GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 550 AIRFOIL (goe550-il) Reynolds number: 200,000 Max Cl/Cd: 76.26 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe550-il-200000.txt Download as CSV file: xf-goe550-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 550 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6140 0.06364 0.05985 -0.0702 1.0000 0.0629
-11.000 -0.7509 0.04607 0.04205 -0.0814 1.0000 0.0592
-10.750 -0.7803 0.04160 0.03730 -0.0810 1.0000 0.0594
-10.500 -0.7941 0.03833 0.03371 -0.0797 1.0000 0.0601
-10.250 -0.7991 0.03573 0.03074 -0.0783 1.0000 0.0613
-10.000 -0.7980 0.03320 0.02791 -0.0769 1.0000 0.0626
-9.750 -0.7717 0.03200 0.02678 -0.0782 0.9975 0.0646
-9.500 -0.7355 0.03081 0.02543 -0.0814 0.9935 0.0675
-9.250 -0.7038 0.02897 0.02319 -0.0842 0.9880 0.0703
-9.000 -0.6700 0.02703 0.02103 -0.0871 0.9838 0.0731
-8.750 -0.6361 0.02632 0.02033 -0.0890 0.9787 0.0761
-8.500 -0.6011 0.02523 0.01898 -0.0913 0.9735 0.0797
-8.250 -0.5634 0.02380 0.01730 -0.0942 0.9702 0.0833
-8.000 -0.5335 0.02312 0.01666 -0.0950 0.9630 0.0869
-7.750 -0.4958 0.02231 0.01561 -0.0974 0.9588 0.0916
-7.500 -0.4597 0.02121 0.01445 -0.0995 0.9549 0.0965
-7.250 -0.4294 0.02063 0.01383 -0.1003 0.9476 0.1018
-7.000 -0.3918 0.01968 0.01275 -0.1025 0.9440 0.1086
-6.750 -0.3506 0.01908 0.01209 -0.1052 0.9416 0.1169
-6.500 -0.3258 0.01844 0.01147 -0.1049 0.9328 0.1243
-6.250 -0.2867 0.01785 0.01079 -0.1071 0.9293 0.1347
-6.000 -0.2446 0.01747 0.01037 -0.1099 0.9271 0.1459
-5.750 -0.2169 0.01722 0.01019 -0.1098 0.9190 0.1542
-5.500 -0.1775 0.01689 0.00980 -0.1120 0.9153 0.1644
-5.250 -0.1356 0.01671 0.00952 -0.1145 0.9125 0.1750
-5.000 -0.1026 0.01652 0.00940 -0.1154 0.9064 0.1827
-4.750 -0.0685 0.01629 0.00904 -0.1164 0.9002 0.1923
-4.500 -0.0293 0.01611 0.00891 -0.1183 0.8964 0.2012
-4.250 0.0011 0.01592 0.00866 -0.1186 0.8888 0.2101
-4.000 0.0353 0.01586 0.00856 -0.1195 0.8824 0.2201
-3.750 0.0723 0.01562 0.00832 -0.1211 0.8775 0.2293
-3.500 0.0985 0.01560 0.00817 -0.1205 0.8677 0.2387
-3.250 0.1341 0.01528 0.00789 -0.1217 0.8621 0.2466
-3.000 0.1596 0.01523 0.00772 -0.1210 0.8519 0.2548
-2.750 0.1932 0.01493 0.00742 -0.1218 0.8455 0.2621
-2.500 0.2184 0.01489 0.00732 -0.1211 0.8351 0.2698
-2.250 0.2506 0.01465 0.00700 -0.1216 0.8279 0.2769
-2.000 0.2757 0.01453 0.00689 -0.1208 0.8169 0.2830
-1.750 0.3041 0.01445 0.00666 -0.1206 0.8067 0.2895
-1.500 0.3326 0.01415 0.00636 -0.1204 0.7962 0.2952
-1.250 0.3582 0.01406 0.00625 -0.1196 0.7848 0.3015
-1.000 0.3873 0.01395 0.00602 -0.1195 0.7762 0.3081
-0.750 0.4128 0.01379 0.00592 -0.1189 0.7656 0.3140
-0.500 0.4401 0.01375 0.00582 -0.1185 0.7562 0.3217
-0.250 0.4671 0.01358 0.00568 -0.1181 0.7466 0.3291
0.000 0.4931 0.01352 0.00562 -0.1175 0.7366 0.3364
0.250 0.5214 0.01340 0.00545 -0.1173 0.7279 0.3429
0.500 0.5463 0.01330 0.00542 -0.1165 0.7171 0.3500
1.000 0.5994 0.01313 0.00528 -0.1155 0.6978 0.3655
1.250 0.6257 0.01310 0.00526 -0.1150 0.6882 0.3753
1.500 0.6523 0.01300 0.00522 -0.1145 0.6786 0.3873
1.750 0.6771 0.01295 0.00528 -0.1137 0.6678 0.4024
2.000 0.7037 0.01290 0.00528 -0.1133 0.6586 0.4244
2.250 0.7281 0.01281 0.00536 -0.1124 0.6479 0.4594
2.500 0.7516 0.01257 0.00543 -0.1114 0.6379 0.5369
2.750 0.7963 0.01169 0.00545 -0.1142 0.6273 1.0000
3.000 0.8200 0.01183 0.00554 -0.1132 0.6154 1.0000
3.250 0.8450 0.01199 0.00562 -0.1124 0.6045 1.0000
3.500 0.8712 0.01217 0.00568 -0.1118 0.5943 1.0000
3.750 0.8946 0.01234 0.00584 -0.1108 0.5821 1.0000
4.000 0.9187 0.01253 0.00597 -0.1099 0.5697 1.0000
4.250 0.9430 0.01274 0.00609 -0.1090 0.5573 1.0000
4.500 0.9673 0.01295 0.00621 -0.1080 0.5445 1.0000
4.750 0.9899 0.01316 0.00641 -0.1069 0.5310 1.0000
5.000 1.0131 0.01341 0.00663 -0.1058 0.5184 1.0000
5.250 1.0370 0.01369 0.00687 -0.1049 0.5069 1.0000
5.500 1.0609 0.01398 0.00707 -0.1040 0.4952 1.0000
5.750 1.0826 0.01422 0.00733 -0.1027 0.4821 1.0000
6.000 1.1050 0.01449 0.00761 -0.1016 0.4701 1.0000
6.250 1.1284 0.01481 0.00788 -0.1007 0.4599 1.0000
6.500 1.1507 0.01510 0.00818 -0.0996 0.4492 1.0000
6.750 1.1729 0.01541 0.00851 -0.0984 0.4388 1.0000
7.000 1.1957 0.01576 0.00880 -0.0974 0.4291 1.0000
7.250 1.2158 0.01603 0.00913 -0.0959 0.4177 1.0000
7.500 1.2352 0.01632 0.00943 -0.0943 0.4052 1.0000
7.750 1.2538 0.01663 0.00973 -0.0925 0.3925 1.0000
8.000 1.2719 0.01698 0.01004 -0.0908 0.3800 1.0000
8.250 1.2896 0.01732 0.01042 -0.0889 0.3681 1.0000
8.500 1.3068 0.01768 0.01082 -0.0870 0.3563 1.0000
8.750 1.3227 0.01808 0.01124 -0.0849 0.3441 1.0000
9.000 1.3365 0.01852 0.01166 -0.0824 0.3313 1.0000
9.250 1.3471 0.01895 0.01210 -0.0794 0.3176 1.0000
9.500 1.3566 0.01942 0.01260 -0.0762 0.3026 1.0000
9.750 1.3648 0.01997 0.01316 -0.0730 0.2860 1.0000
10.000 1.3723 0.02059 0.01381 -0.0698 0.2660 1.0000
10.250 1.3765 0.02140 0.01459 -0.0664 0.2405 1.0000
10.500 1.3764 0.02255 0.01560 -0.0627 0.2081 1.0000
10.750 1.3722 0.02410 0.01696 -0.0589 0.1744 1.0000
11.000 1.3666 0.02595 0.01862 -0.0554 0.1511 1.0000
11.250 1.3629 0.02786 0.02044 -0.0524 0.1346 1.0000
11.500 1.3586 0.02994 0.02247 -0.0496 0.1216 1.0000
11.750 1.3531 0.03227 0.02476 -0.0472 0.1103 1.0000
12.000 1.3514 0.03446 0.02696 -0.0452 0.0987 1.0000
12.250 1.3504 0.03671 0.02924 -0.0435 0.0881 1.0000
12.500 1.3485 0.03912 0.03167 -0.0420 0.0796 1.0000
12.750 1.3434 0.04195 0.03444 -0.0407 0.0735 1.0000
13.000 1.3444 0.04432 0.03689 -0.0397 0.0673 1.0000
13.250 1.3377 0.04751 0.04004 -0.0387 0.0635 1.0000
13.500 1.3386 0.05008 0.04272 -0.0380 0.0594 1.0000
13.750 1.3362 0.05305 0.04573 -0.0375 0.0563 1.0000
14.000 1.3325 0.05621 0.04889 -0.0369 0.0537 1.0000
14.250 1.3343 0.05891 0.05170 -0.0366 0.0509 1.0000
14.500 1.3346 0.06180 0.05463 -0.0363 0.0487 1.0000
14.750 1.3346 0.06463 0.05739 -0.0358 0.0466 1.0000
15.000 1.3380 0.06727 0.06017 -0.0355 0.0449 1.0000
15.250 1.3417 0.06991 0.06291 -0.0353 0.0432 1.0000
15.500 1.3456 0.07252 0.06556 -0.0352 0.0416 1.0000
15.750 1.3517 0.07477 0.06778 -0.0349 0.0402 1.0000
16.000 1.3589 0.07698 0.07004 -0.0343 0.0387 1.0000
16.250 1.3618 0.07991 0.07313 -0.0345 0.0376 1.0000
16.500 1.3651 0.08279 0.07614 -0.0348 0.0365 1.0000
16.750 1.3696 0.08550 0.07893 -0.0349 0.0355 1.0000
17.000 1.3765 0.08786 0.08132 -0.0349 0.0346 1.0000
17.250 1.3947 0.08877 0.08214 -0.0335 0.0333 1.0000
17.500 1.3901 0.09289 0.08650 -0.0346 0.0329 1.0000
17.750 1.3854 0.09713 0.09096 -0.0358 0.0325 1.0000
18.000 1.3800 0.10156 0.09561 -0.0373 0.0319 1.0000
18.250 1.3739 0.10617 0.10042 -0.0390 0.0314 1.0000
18.500 1.3682 0.11080 0.10523 -0.0409 0.0309 1.0000
18.750 1.3625 0.11543 0.11001 -0.0429 0.0304 1.0000
19.000 1.3572 0.12007 0.11480 -0.0450 0.0300 1.0000
19.250 1.3494 0.12522 0.12012 -0.0476 0.0296 1.0000
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