0.01297 -0.0056 1.0000 0.0159
-9.500 -1.0108 0.01879 0.01222 -0.0051 1.0000 0.0164
-9.250 -0.9876 0.01818 0.01156 -0.0046 1.0000 0.0168
-9.000 -0.9640 0.01761 0.01094 -0.0041 1.0000 0.0174
-8.750 -0.9402 0.01704 0.01031 -0.0036 1.0000 0.0179
-8.500 -0.9162 0.01648 0.00969 -0.0031 1.0000 0.0184
-8.250 -0.8919 0.01596 0.00910 -0.0027 1.0000 0.0189
-8.000 -0.8677 0.01540 0.00850 -0.0023 1.0000 0.0195
-7.750 -0.8432 0.01490 0.00799 -0.0019 1.0000 0.0204
-7.500 -0.8182 0.01446 0.00753 -0.0015 1.0000 0.0214
-7.250 -0.7930 0.01405 0.00708 -0.0012 1.0000 0.0226
-7.000 -0.7679 0.01364 0.00665 -0.0008 1.0000 0.0239
-6.750 -0.7426 0.01326 0.00628 -0.0005 1.0000 0.0258
-6.500 -0.7171 0.01294 0.00593 -0.0002 1.0000 0.0281
-6.250 -0.6919 0.01259 0.00562 0.0002 1.0000 0.0309
-6.000 -0.6649 0.01232 0.00533 0.0002 0.9978 0.0338
-5.750 -0.6328 0.01198 0.00503 -0.0009 0.9880 0.0373
-5.500 -0.6006 0.01173 0.00475 -0.0020 0.9769 0.0404
-5.250 -0.5690 0.01143 0.00447 -0.0030 0.9641 0.0439
-5.000 -0.5385 0.01120 0.00422 -0.0036 0.9492 0.0474
-4.750 -0.5101 0.01098 0.00398 -0.0037 0.9325 0.0511
-4.500 -0.4836 0.01076 0.00376 -0.0034 0.9156 0.0559
-4.250 -0.4575 0.01059 0.00355 -0.0030 0.9003 0.0609
-4.000 -0.4315 0.01038 0.00334 -0.0026 0.8863 0.0674
-3.750 -0.4050 0.01020 0.00314 -0.0022 0.8737 0.0741
-3.500 -0.3782 0.01002 0.00296 -0.0020 0.8624 0.0836
-3.250 -0.3514 0.00980 0.00278 -0.0018 0.8526 0.0988
-3.000 -0.3244 0.00958 0.00261 -0.0017 0.8434 0.1193
-2.750 -0.2974 0.00933 0.00245 -0.0016 0.8356 0.1483
-2.500 -0.2705 0.00902 0.00230 -0.0015 0.8278 0.1900
-2.250 -0.2437 0.00871 0.00215 -0.0015 0.8206 0.2435
-2.000 -0.2173 0.00826 0.00199 -0.0014 0.8131 0.3205
-1.750 -0.1915 0.00773 0.00182 -0.0013 0.8066 0.4235
-1.500 -0.1656 0.00718 0.00168 -0.0011 0.8011 0.5318
-1.250 -0.1395 0.00685 0.00170 -0.0008 0.7952 0.6308
-1.000 -0.1118 0.00681 0.00171 -0.0006 0.7881 0.6679
-0.750 -0.0839 0.00676 0.00172 -0.0005 0.7776 0.6954
-0.500 -0.0562 0.00674 0.00173 -0.0002 0.7672 0.7199
-0.250 -0.0280 0.00673 0.00173 -0.0002 0.7589 0.7333
0.000 0.0000 0.00672 0.00174 0.0000 0.7471 0.7471
0.250 0.0280 0.00673 0.00173 0.0002 0.7334 0.7590
0.500 0.0561 0.00674 0.00173 0.0002 0.7197 0.7674
0.750 0.0839 0.00676 0.00172 0.0005 0.6958 0.7776
1.000 0.1117 0.00681 0.00171 0.0006 0.6679 0.7881
1.250 0.1394 0.00685 0.00170 0.0008 0.6304 0.7952
1.500 0.1656 0.00718 0.00168 0.0011 0.5317 0.8011
1.750 0.1914 0.00774 0.00182 0.0013 0.4226 0.8066
2.000 0.2173 0.00826 0.00199 0.0014 0.3211 0.8130
2.250 0.2437 0.00871 0.00215 0.0015 0.2435 0.8206
2.500 0.2705 0.00902 0.00230 0.0015 0.1900 0.8278
2.750 0.2974 0.00933 0.00245 0.0016 0.1482 0.8356
3.000 0.3244 0.00958 0.00261 0.0017 0.1192 0.8434
3.250 0.3514 0.00980 0.00278 0.0018 0.0988 0.8526
3.500 0.3782 0.01002 0.00296 0.0020 0.0836 0.8624
3.750 0.4050 0.01020 0.00314 0.0022 0.0741 0.8737
4.000 0.4315 0.01038 0.00334 0.0026 0.0674 0.8864
4.250 0.4575 0.01059 0.00355 0.0030 0.0609 0.9003
4.500 0.4836 0.01076 0.00376 0.0034 0.0559 0.9157
4.750 0.5101 0.01098 0.00398 0.0037 0.0511 0.9325
5.000 0.5385 0.01120 0.00422 0.0036 0.0475 0.9493
5.250 0.5690 0.01143 0.00447 0.0030 0.0439 0.9641
5.500 0.6006 0.01173 0.00475 0.0020 0.0404 0.9769
5.750 0.6329 0.01198 0.00503 0.0009 0.0372 0.9881
6.000 0.6649 0.01232 0.00533 -0.0002 0.0338 0.9979
6.250 0.6919 0.01259 0.00562 -0.0002 0.0309 1.0000
6.500 0.7171 0.01294 0.00593 0.0002 0.0281 1.0000
6.750 0.7426 0.01326 0.00628 0.0005 0.0258 1.0000
7.000 0.7679 0.01364 0.00665 0.0008 0.0239 1.0000
7.250 0.7930 0.01405 0.00708 0.0012 0.0226 1.0000
7.500 0.8182 0.01446 0.00753 0.0015 0.0214 1.0000
7.750 0.8432 0.01490 0.00799 0.0019 0.0204 1.0000
8.000 0.8678 0.01540 0.00850 0.0023 0.0195 1.0000
8.250 0.8919 0.01596 0.00910 0.0027 0.0189 1.0000
8.500 0.9163 0.01648 0.00969 0.0031 0.0184 1.0000
8.750 0.9402 0.01704 0.01031 0.0036 0.0179 1.0000
9.000 0.9640 0.01761 0.01093 0.0041 0.0174 1.0000
9.250 0.9876 0.01818 0.01156 0.0045 0.0168 1.0000
9.500 1.0108 0.01879 0.01222 0.0050 0.0164 1.0000
9.750 1.0331 0.01949 0.01297 0.0056 0.0159 1.0000
10.000 1.0538 0.02041 0.01395 0.0064 0.0155 1.0000
10.250 1.0753 0.02118 0.01481 0.0071 0.0153 1.0000
10.500 1.0963 0.02199 0.01574 0.0079 0.0151 1.0000
10.750 1.1165 0.02286 0.01672 0.0087 0.0149 1.0000
11.000 1.1359 0.02379 0.01777 0.0096 0.0147 1.0000
11.250 1.1544 0.02478 0.01888 0.0105 0.0144 1.0000
11.500 1.1719 0.02583 0.02006 0.0116 0.0142 1.0000
11.750 1.1883 0.02693 0.02129 0.0127 0.0140 1.0000
12.000 1.2033 0.02809 0.02258 0.0140 0.0138 1.0000
12.250 1.2166 0.02932 0.02394 0.0153 0.0137 1.0000
12.500 1.2281 0.03060 0.02535 0.0169 0.0135 1.0000
12.750 1.2353 0.03193 0.02681 0.0190 0.0134 1.0000
13.000 1.2398 0.03338 0.02840 0.0212 0.0133 1.0000
13.250 1.2430 0.03504 0.03019 0.0230 0.0132 1.0000
13.500 1.2449 0.03690 0.03218 0.0245 0.0130 1.0000
13.750 1.2453 0.03905 0.03446 0.0255 0.0129 1.0000
14.000 1.2433 0.04161 0.03716 0.0261 0.0128 1.0000
14.250 1.2384 0.04470 0.04041 0.0261 0.0127 1.0000
14.500 1.2302 0.04846 0.04433 0.0254 0.0126 1.0000
14.750 1.2178 0.05309 0.04913 0.0238 0.0126 1.0000
15.000 1.2015 0.05885 0.05508 0.0209 0.0125 1.0000
15.250 1.1811 0.06623 0.06266 0.0162 0.0125 1.0000
15.500 1.1537 0.07634 0.07302 0.0090 0.0125 1.0000
15.750 1.1013 0.09328 0.09028 -0.0023 0.0127 1.0000
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