GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Reynolds number: 500,000 Max Cl/Cd: 89.81 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe199-il-500000.txt Download as CSV file: xf-goe199-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 199 (L.F.G. 5406) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3420 0.09922 0.09705 -0.0160 1.0000 0.0171
-8.000 -0.3374 0.09634 0.09421 -0.0185 1.0000 0.0173
-7.750 -0.3348 0.09356 0.09146 -0.0214 1.0000 0.0173
-7.500 -0.2355 0.07476 0.07284 -0.0323 0.9905 0.0177
-7.250 -0.2217 0.07054 0.06862 -0.0347 0.9825 0.0179
-7.000 -0.3000 0.08193 0.07988 -0.0347 0.9953 0.0176
-6.750 -0.2822 0.07792 0.07586 -0.0360 0.9906 0.0178
-6.500 -0.2575 0.07402 0.07194 -0.0408 0.9837 0.0182
-6.250 -0.2317 0.07020 0.06809 -0.0462 0.9730 0.0187
-6.000 -0.2063 0.06651 0.06434 -0.0511 0.9599 0.0196
-5.750 -0.1719 0.06250 0.06021 -0.0586 0.9447 0.0210
-5.500 -0.1356 0.05809 0.05560 -0.0658 0.9308 0.0213
-5.250 -0.1129 0.05364 0.05102 -0.0685 0.9192 0.0214
-5.000 -0.1002 0.05064 0.04799 -0.0681 0.9088 0.0217
-4.750 -0.0810 0.04810 0.04539 -0.0688 0.8984 0.0220
-4.500 -0.0578 0.04565 0.04284 -0.0702 0.8892 0.0227
-4.250 -0.0312 0.04300 0.04007 -0.0720 0.8805 0.0238
-4.000 0.0134 0.03987 0.03659 -0.0755 0.8723 0.0258
-3.750 0.0453 0.03700 0.03342 -0.0768 0.8648 0.0260
-3.250 0.0897 0.03135 0.02764 -0.0786 0.8492 0.0271
-3.000 0.1164 0.02957 0.02574 -0.0793 0.8390 0.0280
-2.750 0.1448 0.02767 0.02364 -0.0796 0.8260 0.0294
-2.500 0.1811 0.02656 0.02204 -0.0791 0.8124 0.0318
-2.250 0.2078 0.02312 0.01835 -0.0799 0.8006 0.0325
-2.000 0.2342 0.02173 0.01689 -0.0804 0.7896 0.0334
-1.750 0.2619 0.02061 0.01566 -0.0807 0.7796 0.0347
-1.500 0.2912 0.01950 0.01432 -0.0807 0.7707 0.0371
-1.250 0.3225 0.01804 0.01247 -0.0807 0.7610 0.0404
-1.000 0.3500 0.01693 0.01133 -0.0811 0.7507 0.0419
-0.750 0.3782 0.01621 0.01047 -0.0812 0.7396 0.0445
-0.500 0.4080 0.01556 0.00950 -0.0810 0.7274 0.0504
-0.250 0.4358 0.01468 0.00863 -0.0814 0.7147 0.0533
0.000 0.4648 0.01574 0.00950 -0.0810 0.7004 0.0603
0.250 0.4925 0.01357 0.00729 -0.0815 0.6855 0.0660
0.500 0.5208 0.01311 0.00668 -0.0816 0.6676 0.0766
0.750 0.5488 0.01268 0.00614 -0.0817 0.6464 0.0897
1.250 0.6074 0.01155 0.00448 -0.0805 0.5935 0.0496
1.500 0.6348 0.01118 0.00399 -0.0803 0.5645 0.0474
1.750 0.6621 0.01098 0.00366 -0.0802 0.5382 0.0466
2.250 0.7171 0.01075 0.00322 -0.0800 0.4915 0.0436
2.500 0.7446 0.01077 0.00314 -0.0800 0.4677 0.0436
2.750 0.7722 0.01083 0.00310 -0.0800 0.4402 0.0445
3.000 0.7993 0.01099 0.00312 -0.0800 0.4073 0.0459
3.250 0.8261 0.01124 0.00319 -0.0800 0.3705 0.0477
3.500 0.8526 0.01153 0.00331 -0.0799 0.3376 0.0526
3.750 0.8793 0.01181 0.00349 -0.0798 0.3119 0.0669
4.000 0.9042 0.01040 0.00377 -0.0798 0.2923 1.0000
4.250 0.9308 0.01072 0.00396 -0.0798 0.2759 1.0000
4.500 0.9575 0.01102 0.00417 -0.0797 0.2629 1.0000
4.750 0.9841 0.01131 0.00439 -0.0796 0.2530 1.0000
5.000 1.0106 0.01161 0.00463 -0.0795 0.2451 1.0000
5.250 1.0372 0.01187 0.00488 -0.0794 0.2387 1.0000
5.500 1.0636 0.01214 0.00511 -0.0794 0.2320 1.0000
5.750 1.0897 0.01246 0.00541 -0.0792 0.2266 1.0000
6.000 1.1164 0.01266 0.00564 -0.0792 0.2218 1.0000
6.250 1.1423 0.01296 0.00591 -0.0790 0.2157 1.0000
6.500 1.1685 0.01321 0.00618 -0.0789 0.2103 1.0000
6.750 1.1947 0.01343 0.00643 -0.0788 0.2048 1.0000
7.250 1.2465 0.01394 0.00697 -0.0785 0.1931 1.0000
7.500 1.2718 0.01423 0.00726 -0.0783 0.1862 1.0000
7.750 1.2977 0.01445 0.00752 -0.0782 0.1764 1.0000
8.000 1.3226 0.01478 0.00780 -0.0780 0.1604 1.0000
8.250 1.3366 0.01649 0.00891 -0.0764 0.0654 1.0000
8.500 1.3528 0.01791 0.01013 -0.0749 0.0344 1.0000
8.750 1.3728 0.01879 0.01109 -0.0738 0.0291 1.0000
9.000 1.3929 0.01957 0.01195 -0.0728 0.0262 1.0000
9.250 1.4078 0.02086 0.01335 -0.0711 0.0235 1.0000
9.500 1.4265 0.02163 0.01422 -0.0698 0.0223 1.0000
9.750 1.4439 0.02246 0.01514 -0.0685 0.0209 1.0000
10.000 1.4595 0.02335 0.01610 -0.0669 0.0196 1.0000
10.250 1.4694 0.02459 0.01742 -0.0645 0.0185 1.0000
10.500 1.4662 0.02653 0.01950 -0.0602 0.0176 1.0000
10.750 1.4744 0.02749 0.02056 -0.0574 0.0172 1.0000
11.000 1.4794 0.02875 0.02193 -0.0546 0.0167 1.0000
11.250 1.4832 0.03024 0.02354 -0.0520 0.0162 1.0000
11.500 1.4862 0.03193 0.02534 -0.0496 0.0157 1.0000
11.750 1.4889 0.03379 0.02729 -0.0477 0.0152 1.0000
12.000 1.4915 0.03577 0.02937 -0.0460 0.0148 1.0000
12.250 1.4928 0.03801 0.03168 -0.0446 0.0144 1.0000
12.500 1.4902 0.04074 0.03450 -0.0433 0.0140 1.0000
12.750 1.4813 0.04428 0.03814 -0.0419 0.0136 1.0000
13.000 1.4724 0.04796 0.04194 -0.0405 0.0133 1.0000
13.250 1.4746 0.05056 0.04468 -0.0401 0.0131 1.0000
13.500 1.4743 0.05351 0.04776 -0.0397 0.0128 1.0000
13.750 1.4727 0.05667 0.05105 -0.0393 0.0126 1.0000
14.000 1.4704 0.05998 0.05448 -0.0391 0.0124 1.0000
14.250 1.4677 0.06343 0.05806 -0.0391 0.0122 1.0000
14.500 1.4644 0.06701 0.06175 -0.0391 0.0120 1.0000
14.750 1.4610 0.07071 0.06558 -0.0394 0.0118 1.0000
15.000 1.4574 0.07456 0.06955 -0.0399 0.0116 1.0000
15.250 1.4535 0.07852 0.07364 -0.0405 0.0114 1.0000
15.500 1.4491 0.08262 0.07786 -0.0412 0.0113 1.0000
15.750 1.4437 0.08698 0.08234 -0.0423 0.0111 1.0000
16.000 1.4380 0.09151 0.08699 -0.0435 0.0110 1.0000
16.250 1.4318 0.09620 0.09181 -0.0450 0.0108 1.0000
16.500 1.4251 0.10104 0.09676 -0.0467 0.0107 1.0000
16.750 1.4185 0.10592 0.10175 -0.0486 0.0106 1.0000
17.000 1.4118 0.11084 0.10677 -0.0505 0.0104 1.0000
17.250 1.4043 0.11594 0.11198 -0.0524 0.0103 1.0000
17.500 1.3943 0.12147 0.11763 -0.0545 0.0102 1.0000
17.750 1.3812 0.12786 0.12418 -0.0573 0.0101 1.0000
18.000 1.3665 0.13494 0.13144 -0.0609 0.0100 1.0000
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