GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Reynolds number: 500,000 Max Cl/Cd: 89.47 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe199-il-500000-n5.txt Download as CSV file: xf-goe199-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3467 0.10658 0.10438 -0.0150 1.0000 0.0097
-8.750 -0.3426 0.10263 0.10045 -0.0168 1.0000 0.0093
-8.500 -0.3370 0.09934 0.09718 -0.0184 1.0000 0.0093
-8.250 -0.3315 0.09625 0.09411 -0.0199 1.0000 0.0093
-8.000 -0.3234 0.09294 0.09082 -0.0223 0.9879 0.0094
-7.750 -0.3110 0.08928 0.08716 -0.0261 0.9648 0.0096
-7.500 -0.2987 0.08575 0.08359 -0.0297 0.9439 0.0098
-7.250 -0.2870 0.08242 0.08022 -0.0327 0.9237 0.0104
-7.000 -0.2746 0.07842 0.07615 -0.0366 0.9055 0.0110
-6.750 -0.2596 0.07383 0.07148 -0.0413 0.8901 0.0112
-6.500 -0.2419 0.06966 0.06724 -0.0458 0.8770 0.0115
-6.250 -0.2232 0.06710 0.06460 -0.0483 0.8651 0.0117
-6.000 -0.2023 0.06401 0.06142 -0.0516 0.8539 0.0121
-5.750 -0.1792 0.06057 0.05789 -0.0554 0.8435 0.0125
-5.500 -0.1524 0.05646 0.05366 -0.0600 0.8347 0.0138
-5.250 -0.1238 0.05205 0.04912 -0.0647 0.8271 0.0145
-5.000 -0.0984 0.04960 0.04658 -0.0670 0.8196 0.0149
-4.750 -0.0707 0.04665 0.04351 -0.0699 0.8128 0.0154
-4.500 -0.0334 0.04177 0.03839 -0.0745 0.8068 0.0173
-4.250 -0.0094 0.04016 0.03671 -0.0756 0.7996 0.0181
-4.000 0.0191 0.03773 0.03415 -0.0774 0.7934 0.0186
-3.750 0.0496 0.03497 0.03122 -0.0793 0.7869 0.0192
-3.250 0.1105 0.03029 0.02619 -0.0820 0.7741 0.0226
-3.000 0.1463 0.02822 0.02379 -0.0827 0.7660 0.0256
-2.750 0.1759 0.02584 0.02115 -0.0833 0.7530 0.0256
-2.500 0.2063 0.02392 0.01888 -0.0836 0.7350 0.0258
-2.250 0.2336 0.02171 0.01644 -0.0842 0.7155 0.0255
-2.000 0.2621 0.01999 0.01449 -0.0847 0.6988 0.0251
-1.750 0.2917 0.01845 0.01266 -0.0849 0.6833 0.0251
-1.500 0.3222 0.01703 0.01082 -0.0849 0.6677 0.0262
-1.250 0.3510 0.01586 0.00941 -0.0851 0.6506 0.0263
-1.000 0.3797 0.01525 0.00856 -0.0851 0.6300 0.0260
-0.750 0.4080 0.01447 0.00752 -0.0852 0.6035 0.0261
-0.500 0.4360 0.01366 0.00644 -0.0853 0.5726 0.0263
-0.250 0.4638 0.01319 0.00575 -0.0853 0.5454 0.0266
0.000 0.4917 0.01283 0.00522 -0.0854 0.5230 0.0268
0.250 0.5196 0.01257 0.00484 -0.0855 0.5048 0.0273
0.500 0.5475 0.01238 0.00458 -0.0856 0.4879 0.0281
0.750 0.5754 0.01215 0.00424 -0.0856 0.4708 0.0283
1.000 0.6033 0.01193 0.00392 -0.0857 0.4520 0.0282
1.250 0.6310 0.01179 0.00368 -0.0857 0.4301 0.0282
1.500 0.6585 0.01173 0.00351 -0.0857 0.4048 0.0284
1.750 0.6858 0.01175 0.00340 -0.0857 0.3767 0.0288
2.000 0.7130 0.01182 0.00334 -0.0858 0.3497 0.0293
2.250 0.7402 0.01191 0.00332 -0.0858 0.3267 0.0300
2.500 0.7675 0.01201 0.00334 -0.0859 0.3071 0.0306
2.750 0.7948 0.01214 0.00340 -0.0859 0.2900 0.0313
3.000 0.8220 0.01228 0.00347 -0.0859 0.2750 0.0323
3.250 0.8493 0.01238 0.00351 -0.0860 0.2621 0.0333
3.500 0.8765 0.01252 0.00361 -0.0860 0.2509 0.0339
3.750 0.9036 0.01269 0.00372 -0.0860 0.2401 0.0350
4.000 0.9306 0.01286 0.00385 -0.0860 0.2308 0.0366
4.250 0.9577 0.01302 0.00400 -0.0860 0.2239 0.0391
4.500 0.9848 0.01317 0.00417 -0.0860 0.2183 0.0492
4.750 1.0095 0.01180 0.00448 -0.0859 0.2136 1.0000
5.000 1.0365 0.01199 0.00468 -0.0859 0.2100 1.0000
5.250 1.0633 0.01220 0.00488 -0.0858 0.2064 1.0000
5.500 1.0898 0.01243 0.00510 -0.0857 0.2028 1.0000
5.750 1.1160 0.01271 0.00536 -0.0856 0.1980 1.0000
6.000 1.1425 0.01291 0.00558 -0.0856 0.1936 1.0000
6.250 1.1687 0.01316 0.00583 -0.0855 0.1891 1.0000
6.500 1.1946 0.01343 0.00610 -0.0853 0.1856 1.0000
6.750 1.2205 0.01368 0.00638 -0.0852 0.1814 1.0000
7.000 1.2463 0.01393 0.00664 -0.0850 0.1749 1.0000
7.250 1.2713 0.01426 0.00696 -0.0848 0.1683 1.0000
7.500 1.2969 0.01451 0.00725 -0.0846 0.1612 1.0000
7.750 1.3215 0.01487 0.00758 -0.0843 0.1494 1.0000
8.000 1.3418 0.01573 0.00813 -0.0835 0.0961 1.0000
8.500 1.3766 0.01805 0.01012 -0.0810 0.0324 1.0000
8.750 1.3981 0.01865 0.01075 -0.0802 0.0267 1.0000
9.000 1.4184 0.01934 0.01147 -0.0793 0.0218 1.0000
9.250 1.4393 0.01992 0.01210 -0.0785 0.0188 1.0000
9.500 1.4584 0.02065 0.01284 -0.0774 0.0159 1.0000
9.750 1.4776 0.02131 0.01359 -0.0763 0.0144 1.0000
10.000 1.4958 0.02201 0.01435 -0.0750 0.0131 1.0000
10.250 1.5118 0.02282 0.01522 -0.0735 0.0119 1.0000
10.500 1.5259 0.02372 0.01619 -0.0717 0.0109 1.0000
10.750 1.5401 0.02451 0.01709 -0.0699 0.0102 1.0000
11.000 1.5513 0.02538 0.01805 -0.0676 0.0096 1.0000
11.250 1.5588 0.02637 0.01913 -0.0648 0.0091 1.0000
11.500 1.5650 0.02753 0.02038 -0.0622 0.0087 1.0000
11.750 1.5688 0.02899 0.02193 -0.0595 0.0083 1.0000
12.000 1.5706 0.03071 0.02377 -0.0569 0.0079 1.0000
12.250 1.5755 0.03231 0.02551 -0.0550 0.0077 1.0000
12.500 1.5790 0.03413 0.02745 -0.0533 0.0075 1.0000
12.750 1.5816 0.03615 0.02959 -0.0518 0.0072 1.0000
13.000 1.5832 0.03837 0.03193 -0.0505 0.0069 1.0000
13.250 1.5837 0.04082 0.03451 -0.0494 0.0067 1.0000
13.500 1.5834 0.04349 0.03729 -0.0486 0.0065 1.0000
13.750 1.5814 0.04646 0.04038 -0.0481 0.0063 1.0000
14.000 1.5771 0.04987 0.04390 -0.0478 0.0061 1.0000
14.250 1.5704 0.05375 0.04792 -0.0478 0.0060 1.0000
14.500 1.5604 0.05824 0.05255 -0.0483 0.0059 1.0000
14.750 1.5479 0.06336 0.05782 -0.0492 0.0058 1.0000
15.000 1.5337 0.06904 0.06364 -0.0506 0.0057 1.0000
15.250 1.5177 0.07518 0.06993 -0.0523 0.0056 1.0000
15.500 1.5040 0.08114 0.07602 -0.0541 0.0056 1.0000
15.750 1.4908 0.08712 0.08214 -0.0559 0.0056 1.0000
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Polar data table (+)
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