GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.61 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe180-il-1000000.txt Download as CSV file: xf-goe180-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3586 0.09187 0.09026 -0.0257 1.0000 0.0151
-8.250 -0.3576 0.08921 0.08762 -0.0259 1.0000 0.0156
-8.000 -0.3606 0.08644 0.08489 -0.0258 1.0000 0.0165
-7.000 -0.3115 0.06015 0.05856 -0.0587 0.9885 0.0178
-6.750 -0.2845 0.05814 0.05653 -0.0623 0.9858 0.0182
-6.500 -0.2573 0.05519 0.05354 -0.0669 0.9812 0.0187
-6.250 -0.2273 0.05081 0.04910 -0.0732 0.9746 0.0199
-5.750 -0.1431 0.00758 0.00443 -0.0941 0.9298 0.0216
-5.500 -0.1327 0.01652 0.01267 -0.0969 0.9421 0.0226
-5.250 -0.1009 0.01659 0.01282 -0.0979 0.9298 0.0234
-5.000 -0.0718 0.01652 0.01271 -0.0983 0.9164 0.0245
-4.750 -0.0450 0.01496 0.01083 -0.0982 0.9039 0.0251
-4.500 -0.0183 0.01375 0.00936 -0.0980 0.8923 0.0257
-4.250 0.0088 0.01296 0.00836 -0.0978 0.8812 0.0263
-4.000 0.0370 0.01368 0.00898 -0.0974 0.8692 0.0275
-3.750 0.0628 0.01181 0.00681 -0.0972 0.8562 0.0278
-3.500 0.0894 0.01088 0.00572 -0.0968 0.8397 0.0280
-3.250 0.1158 0.01009 0.00478 -0.0964 0.8185 0.0283
-3.000 0.1419 0.00954 0.00409 -0.0960 0.7915 0.0288
-2.750 0.1678 0.00927 0.00368 -0.0954 0.7564 0.0297
-2.500 0.1935 0.00909 0.00331 -0.0948 0.7168 0.0303
-2.250 0.2192 0.00895 0.00298 -0.0943 0.6763 0.0308
-2.000 0.2456 0.00883 0.00269 -0.0939 0.6415 0.0313
-1.750 0.2723 0.00871 0.00244 -0.0935 0.6127 0.0317
-1.500 0.2993 0.00861 0.00222 -0.0933 0.5888 0.0321
-1.250 0.3266 0.00852 0.00202 -0.0931 0.5694 0.0326
-1.000 0.3541 0.00845 0.00187 -0.0929 0.5523 0.0332
-0.750 0.3816 0.00842 0.00175 -0.0928 0.5369 0.0340
-0.250 0.4372 0.00828 0.00148 -0.0925 0.5137 0.0359
0.000 0.4651 0.00825 0.00139 -0.0924 0.5035 0.0376
0.250 0.4927 0.00826 0.00135 -0.0923 0.4925 0.0398
0.500 0.5207 0.00824 0.00132 -0.0923 0.4831 0.0430
0.750 0.5485 0.00815 0.00133 -0.0922 0.4753 0.0908
1.000 0.5763 0.00791 0.00139 -0.0923 0.4678 0.2129
1.250 0.6036 0.00752 0.00148 -0.0925 0.4612 0.4170
1.500 0.6278 0.00624 0.00161 -0.0918 0.4550 1.0000
2.000 0.6834 0.00642 0.00168 -0.0916 0.4425 1.0000
2.250 0.7111 0.00652 0.00174 -0.0915 0.4355 1.0000
2.500 0.7389 0.00661 0.00179 -0.0914 0.4291 1.0000
2.750 0.7666 0.00671 0.00185 -0.0914 0.4223 1.0000
3.000 0.7942 0.00682 0.00192 -0.0913 0.4156 1.0000
3.250 0.8219 0.00691 0.00200 -0.0912 0.4087 1.0000
3.500 0.8493 0.00703 0.00208 -0.0911 0.4014 1.0000
3.750 0.8770 0.00713 0.00216 -0.0910 0.3924 1.0000
4.000 0.9043 0.00726 0.00226 -0.0909 0.3826 1.0000
4.250 0.9314 0.00741 0.00237 -0.0908 0.3705 1.0000
4.500 0.9584 0.00757 0.00248 -0.0906 0.3554 1.0000
4.750 0.9849 0.00778 0.00262 -0.0904 0.3331 1.0000
5.000 1.0100 0.00815 0.00282 -0.0900 0.2973 1.0000
5.250 1.0346 0.00858 0.00308 -0.0895 0.2645 1.0000
5.500 1.0594 0.00898 0.00335 -0.0890 0.2427 1.0000
5.750 1.0848 0.00930 0.00361 -0.0887 0.2275 1.0000
6.000 1.1107 0.00956 0.00383 -0.0884 0.2168 1.0000
6.250 1.1364 0.00983 0.00406 -0.0881 0.2044 1.0000
6.500 1.1622 0.01009 0.00429 -0.0878 0.1936 1.0000
6.750 1.1877 0.01037 0.00453 -0.0875 0.1808 1.0000
7.000 1.2123 0.01074 0.00480 -0.0870 0.1589 1.0000
7.250 1.2355 0.01126 0.00517 -0.0864 0.1341 1.0000
7.500 1.2589 0.01172 0.00556 -0.0858 0.1195 1.0000
7.750 1.2828 0.01213 0.00593 -0.0852 0.1083 1.0000
8.000 1.3061 0.01259 0.00633 -0.0846 0.0936 1.0000
8.250 1.3191 0.01411 0.00742 -0.0825 0.0324 1.0000
8.500 1.3395 0.01482 0.00809 -0.0814 0.0220 1.0000
8.750 1.3603 0.01548 0.00875 -0.0803 0.0180 1.0000
9.000 1.3827 0.01592 0.00924 -0.0795 0.0168 1.0000
9.250 1.4040 0.01646 0.00981 -0.0786 0.0154 1.0000
9.500 1.4224 0.01726 0.01067 -0.0771 0.0139 1.0000
9.750 1.4431 0.01780 0.01127 -0.0761 0.0133 1.0000
10.000 1.4633 0.01835 0.01187 -0.0750 0.0126 1.0000
10.250 1.4825 0.01894 0.01250 -0.0739 0.0119 1.0000
10.500 1.4998 0.01965 0.01326 -0.0724 0.0113 1.0000
10.750 1.5113 0.02077 0.01447 -0.0700 0.0106 1.0000
11.000 1.5238 0.02168 0.01548 -0.0679 0.0103 1.0000
11.250 1.5365 0.02238 0.01624 -0.0656 0.0100 1.0000
11.500 1.5473 0.02317 0.01711 -0.0632 0.0097 1.0000
11.750 1.5568 0.02408 0.01810 -0.0607 0.0094 1.0000
12.000 1.5651 0.02509 0.01918 -0.0583 0.0091 1.0000
12.250 1.5725 0.02622 0.02039 -0.0560 0.0089 1.0000
12.500 1.5786 0.02751 0.02176 -0.0538 0.0086 1.0000
12.750 1.5831 0.02901 0.02334 -0.0517 0.0084 1.0000
13.000 1.5834 0.03098 0.02539 -0.0497 0.0081 1.0000
13.250 1.5758 0.03384 0.02838 -0.0476 0.0079 1.0000
13.500 1.5601 0.03780 0.03250 -0.0458 0.0077 1.0000
13.750 1.5663 0.03979 0.03459 -0.0454 0.0076 1.0000
14.000 1.5690 0.04227 0.03716 -0.0451 0.0075 1.0000
14.250 1.5682 0.04530 0.04031 -0.0450 0.0074 1.0000
14.500 1.5661 0.04866 0.04377 -0.0453 0.0073 1.0000
14.750 1.5620 0.05236 0.04759 -0.0457 0.0072 1.0000
15.000 1.5563 0.05642 0.05177 -0.0465 0.0071 1.0000
15.250 1.5499 0.06064 0.05610 -0.0473 0.0070 1.0000
15.500 1.5418 0.06513 0.06070 -0.0483 0.0069 1.0000
15.750 1.5332 0.06977 0.06546 -0.0494 0.0068 1.0000
16.000 1.5239 0.07460 0.07040 -0.0507 0.0068 1.0000
16.250 1.5136 0.07959 0.07550 -0.0521 0.0067 1.0000
16.500 1.5028 0.08478 0.08079 -0.0536 0.0066 1.0000
16.750 1.4921 0.09005 0.08616 -0.0552 0.0066 1.0000
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Polar data table (+)
Polar graphs
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