SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8020-010-88 (sd8020-il) Reynolds number: 500,000 Max Cl/Cd: 63.05 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8020-il-500000.txt Download as CSV file: xf-sd8020-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SD8020-010-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.8684 0.10177 0.09906 -0.0080 1.0000 0.0111
-14.750 -0.9008 0.09065 0.08781 -0.0145 1.0000 0.0110
-14.500 -0.9306 0.08050 0.07752 -0.0209 1.0000 0.0108
-14.250 -0.9482 0.07288 0.06975 -0.0261 1.0000 0.0109
-14.000 -0.9708 0.06508 0.06179 -0.0311 1.0000 0.0107
-13.750 -0.9893 0.05833 0.05487 -0.0355 1.0000 0.0107
-13.500 -1.0063 0.05246 0.04881 -0.0390 1.0000 0.0107
-13.250 -1.0194 0.04777 0.04392 -0.0412 1.0000 0.0108
-13.000 -1.0304 0.04385 0.03983 -0.0422 1.0000 0.0107
-12.750 -1.0388 0.04069 0.03649 -0.0423 1.0000 0.0108
-12.500 -1.0447 0.03817 0.03378 -0.0414 1.0000 0.0110
-12.250 -1.0477 0.03619 0.03161 -0.0398 1.0000 0.0111
-12.000 -1.0578 0.03350 0.02869 -0.0371 1.0000 0.0113
-11.750 -1.0651 0.03098 0.02598 -0.0338 1.0000 0.0115
-11.500 -1.0686 0.02900 0.02386 -0.0302 1.0000 0.0118
-11.250 -1.0646 0.02754 0.02229 -0.0273 1.0000 0.0121
-11.000 -1.0548 0.02642 0.02110 -0.0252 1.0000 0.0125
-10.750 -1.0431 0.02536 0.01992 -0.0231 1.0000 0.0129
-10.500 -1.0301 0.02434 0.01879 -0.0212 1.0000 0.0135
-10.250 -1.0149 0.02353 0.01788 -0.0194 1.0000 0.0143
-10.000 -0.9992 0.02268 0.01690 -0.0177 1.0000 0.0148
-9.750 -0.9888 0.02112 0.01519 -0.0152 1.0000 0.0157
-9.500 -0.9764 0.01992 0.01392 -0.0129 1.0000 0.0166
-9.250 -0.9602 0.01912 0.01307 -0.0111 1.0000 0.0175
-9.000 -0.9429 0.01840 0.01227 -0.0093 1.0000 0.0185
-8.750 -0.9249 0.01773 0.01150 -0.0077 1.0000 0.0195
-8.500 -0.9079 0.01696 0.01064 -0.0058 1.0000 0.0205
-8.250 -0.8931 0.01598 0.00963 -0.0037 1.0000 0.0226
-8.000 -0.8739 0.01545 0.00906 -0.0021 1.0000 0.0244
-7.750 -0.8539 0.01497 0.00851 -0.0007 1.0000 0.0262
-7.500 -0.8371 0.01417 0.00765 0.0013 1.0000 0.0291
-7.250 -0.8173 0.01368 0.00715 0.0028 1.0000 0.0326
-7.000 -0.7981 0.01311 0.00655 0.0045 1.0000 0.0375
-6.750 -0.7778 0.01267 0.00611 0.0059 1.0000 0.0444
-6.500 -0.7583 0.01214 0.00563 0.0074 1.0000 0.0568
-6.250 -0.7378 0.01174 0.00526 0.0088 1.0000 0.0686
-6.000 -0.7169 0.01139 0.00494 0.0101 1.0000 0.0798
-5.750 -0.6962 0.01104 0.00463 0.0114 1.0000 0.0923
-5.500 -0.6752 0.01072 0.00436 0.0127 1.0000 0.1059
-5.250 -0.6544 0.01041 0.00411 0.0140 1.0000 0.1221
-5.000 -0.6338 0.01010 0.00387 0.0153 1.0000 0.1400
-4.750 -0.6129 0.00984 0.00368 0.0166 1.0000 0.1607
-4.500 -0.5925 0.00955 0.00351 0.0179 1.0000 0.1870
-4.250 -0.5675 0.00927 0.00337 0.0182 0.9993 0.2179
-4.000 -0.5299 0.00898 0.00321 0.0158 0.9959 0.2539
-3.750 -0.4925 0.00871 0.00308 0.0136 0.9925 0.2915
-3.500 -0.4561 0.00841 0.00293 0.0116 0.9882 0.3308
-3.250 -0.4176 0.00813 0.00281 0.0092 0.9846 0.3713
-3.000 -0.3818 0.00785 0.00268 0.0074 0.9800 0.4133
-2.750 -0.3461 0.00756 0.00255 0.0056 0.9746 0.4569
-2.500 -0.3073 0.00728 0.00243 0.0033 0.9710 0.5009
-2.250 -0.2751 0.00701 0.00231 0.0024 0.9634 0.5427
-2.000 -0.2380 0.00673 0.00220 0.0005 0.9584 0.5851
-1.750 -0.2064 0.00648 0.00208 -0.0001 0.9497 0.6228
-1.500 -0.1715 0.00625 0.00197 -0.0014 0.9420 0.6601
-1.250 -0.1411 0.00604 0.00188 -0.0016 0.9293 0.6933
-1.000 -0.1099 0.00587 0.00180 -0.0020 0.9149 0.7246
-0.750 -0.0799 0.00574 0.00173 -0.0020 0.8979 0.7539
-0.500 -0.0526 0.00566 0.00169 -0.0015 0.8768 0.7813
-0.250 -0.0259 0.00561 0.00166 -0.0008 0.8551 0.8070
0.000 0.0000 0.00559 0.00166 0.0000 0.8314 0.8314
0.250 0.0258 0.00561 0.00166 0.0009 0.8069 0.8550
0.500 0.0525 0.00566 0.00169 0.0016 0.7809 0.8770
0.750 0.0798 0.00574 0.00173 0.0021 0.7537 0.8979
1.000 0.1099 0.00587 0.00180 0.0020 0.7249 0.9149
1.250 0.1411 0.00604 0.00188 0.0016 0.6937 0.9293
1.500 0.1716 0.00625 0.00197 0.0014 0.6603 0.9420
1.750 0.2065 0.00648 0.00208 0.0001 0.6233 0.9497
2.000 0.2381 0.00673 0.00219 -0.0005 0.5850 0.9584
2.250 0.2752 0.00701 0.00231 -0.0024 0.5427 0.9635
2.500 0.3074 0.00727 0.00243 -0.0033 0.5018 0.9710
2.750 0.3462 0.00756 0.00255 -0.0057 0.4566 0.9746
3.000 0.3818 0.00785 0.00268 -0.0074 0.4133 0.9800
3.250 0.4174 0.00814 0.00281 -0.0091 0.3707 0.9846
3.500 0.4559 0.00840 0.00293 -0.0116 0.3307 0.9881
3.750 0.4924 0.00871 0.00308 -0.0136 0.2918 0.9925
4.000 0.5300 0.00898 0.00321 -0.0159 0.2538 0.9959
4.250 0.5679 0.00927 0.00337 -0.0183 0.2183 0.9993
4.500 0.5924 0.00955 0.00351 -0.0179 0.1868 1.0000
4.750 0.6129 0.00983 0.00368 -0.0166 0.1612 1.0000
5.000 0.6337 0.01010 0.00387 -0.0153 0.1401 1.0000
5.250 0.6544 0.01041 0.00411 -0.0140 0.1220 1.0000
5.500 0.6752 0.01072 0.00436 -0.0127 0.1061 1.0000
5.750 0.6961 0.01104 0.00463 -0.0114 0.0922 1.0000
6.000 0.7169 0.01139 0.00494 -0.0101 0.0798 1.0000
6.250 0.7377 0.01175 0.00527 -0.0088 0.0683 1.0000
6.500 0.7583 0.01214 0.00563 -0.0074 0.0567 1.0000
6.750 0.7780 0.01264 0.00609 -0.0059 0.0451 1.0000
7.000 0.7982 0.01310 0.00655 -0.0045 0.0378 1.0000
7.250 0.8173 0.01369 0.00715 -0.0028 0.0326 1.0000
7.500 0.8371 0.01417 0.00765 -0.0013 0.0291 1.0000
7.750 0.8537 0.01500 0.00853 0.0007 0.0263 1.0000
8.000 0.8739 0.01545 0.00906 0.0021 0.0246 1.0000
8.250 0.8932 0.01598 0.00963 0.0036 0.0228 1.0000
8.500 0.9086 0.01689 0.01056 0.0057 0.0207 1.0000
8.750 0.9248 0.01775 0.01153 0.0077 0.0196 1.0000
9.000 0.9430 0.01839 0.01226 0.0093 0.0186 1.0000
9.250 0.9604 0.01911 0.01306 0.0111 0.0176 1.0000
9.500 0.9768 0.01988 0.01388 0.0128 0.0166 1.0000
9.750 0.9884 0.02118 0.01525 0.0152 0.0156 1.0000
10.000 0.9998 0.02259 0.01681 0.0176 0.0148 1.0000
10.250 1.0162 0.02334 0.01767 0.0192 0.0141 1.0000
10.500 1.0301 0.02435 0.01881 0.0212 0.0135 1.0000
10.750 1.0440 0.02524 0.01978 0.0230 0.0129 1.0000
11.000 1.0552 0.02637 0.02104 0.0251 0.0125 1.0000
11.250 1.0651 0.02747 0.02220 0.0272 0.0120 1.0000
11.500 1.0689 0.02898 0.02382 0.0301 0.0117 1.0000
11.750 1.0620 0.03135 0.02636 0.0340 0.0114 1.0000
12.000 1.0524 0.03414 0.02938 0.0374 0.0112 1.0000
12.250 1.0490 0.03605 0.03147 0.0398 0.0111 1.0000
12.500 1.0463 0.03801 0.03361 0.0413 0.0110 1.0000
12.750 1.0391 0.04076 0.03654 0.0422 0.0109 1.0000
13.000 1.0300 0.04400 0.03998 0.0422 0.0108 1.0000
13.250 1.0217 0.04753 0.04369 0.0411 0.0106 1.0000
13.500 1.0073 0.05242 0.04878 0.0389 0.0106 1.0000
13.750 0.9912 0.05815 0.05469 0.0355 0.0107 1.0000
14.000 0.9731 0.06477 0.06148 0.0313 0.0108 1.0000
14.250 0.9519 0.07254 0.06943 0.0260 0.0107 1.0000
14.500 0.9289 0.08102 0.07805 0.0204 0.0109 1.0000
14.750 0.9011 0.09092 0.08809 0.0141 0.0109 1.0000
15.000 0.8697 0.10175 0.09904 0.0078 0.0111 1.0000
15.250 0.7897 0.12825 0.12585 -0.0071 0.0120 1.0000
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Polar data table (+)
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