GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 494 AIRFOIL (goe494-il) Reynolds number: 200,000 Max Cl/Cd: 97.04 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe494-il-200000.txt Download as CSV file: xf-goe494-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 494 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3581 0.09359 0.09028 -0.0234 1.0000 0.0289
-7.000 -0.3688 0.09247 0.08922 -0.0205 1.0000 0.0293
-6.750 -0.3778 0.09108 0.08790 -0.0182 1.0000 0.0297
-6.500 -0.3830 0.08932 0.08620 -0.0171 1.0000 0.0302
-6.250 -0.3872 0.08747 0.08440 -0.0164 1.0000 0.0308
-6.000 -0.3765 0.08446 0.08142 -0.0202 0.9982 0.0320
-5.750 -0.3202 0.07920 0.07607 -0.0400 0.9917 0.0339
-5.500 -0.2747 0.07367 0.07046 -0.0529 0.9865 0.0342
-5.250 -0.2572 0.06668 0.06348 -0.0565 0.9835 0.0356
-5.000 -0.2398 0.06393 0.06073 -0.0567 0.9782 0.0378
-4.750 -0.2007 0.05960 0.05632 -0.0652 0.9737 0.0430
-4.500 -0.1289 0.05074 0.04721 -0.0862 0.9710 0.0480
-4.250 -0.1096 0.04875 0.04521 -0.0861 0.9656 0.0509
-4.000 -0.0441 0.04129 0.03737 -0.1019 0.9622 0.0613
-3.750 0.0043 0.03721 0.03295 -0.1101 0.9595 0.0744
-3.500 0.0330 0.03543 0.03128 -0.1115 0.9573 0.0797
-3.250 0.0837 0.03164 0.02685 -0.1196 0.9531 0.1017
-3.000 0.1100 0.02961 0.02499 -0.1204 0.9485 0.1080
-2.750 0.1492 0.02769 0.02290 -0.1243 0.9459 0.1331
-2.500 0.1895 0.02602 0.02106 -0.1279 0.9440 0.1594
-2.250 0.2517 0.01876 0.01208 -0.1329 0.9439 0.0674
-2.000 0.2850 0.01767 0.01070 -0.1339 0.9391 0.0677
-1.750 0.3218 0.01649 0.00922 -0.1354 0.9347 0.0647
-1.500 0.3624 0.01548 0.00804 -0.1376 0.9321 0.0628
-1.250 0.4039 0.01462 0.00714 -0.1402 0.9302 0.0629
-1.000 0.4337 0.01413 0.00668 -0.1405 0.9242 0.0644
-0.750 0.4679 0.01367 0.00624 -0.1418 0.9200 0.0672
-0.500 0.5050 0.01329 0.00586 -0.1435 0.9172 0.0718
-0.250 0.5371 0.01299 0.00558 -0.1443 0.9126 0.0798
0.000 0.5670 0.01276 0.00539 -0.1447 0.9068 0.0936
0.250 0.6011 0.01187 0.00546 -0.1462 0.9035 0.4001
0.500 0.6313 0.01063 0.00542 -0.1464 0.9000 1.0000
0.750 0.6579 0.01076 0.00546 -0.1461 0.8928 1.0000
1.000 0.6908 0.01073 0.00536 -0.1468 0.8889 1.0000
1.250 0.7168 0.01088 0.00551 -0.1464 0.8819 1.0000
1.500 0.7476 0.01083 0.00544 -0.1466 0.8760 1.0000
1.750 0.7745 0.01082 0.00543 -0.1461 0.8670 1.0000
2.000 0.8059 0.01063 0.00522 -0.1461 0.8595 1.0000
2.250 0.8316 0.01059 0.00521 -0.1451 0.8484 1.0000
2.500 0.8585 0.01036 0.00501 -0.1440 0.8340 1.0000
2.750 0.8828 0.01000 0.00462 -0.1420 0.8094 1.0000
3.000 0.9080 0.00984 0.00443 -0.1405 0.7867 1.0000
3.250 0.9329 0.00979 0.00434 -0.1390 0.7601 1.0000
3.500 0.9558 0.00985 0.00430 -0.1370 0.7194 1.0000
3.750 0.9751 0.01005 0.00432 -0.1344 0.6480 1.0000
4.000 0.9758 0.01189 0.00465 -0.1287 0.3725 1.0000
4.250 0.9733 0.01540 0.00623 -0.1242 0.0642 1.0000
4.500 0.9922 0.01663 0.00747 -0.1224 0.0477 1.0000
4.750 1.0129 0.01757 0.00854 -0.1209 0.0430 1.0000
5.000 1.0313 0.01881 0.00983 -0.1190 0.0391 1.0000
5.250 1.0472 0.02078 0.01181 -0.1169 0.0350 1.0000
5.500 1.0696 0.02207 0.01317 -0.1156 0.0336 1.0000
5.750 1.0940 0.02374 0.01490 -0.1146 0.0325 1.0000
6.000 1.1210 0.02577 0.01704 -0.1138 0.0323 1.0000
6.250 1.1477 0.02769 0.01913 -0.1130 0.0310 1.0000
6.500 1.1734 0.02976 0.02141 -0.1122 0.0296 1.0000
6.750 1.2003 0.03327 0.02535 -0.1109 0.0321 1.0000
12.000 0.9487 0.14182 0.13921 -0.0956 0.0477 1.0000
12.250 0.9348 0.14922 0.14661 -0.1012 0.0473 1.0000
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Polar data table (+)
Polar graphs
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