GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il) Reynolds number: 200,000 Max Cl/Cd: 77.8 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe180-il-200000-n5.txt Download as CSV file: xf-goe180-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 180 (MVA H.26) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3531 0.08932 0.08590 -0.0295 1.0000 0.0226
-7.750 -0.3554 0.08692 0.08356 -0.0283 1.0000 0.0224
-7.500 -0.3596 0.08434 0.08105 -0.0276 1.0000 0.0222
-7.250 -0.3631 0.08151 0.07828 -0.0278 1.0000 0.0220
-6.750 -0.3218 0.06754 0.06424 -0.0482 0.9881 0.0233
-6.500 -0.2997 0.06737 0.06408 -0.0480 0.9841 0.0252
-6.250 -0.2710 0.06167 0.05830 -0.0565 0.9768 0.0259
-6.000 -0.2418 0.05513 0.05163 -0.0650 0.9677 0.0258
-5.750 -0.2104 0.04882 0.04513 -0.0726 0.9592 0.0266
-5.500 -0.1714 0.03985 0.03572 -0.0818 0.9527 0.0286
-5.250 -0.1381 0.03060 0.02562 -0.0875 0.9442 0.0297
-5.000 -0.1064 0.02801 0.02285 -0.0903 0.9388 0.0313
-4.750 -0.0759 0.02595 0.02055 -0.0919 0.9307 0.0324
-4.500 -0.0405 0.02280 0.01688 -0.0944 0.9246 0.0333
-4.250 -0.0078 0.02085 0.01454 -0.0957 0.9159 0.0349
-4.000 0.0278 0.01903 0.01228 -0.0974 0.9083 0.0361
-3.750 0.0599 0.01762 0.01051 -0.0983 0.8980 0.0367
-3.500 0.0919 0.01653 0.00914 -0.0990 0.8873 0.0372
-3.250 0.1232 0.01572 0.00810 -0.0995 0.8752 0.0379
-3.000 0.1527 0.01484 0.00704 -0.0997 0.8610 0.0391
-2.750 0.1811 0.01410 0.00620 -0.0996 0.8447 0.0399
-2.500 0.2089 0.01354 0.00554 -0.0994 0.8263 0.0405
-2.250 0.2366 0.01308 0.00499 -0.0991 0.8059 0.0412
-2.000 0.2639 0.01271 0.00452 -0.0988 0.7826 0.0421
-1.750 0.2910 0.01243 0.00410 -0.0983 0.7571 0.0431
-1.500 0.3177 0.01223 0.00375 -0.0978 0.7294 0.0442
-1.250 0.3441 0.01211 0.00345 -0.0973 0.7005 0.0456
-1.000 0.3703 0.01206 0.00321 -0.0967 0.6722 0.0480
-0.750 0.3965 0.01201 0.00304 -0.0962 0.6470 0.0517
-0.500 0.4228 0.01200 0.00291 -0.0958 0.6252 0.0561
-0.250 0.4492 0.01199 0.00282 -0.0953 0.6065 0.0692
0.000 0.4757 0.01195 0.00277 -0.0950 0.5901 0.1004
0.250 0.5021 0.01183 0.00278 -0.0948 0.5758 0.1672
0.500 0.5286 0.01171 0.00282 -0.0946 0.5629 0.2514
0.750 0.5519 0.01087 0.00294 -0.0941 0.5516 0.5975
1.250 0.6063 0.01037 0.00298 -0.0930 0.5330 1.0000
1.500 0.6334 0.01053 0.00304 -0.0928 0.5248 1.0000
1.750 0.6601 0.01072 0.00311 -0.0925 0.5162 1.0000
2.000 0.6871 0.01088 0.00320 -0.0923 0.5068 1.0000
2.250 0.7137 0.01107 0.00329 -0.0920 0.4971 1.0000
2.500 0.7402 0.01125 0.00339 -0.0917 0.4865 1.0000
2.750 0.7669 0.01141 0.00351 -0.0914 0.4770 1.0000
3.000 0.7935 0.01161 0.00364 -0.0911 0.4697 1.0000
3.250 0.8205 0.01177 0.00380 -0.0910 0.4626 1.0000
3.500 0.8469 0.01197 0.00396 -0.0907 0.4550 1.0000
3.750 0.8736 0.01213 0.00414 -0.0904 0.4463 1.0000
4.000 0.8997 0.01234 0.00431 -0.0901 0.4374 1.0000
4.250 0.9260 0.01252 0.00451 -0.0898 0.4272 1.0000
4.500 0.9521 0.01271 0.00470 -0.0895 0.4165 1.0000
4.750 0.9778 0.01293 0.00491 -0.0891 0.4047 1.0000
5.000 1.0033 0.01315 0.00514 -0.0886 0.3919 1.0000
5.250 1.0288 0.01337 0.00537 -0.0882 0.3780 1.0000
5.500 1.0541 0.01361 0.00562 -0.0878 0.3626 1.0000
5.750 1.0791 0.01387 0.00590 -0.0873 0.3440 1.0000
6.000 1.1031 0.01419 0.00619 -0.0867 0.3215 1.0000
6.250 1.1264 0.01459 0.00653 -0.0860 0.2975 1.0000
7.000 1.1942 0.01604 0.00788 -0.0837 0.2500 1.0000
7.250 1.2167 0.01653 0.00839 -0.0829 0.2394 1.0000
7.500 1.2383 0.01710 0.00895 -0.0820 0.2275 1.0000
7.750 1.2592 0.01770 0.00956 -0.0810 0.2118 1.0000
8.000 1.2801 0.01828 0.01012 -0.0801 0.1930 1.0000
8.250 1.3007 0.01887 0.01068 -0.0791 0.1729 1.0000
8.500 1.3208 0.01948 0.01126 -0.0781 0.1509 1.0000
8.750 1.3380 0.02033 0.01200 -0.0768 0.1291 1.0000
9.000 1.3548 0.02120 0.01283 -0.0753 0.1118 1.0000
9.250 1.3700 0.02218 0.01375 -0.0737 0.0828 1.0000
10.000 1.3893 0.02676 0.01803 -0.0652 0.0247 1.0000
10.250 1.3956 0.02807 0.01942 -0.0624 0.0219 1.0000
10.500 1.4026 0.02935 0.02085 -0.0599 0.0201 1.0000
10.750 1.4093 0.03068 0.02233 -0.0576 0.0186 1.0000
11.000 1.4138 0.03223 0.02402 -0.0553 0.0175 1.0000
11.250 1.4157 0.03407 0.02599 -0.0531 0.0167 1.0000
11.500 1.4140 0.03633 0.02840 -0.0510 0.0160 1.0000
11.750 1.4084 0.03912 0.03132 -0.0492 0.0154 1.0000
12.000 1.4087 0.04156 0.03393 -0.0481 0.0150 1.0000
12.250 1.4075 0.04430 0.03683 -0.0473 0.0145 1.0000
12.500 1.4054 0.04733 0.04001 -0.0468 0.0140 1.0000
12.750 1.4024 0.05061 0.04345 -0.0467 0.0135 1.0000
13.000 1.3986 0.05416 0.04714 -0.0469 0.0131 1.0000
13.250 1.3938 0.05795 0.05107 -0.0473 0.0127 1.0000
13.500 1.3881 0.06195 0.05519 -0.0479 0.0124 1.0000
13.750 1.3816 0.06611 0.05948 -0.0486 0.0122 1.0000
14.000 1.3747 0.07040 0.06387 -0.0494 0.0120 1.0000
14.250 1.3673 0.07476 0.06835 -0.0502 0.0118 1.0000
14.500 1.3600 0.07916 0.07285 -0.0510 0.0116 1.0000
14.750 1.3527 0.08357 0.07736 -0.0518 0.0114 1.0000
15.000 1.3458 0.08780 0.08167 -0.0523 0.0112 1.0000
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Polar data table (+)
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