GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 492 AIRFOIL (goe492-il) Reynolds number: 100,000 Max Cl/Cd: 57.2 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe492-il-100000.txt Download as CSV file: xf-goe492-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4136 0.09375 0.08902 -0.0312 1.0000 0.0752
-7.500 -0.4256 0.09237 0.08778 -0.0339 1.0000 0.0760
-7.250 -0.4307 0.09014 0.08561 -0.0398 1.0000 0.0765
-7.000 -0.4223 0.08501 0.08053 -0.0309 1.0000 0.0791
-6.750 -0.4197 0.08236 0.07792 -0.0291 1.0000 0.0822
-6.500 -0.4204 0.07974 0.07535 -0.0298 1.0000 0.0852
-6.250 -0.4179 0.07675 0.07228 -0.0421 1.0000 0.0898
-6.000 -0.4172 0.07259 0.06822 -0.0379 1.0000 0.0915
-5.750 -0.4135 0.07012 0.06580 -0.0338 1.0000 0.0948
-5.500 -0.3957 0.06577 0.06120 -0.0453 1.0000 0.1041
-5.250 -0.3947 0.06280 0.05836 -0.0392 1.0000 0.1067
-5.000 -0.3758 0.05888 0.05422 -0.0451 1.0000 0.1184
-4.750 -0.3712 0.05684 0.05232 -0.0403 1.0000 0.1266
-4.500 -0.3524 0.05326 0.04856 -0.0443 1.0000 0.1463
-4.250 -0.3398 0.05067 0.04597 -0.0432 1.0000 0.1611
-4.000 -0.3243 0.04805 0.04332 -0.0429 1.0000 0.1768
-3.500 -0.2184 0.02889 0.02160 -0.0592 1.0000 0.0748
-3.250 -0.1893 0.02619 0.01823 -0.0595 1.0000 0.0756
-3.000 -0.1622 0.02363 0.01529 -0.0597 1.0000 0.0800
-2.750 -0.1354 0.02183 0.01312 -0.0594 1.0000 0.0833
-2.500 -0.1099 0.02053 0.01144 -0.0589 1.0000 0.0928
-2.250 -0.0855 0.01957 0.01030 -0.0583 1.0000 0.1022
-2.000 -0.0619 0.01862 0.00936 -0.0577 1.0000 0.1133
-1.750 -0.0388 0.01792 0.00867 -0.0571 1.0000 0.1252
-1.500 -0.0159 0.01736 0.00816 -0.0565 1.0000 0.1390
-1.250 0.0069 0.01691 0.00791 -0.0559 1.0000 0.1699
-1.000 0.0303 0.01630 0.00804 -0.0557 1.0000 0.3678
-0.750 0.0542 0.01580 0.00823 -0.0556 1.0000 0.5358
-0.500 0.0990 0.01512 0.00832 -0.0590 0.9924 1.0000
-0.250 0.1443 0.01568 0.00858 -0.0631 0.9838 1.0000
0.000 0.1862 0.01612 0.00877 -0.0665 0.9739 1.0000
0.250 0.2285 0.01655 0.00903 -0.0699 0.9646 1.0000
0.500 0.2739 0.01696 0.00931 -0.0739 0.9563 1.0000
0.750 0.3115 0.01724 0.00951 -0.0763 0.9454 1.0000
1.000 0.3496 0.01753 0.00974 -0.0787 0.9350 1.0000
1.250 0.3913 0.01778 0.00997 -0.0817 0.9263 1.0000
1.500 0.4318 0.01797 0.01017 -0.0844 0.9169 1.0000
1.750 0.4664 0.01818 0.01044 -0.0859 0.9060 1.0000
2.000 0.5037 0.01835 0.01067 -0.0879 0.8962 1.0000
2.250 0.5493 0.01835 0.01078 -0.0913 0.8891 1.0000
2.500 0.5831 0.01847 0.01101 -0.0925 0.8778 1.0000
2.750 0.6210 0.01845 0.01119 -0.0941 0.8670 1.0000
3.000 0.6614 0.01822 0.01115 -0.0958 0.8560 1.0000
3.250 0.7045 0.01782 0.01099 -0.0977 0.8461 1.0000
3.500 0.7413 0.01694 0.01035 -0.0973 0.8253 1.0000
3.750 0.7801 0.01392 0.00743 -0.0923 0.7537 1.0000
4.000 0.7899 0.01381 0.00626 -0.0843 0.5218 1.0000
4.250 0.7791 0.01804 0.00779 -0.0779 0.0949 1.0000
4.500 0.7965 0.01942 0.00911 -0.0757 0.0721 1.0000
4.750 0.8123 0.02084 0.01052 -0.0734 0.0618 1.0000
5.000 0.8307 0.02227 0.01203 -0.0713 0.0579 1.0000
5.250 0.8534 0.02405 0.01379 -0.0699 0.0553 1.0000
5.500 0.8819 0.02625 0.01597 -0.0693 0.0532 1.0000
5.750 0.9120 0.02947 0.01926 -0.0693 0.0493 1.0000
6.000 0.9415 0.03251 0.02254 -0.0688 0.0495 1.0000
6.250 0.9700 0.03438 0.02479 -0.0674 0.0521 1.0000
6.500 0.9968 0.03838 0.02946 -0.0654 0.0602 1.0000
6.750 1.0319 0.04431 0.03605 -0.0633 0.0887 1.0000
9.000 1.1122 0.08755 0.08240 -0.0471 0.1143 1.0000
9.250 1.0810 0.08903 0.08431 -0.0441 0.1137 1.0000
9.500 1.0505 0.09184 0.08728 -0.0422 0.1132 1.0000
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Polar data table (+)
Polar graphs
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