GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 585 AIRFOIL (goe585-il) Reynolds number: 50,000 Max Cl/Cd: 34.65 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe585-il-50000.txt Download as CSV file: xf-goe585-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 585 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3985 0.10346 0.09647 -0.0186 1.0000 0.2076
-8.000 -0.3856 0.09969 0.09270 -0.0173 1.0000 0.2180
-7.750 -0.3900 0.09720 0.09033 -0.0171 1.0000 0.2242
-7.500 -0.3948 0.09543 0.08866 -0.0161 1.0000 0.2350
-7.250 -0.3836 0.09159 0.08483 -0.0146 1.0000 0.2453
-7.000 -0.4117 0.09173 0.08519 -0.0156 1.0000 0.2516
-6.750 -0.3970 0.08757 0.08106 -0.0127 1.0000 0.2650
-6.500 -0.3904 0.08421 0.07776 -0.0110 1.0000 0.2752
-6.250 -0.3965 0.08194 0.07560 -0.0104 1.0000 0.2860
-5.750 -0.4042 0.07753 0.07137 -0.0086 1.0000 0.3142
-5.500 -0.4013 0.07472 0.06863 -0.0062 1.0000 0.3301
-5.250 -0.3942 0.07178 0.06576 -0.0025 1.0000 0.3499
-5.000 -0.4031 0.07019 0.06426 -0.0012 1.0000 0.3746
-4.750 -0.3975 0.06745 0.06157 0.0037 1.0000 0.4020
-3.000 -0.2302 0.03677 0.02809 -0.0349 1.0000 0.1739
-2.750 -0.2071 0.03426 0.02528 -0.0347 1.0000 0.1692
-2.500 -0.1816 0.03191 0.02240 -0.0348 1.0000 0.1650
-2.250 -0.1567 0.03010 0.02013 -0.0344 1.0000 0.1644
-2.000 -0.1336 0.02881 0.01860 -0.0338 1.0000 0.1696
-1.750 -0.1092 0.02769 0.01701 -0.0332 1.0000 0.1760
-1.500 -0.0861 0.02653 0.01584 -0.0327 1.0000 0.1835
-1.250 -0.0626 0.02557 0.01462 -0.0319 1.0000 0.1931
-1.000 -0.0394 0.02480 0.01384 -0.0311 1.0000 0.2122
-0.750 -0.0133 0.02408 0.01313 -0.0308 1.0000 0.2507
-0.500 0.0122 0.02312 0.01259 -0.0305 1.0000 0.3332
-0.250 0.0495 0.02002 0.01149 -0.0313 1.0000 1.0000
0.000 0.0691 0.02048 0.01148 -0.0305 1.0000 1.0000
0.250 0.0878 0.02098 0.01167 -0.0298 1.0000 1.0000
0.500 0.1059 0.02153 0.01199 -0.0292 1.0000 1.0000
0.750 0.1235 0.02213 0.01240 -0.0286 1.0000 1.0000
1.000 0.1406 0.02280 0.01293 -0.0281 1.0000 1.0000
1.250 0.1813 0.02391 0.01388 -0.0322 0.9889 1.0000
1.500 0.2464 0.02519 0.01501 -0.0404 0.9643 1.0000
1.750 0.3094 0.02612 0.01586 -0.0476 0.9387 1.0000
2.000 0.3746 0.02671 0.01642 -0.0546 0.9121 1.0000
2.250 0.4369 0.02687 0.01661 -0.0603 0.8840 1.0000
2.500 0.4969 0.02664 0.01646 -0.0650 0.8545 1.0000
2.750 0.5600 0.02595 0.01588 -0.0693 0.8249 1.0000
3.000 0.6165 0.02502 0.01506 -0.0718 0.7945 1.0000
3.250 0.6653 0.02409 0.01419 -0.0727 0.7624 1.0000
3.500 0.7024 0.02358 0.01370 -0.0719 0.7264 1.0000
3.750 0.7388 0.02318 0.01324 -0.0710 0.6912 1.0000
4.000 0.7706 0.02314 0.01308 -0.0698 0.6574 1.0000
4.250 0.7955 0.02350 0.01337 -0.0681 0.6242 1.0000
4.500 0.8214 0.02392 0.01372 -0.0667 0.5950 1.0000
4.750 0.8468 0.02444 0.01416 -0.0654 0.5687 1.0000
5.000 0.8697 0.02520 0.01492 -0.0641 0.5443 1.0000
5.250 0.8958 0.02589 0.01556 -0.0631 0.5237 1.0000
5.500 0.9184 0.02683 0.01654 -0.0620 0.5039 1.0000
5.750 0.9413 0.02786 0.01763 -0.0609 0.4862 1.0000
6.000 0.9642 0.02896 0.01879 -0.0599 0.4697 1.0000
6.250 0.9866 0.03013 0.02008 -0.0588 0.4542 1.0000
6.500 1.0082 0.03143 0.02149 -0.0577 0.4396 1.0000
6.750 1.0291 0.03275 0.02294 -0.0565 0.4245 1.0000
7.000 1.0493 0.03408 0.02439 -0.0552 0.4090 1.0000
7.250 1.0702 0.03523 0.02565 -0.0537 0.3917 1.0000
7.500 1.0935 0.03615 0.02655 -0.0524 0.3730 1.0000
7.750 1.1092 0.03752 0.02810 -0.0504 0.3545 1.0000
8.000 1.1246 0.03886 0.02963 -0.0484 0.3349 1.0000
8.250 1.1481 0.03964 0.03035 -0.0469 0.3129 1.0000
8.500 1.1583 0.04131 0.03232 -0.0443 0.2914 1.0000
8.750 1.1779 0.04208 0.03302 -0.0422 0.2654 1.0000
9.000 1.1962 0.04278 0.03360 -0.0400 0.2381 1.0000
9.250 1.2009 0.04442 0.03550 -0.0366 0.2145 1.0000
9.500 1.2126 0.04522 0.03622 -0.0339 0.1901 1.0000
9.750 1.2298 0.04564 0.03633 -0.0319 0.1662 1.0000
10.000 1.2335 0.04788 0.03881 -0.0288 0.1507 1.0000
10.250 1.2407 0.05008 0.04108 -0.0263 0.1374 1.0000
10.500 1.2402 0.05300 0.04435 -0.0234 0.1284 1.0000
10.750 1.2392 0.05662 0.04822 -0.0209 0.1227 1.0000
11.000 1.2244 0.06075 0.05278 -0.0178 0.1198 1.0000
11.250 1.2401 0.06290 0.05478 -0.0166 0.1118 1.0000
11.500 1.2175 0.06712 0.05936 -0.0134 0.1113 1.0000
11.750 1.1916 0.07152 0.06402 -0.0109 0.1113 1.0000
12.000 1.1657 0.07656 0.06926 -0.0100 0.1117 1.0000
12.250 1.1398 0.08236 0.07521 -0.0105 0.1122 1.0000
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Polar data table (+)
Polar graphs
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