GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 492 AIRFOIL (goe492-il) Reynolds number: 50,000 Max Cl/Cd: 31.13 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe492-il-50000.txt Download as CSV file: xf-goe492-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 492 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4151 0.09792 0.09135 -0.0226 1.0000 0.2107
-7.250 -0.4077 0.09411 0.08759 -0.0212 1.0000 0.2186
-7.000 -0.4258 0.09391 0.08758 -0.0217 1.0000 0.2252
-6.750 -0.4149 0.08964 0.08327 -0.0193 1.0000 0.2360
-6.500 -0.4158 0.08688 0.08061 -0.0185 1.0000 0.2440
-6.250 -0.4274 0.08583 0.07969 -0.0204 1.0000 0.2537
-6.000 -0.4239 0.08279 0.07671 -0.0188 1.0000 0.2662
-5.750 -0.4192 0.07940 0.07337 -0.0165 1.0000 0.2783
-5.500 -0.4169 0.07641 0.07044 -0.0151 1.0000 0.2905
-5.000 -0.4154 0.07104 0.06519 -0.0145 1.0000 0.3225
-4.750 -0.4134 0.06852 0.06271 -0.0134 1.0000 0.3487
-4.500 -0.4105 0.06553 0.05978 -0.0095 1.0000 0.3767
-3.750 -0.2639 0.04182 0.03410 -0.0555 1.0000 0.1570
-3.500 -0.2305 0.03658 0.02824 -0.0584 1.0000 0.1412
-3.250 -0.1997 0.03283 0.02386 -0.0601 1.0000 0.1402
-3.000 -0.1705 0.02999 0.02043 -0.0609 1.0000 0.1474
-2.750 -0.1415 0.02749 0.01737 -0.0611 1.0000 0.1512
-2.500 -0.1147 0.02585 0.01540 -0.0609 1.0000 0.1645
-2.250 -0.0881 0.02451 0.01379 -0.0605 1.0000 0.1796
-2.000 -0.0623 0.02335 0.01241 -0.0598 1.0000 0.1943
-1.750 -0.0371 0.02266 0.01163 -0.0591 1.0000 0.2225
-1.500 -0.0106 0.02192 0.01090 -0.0587 1.0000 0.2786
-1.250 0.0155 0.01834 0.00950 -0.0571 1.0000 0.6570
-1.000 0.0372 0.01775 0.00877 -0.0559 1.0000 1.0000
-0.750 0.0600 0.01805 0.00860 -0.0555 1.0000 1.0000
-0.500 0.0817 0.01840 0.00858 -0.0551 1.0000 1.0000
-0.250 0.1028 0.01877 0.00867 -0.0546 1.0000 1.0000
0.000 0.1234 0.01919 0.00885 -0.0542 1.0000 1.0000
0.250 0.1435 0.01966 0.00907 -0.0537 1.0000 1.0000
0.500 0.1631 0.02017 0.00941 -0.0532 1.0000 1.0000
0.750 0.1824 0.02072 0.00982 -0.0528 1.0000 1.0000
1.000 0.2013 0.02131 0.01030 -0.0524 1.0000 1.0000
1.250 0.2199 0.02196 0.01085 -0.0520 1.0000 1.0000
1.500 0.2383 0.02264 0.01147 -0.0517 1.0000 1.0000
1.750 0.2563 0.02338 0.01215 -0.0514 1.0000 1.0000
2.000 0.2741 0.02415 0.01289 -0.0511 1.0000 1.0000
2.250 0.2917 0.02498 0.01370 -0.0509 1.0000 1.0000
2.500 0.3091 0.02585 0.01458 -0.0507 1.0000 1.0000
2.750 0.3413 0.02706 0.01584 -0.0535 0.9927 1.0000
3.000 0.3843 0.02845 0.01736 -0.0582 0.9788 1.0000
3.250 0.4245 0.02974 0.01878 -0.0622 0.9650 1.0000
3.500 0.4626 0.03098 0.02017 -0.0657 0.9510 1.0000
3.750 0.4990 0.03218 0.02156 -0.0687 0.9369 1.0000
4.000 0.5341 0.03336 0.02304 -0.0715 0.9226 1.0000
4.250 0.5679 0.03454 0.02448 -0.0739 0.9083 1.0000
4.500 0.6009 0.03572 0.02596 -0.0761 0.8937 1.0000
4.750 0.6352 0.03687 0.02747 -0.0783 0.8783 1.0000
5.000 0.8019 0.02576 0.01380 -0.0662 0.1364 1.0000
5.250 0.8182 0.02788 0.01590 -0.0638 0.1191 1.0000
5.500 0.8479 0.03008 0.01811 -0.0629 0.1073 1.0000
5.750 0.8868 0.03256 0.02067 -0.0633 0.0947 1.0000
6.000 0.9277 0.03549 0.02371 -0.0638 0.0910 1.0000
6.250 0.9617 0.03859 0.02719 -0.0633 0.0914 1.0000
6.500 0.9906 0.04191 0.03106 -0.0620 0.0943 1.0000
6.750 1.0156 0.04565 0.03525 -0.0606 0.0974 1.0000
7.000 1.0361 0.04952 0.03954 -0.0590 0.0990 1.0000
7.250 1.0557 0.05415 0.04443 -0.0577 0.1005 1.0000
7.500 1.0648 0.05698 0.04834 -0.0542 0.1102 1.0000
7.750 1.0777 0.06182 0.05380 -0.0521 0.1250 1.0000
8.000 1.0956 0.06858 0.06111 -0.0512 0.1542 1.0000
8.250 1.0725 0.07318 0.06667 -0.0493 0.1760 1.0000
8.500 1.0559 0.08076 0.07471 -0.0508 0.2098 1.0000
8.750 1.0172 0.08654 0.08062 -0.0518 0.2172 1.0000
9.000 0.9701 0.09475 0.08881 -0.0573 0.2386 1.0000
9.250 0.9168 0.10673 0.10061 -0.0702 0.2801 1.0000
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Polar data table (+)
Polar graphs
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