GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 493 AIRFOIL (goe493-il) Reynolds number: 500,000 Max Cl/Cd: 105.9 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe493-il-500000.txt Download as CSV file: xf-goe493-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 493 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.6573 0.11018 0.10726 -0.0638 1.0000 0.0171
-16.750 -0.7004 0.09796 0.09485 -0.0704 1.0000 0.0168
-16.500 -0.7283 0.08921 0.08594 -0.0752 1.0000 0.0167
-16.250 -0.7502 0.08197 0.07857 -0.0791 1.0000 0.0167
-16.000 -0.7685 0.07566 0.07213 -0.0825 1.0000 0.0167
-15.750 -0.7859 0.06983 0.06618 -0.0855 1.0000 0.0168
-15.500 -0.8017 0.06467 0.06090 -0.0879 1.0000 0.0169
-15.250 -0.8153 0.06010 0.05621 -0.0899 1.0000 0.0169
-15.000 -0.8283 0.05589 0.05189 -0.0914 1.0000 0.0170
-14.750 -0.8412 0.05200 0.04789 -0.0925 1.0000 0.0171
-14.500 -0.8517 0.04870 0.04450 -0.0930 1.0000 0.0172
-14.250 -0.8650 0.04558 0.04127 -0.0929 1.0000 0.0174
-14.000 -0.8789 0.04303 0.03864 -0.0917 1.0000 0.0174
-13.750 -0.8972 0.04076 0.03630 -0.0894 1.0000 0.0175
-13.500 -0.9022 0.03827 0.03369 -0.0898 0.9990 0.0176
-13.250 -0.8865 0.03542 0.03065 -0.0943 0.9960 0.0179
-13.000 -0.8766 0.03218 0.02730 -0.0977 0.9926 0.0184
-12.750 -0.8611 0.03004 0.02509 -0.1004 0.9882 0.0190
-12.500 -0.8403 0.02835 0.02331 -0.1032 0.9849 0.0196
-12.250 -0.8197 0.02681 0.02167 -0.1052 0.9818 0.0200
-12.000 -0.8046 0.02556 0.02030 -0.1053 0.9757 0.0206
-11.750 -0.7811 0.02436 0.01897 -0.1066 0.9726 0.0212
-11.500 -0.7543 0.02301 0.01749 -0.1084 0.9707 0.0219
-11.250 -0.7417 0.02169 0.01613 -0.1074 0.9637 0.0226
-11.000 -0.7152 0.02069 0.01507 -0.1086 0.9609 0.0236
-10.750 -0.6841 0.01986 0.01417 -0.1104 0.9591 0.0250
-10.500 -0.6510 0.01906 0.01326 -0.1124 0.9577 0.0261
-10.250 -0.6316 0.01791 0.01208 -0.1122 0.9529 0.0278
-10.000 -0.6080 0.01723 0.01136 -0.1121 0.9481 0.0293
-9.750 -0.5778 0.01661 0.01063 -0.1132 0.9451 0.0310
-9.500 -0.5502 0.01564 0.00965 -0.1141 0.9423 0.0342
-9.250 -0.5298 0.01523 0.00916 -0.1130 0.9363 0.0369
-9.000 -0.5072 0.01451 0.00845 -0.1126 0.9312 0.0420
-8.750 -0.4802 0.01386 0.00780 -0.1130 0.9276 0.0492
-8.500 -0.4589 0.01339 0.00735 -0.1120 0.9221 0.0582
-8.250 -0.4358 0.01299 0.00697 -0.1114 0.9166 0.0693
-8.000 -0.4082 0.01264 0.00662 -0.1116 0.9125 0.0806
-7.750 -0.3827 0.01236 0.00635 -0.1113 0.9079 0.0904
-7.500 -0.3596 0.01213 0.00610 -0.1105 0.9021 0.0979
-7.250 -0.3324 0.01190 0.00584 -0.1105 0.8976 0.1060
-7.000 -0.3053 0.01163 0.00555 -0.1105 0.8934 0.1138
-6.750 -0.2825 0.01148 0.00537 -0.1096 0.8874 0.1206
-6.500 -0.2570 0.01120 0.00509 -0.1092 0.8824 0.1287
-6.250 -0.2283 0.01102 0.00485 -0.1095 0.8784 0.1373
-6.000 -0.2065 0.01078 0.00466 -0.1084 0.8723 0.1471
-5.750 -0.1810 0.01055 0.00442 -0.1080 0.8670 0.1570
-5.500 -0.1533 0.01033 0.00418 -0.1081 0.8628 0.1694
-5.250 -0.1302 0.01012 0.00401 -0.1072 0.8568 0.1836
-5.000 -0.1052 0.00987 0.00380 -0.1067 0.8513 0.2018
-4.750 -0.0781 0.00962 0.00359 -0.1067 0.8468 0.2235
-4.500 -0.0550 0.00939 0.00345 -0.1058 0.8406 0.2476
-4.250 -0.0299 0.00916 0.00328 -0.1053 0.8349 0.2757
-4.000 -0.0028 0.00893 0.00312 -0.1053 0.8301 0.3082
-3.750 0.0203 0.00874 0.00303 -0.1044 0.8235 0.3385
-3.500 0.0463 0.00858 0.00292 -0.1040 0.8178 0.3672
-3.250 0.0728 0.00845 0.00283 -0.1037 0.8123 0.3942
-3.000 0.0976 0.00834 0.00278 -0.1031 0.8055 0.4187
-2.750 0.1252 0.00826 0.00269 -0.1030 0.7999 0.4407
-2.500 0.1505 0.00820 0.00266 -0.1024 0.7933 0.4591
-2.250 0.1767 0.00813 0.00260 -0.1021 0.7868 0.4768
-2.000 0.2038 0.00809 0.00256 -0.1019 0.7807 0.4941
-1.750 0.2291 0.00804 0.00253 -0.1013 0.7732 0.5098
-1.500 0.2572 0.00803 0.00247 -0.1013 0.7671 0.5245
-1.000 0.3088 0.00797 0.00243 -0.1003 0.7517 0.5542
-0.750 0.3331 0.00793 0.00243 -0.0995 0.7426 0.5694
-0.500 0.3596 0.00791 0.00240 -0.0991 0.7348 0.5858
-0.250 0.3841 0.00788 0.00241 -0.0984 0.7257 0.6007
0.000 0.4098 0.00787 0.00239 -0.0979 0.7174 0.6153
0.250 0.4345 0.00785 0.00240 -0.0972 0.7081 0.6305
0.500 0.4595 0.00784 0.00241 -0.0965 0.6995 0.6469
0.750 0.4844 0.00783 0.00244 -0.0959 0.6913 0.6655
1.000 0.5091 0.00783 0.00249 -0.0952 0.6836 0.6866
1.250 0.5335 0.00783 0.00254 -0.0944 0.6754 0.7096
1.500 0.5576 0.00783 0.00261 -0.0936 0.6677 0.7337
1.750 0.5817 0.00785 0.00267 -0.0927 0.6598 0.7589
2.000 0.6056 0.00785 0.00275 -0.0918 0.6526 0.7847
2.250 0.6291 0.00786 0.00283 -0.0908 0.6449 0.8116
2.500 0.6528 0.00787 0.00291 -0.0898 0.6379 0.8403
2.750 0.6769 0.00786 0.00300 -0.0889 0.6302 0.8731
3.000 0.7086 0.00790 0.00312 -0.0896 0.6229 0.9112
3.250 0.7569 0.00801 0.00329 -0.0941 0.6141 0.9447
3.500 0.8054 0.00817 0.00344 -0.0988 0.6057 0.9680
3.750 0.8484 0.00833 0.00356 -0.1022 0.5940 0.9847
4.000 0.8886 0.00849 0.00371 -0.1051 0.5813 1.0000
4.250 0.9050 0.00860 0.00379 -0.1028 0.5695 1.0000
4.500 0.9215 0.00875 0.00388 -0.1005 0.5568 1.0000
4.750 0.9391 0.00891 0.00399 -0.0985 0.5459 1.0000
5.000 0.9572 0.00904 0.00412 -0.0965 0.5344 1.0000
5.250 0.9743 0.00920 0.00426 -0.0943 0.5216 1.0000
5.500 0.9895 0.00939 0.00440 -0.0918 0.5056 1.0000
5.750 1.0039 0.00960 0.00456 -0.0891 0.4882 1.0000
6.000 1.0172 0.00983 0.00474 -0.0862 0.4712 1.0000
6.250 1.0271 0.01010 0.00494 -0.0826 0.4517 1.0000
6.500 1.0379 0.01040 0.00516 -0.0793 0.4291 1.0000
6.750 1.0468 0.01081 0.00545 -0.0757 0.4039 1.0000
7.000 1.0569 0.01125 0.00579 -0.0725 0.3773 1.0000
7.250 1.0660 0.01179 0.00620 -0.0692 0.3511 1.0000
7.500 1.0748 0.01239 0.00667 -0.0660 0.3259 1.0000
7.750 1.0861 0.01295 0.00714 -0.0632 0.3017 1.0000
8.000 1.0954 0.01362 0.00768 -0.0603 0.2729 1.0000
8.250 1.0972 0.01466 0.00844 -0.0564 0.2183 1.0000
8.500 1.0875 0.01637 0.00970 -0.0510 0.1478 1.0000
9.000 1.0853 0.01926 0.01208 -0.0435 0.0648 1.0000
9.250 1.0933 0.02031 0.01306 -0.0411 0.0532 1.0000
9.500 1.1035 0.02126 0.01401 -0.0391 0.0482 1.0000
9.750 1.1154 0.02214 0.01492 -0.0373 0.0454 1.0000
10.000 1.1248 0.02320 0.01599 -0.0354 0.0429 1.0000
10.250 1.1328 0.02438 0.01720 -0.0334 0.0410 1.0000
10.500 1.1446 0.02535 0.01823 -0.0319 0.0397 1.0000
10.750 1.1546 0.02646 0.01941 -0.0304 0.0384 1.0000
11.000 1.1632 0.02770 0.02070 -0.0288 0.0373 1.0000
11.250 1.1699 0.02913 0.02216 -0.0271 0.0362 1.0000
11.500 1.1705 0.03104 0.02412 -0.0251 0.0348 1.0000
11.750 1.1765 0.03263 0.02577 -0.0236 0.0340 1.0000
12.000 1.1854 0.03403 0.02725 -0.0224 0.0334 1.0000
12.250 1.1933 0.03554 0.02884 -0.0213 0.0326 1.0000
12.500 1.2001 0.03720 0.03055 -0.0201 0.0317 1.0000
12.750 1.2066 0.03891 0.03231 -0.0191 0.0308 1.0000
13.000 1.2116 0.04078 0.03422 -0.0181 0.0299 1.0000
13.250 1.2124 0.04307 0.03655 -0.0169 0.0292 1.0000
13.500 1.2117 0.04548 0.03901 -0.0155 0.0284 1.0000
13.750 1.2206 0.04714 0.04076 -0.0149 0.0279 1.0000
14.000 1.2283 0.04893 0.04263 -0.0143 0.0273 1.0000
14.250 1.2350 0.05083 0.04461 -0.0137 0.0266 1.0000
14.500 1.2413 0.05281 0.04665 -0.0132 0.0259 1.0000
14.750 1.2474 0.05483 0.04871 -0.0127 0.0252 1.0000
15.000 1.2526 0.05694 0.05085 -0.0123 0.0246 1.0000
15.250 1.2563 0.05905 0.05297 -0.0115 0.0239 1.0000
15.500 1.2612 0.06106 0.05504 -0.0105 0.0233 1.0000
15.750 1.2666 0.06335 0.05746 -0.0105 0.0228 1.0000
16.000 1.2718 0.06562 0.05983 -0.0103 0.0223 1.0000
16.250 1.2767 0.06794 0.06223 -0.0102 0.0218 1.0000
16.500 1.2808 0.07035 0.06473 -0.0102 0.0213 1.0000
16.750 1.2842 0.07296 0.06739 -0.0104 0.0207 1.0000
17.000 1.2878 0.07549 0.06997 -0.0106 0.0203 1.0000
17.250 1.2913 0.07802 0.07253 -0.0107 0.0198 1.0000
17.500 1.2967 0.07983 0.07437 -0.0096 0.0192 1.0000
17.750 1.2953 0.08332 0.07801 -0.0106 0.0189 1.0000
18.000 1.2955 0.08650 0.08132 -0.0111 0.0186 1.0000
18.250 1.2948 0.08987 0.08482 -0.0118 0.0183 1.0000
18.500 1.2939 0.09326 0.08833 -0.0125 0.0180 1.0000
18.750 1.2927 0.09674 0.09193 -0.0135 0.0176 1.0000
19.000 1.2906 0.10038 0.09568 -0.0145 0.0173 1.0000
19.250 1.2881 0.10418 0.09958 -0.0158 0.0170 1.0000
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