GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il) Reynolds number: 200,000 Max Cl/Cd: 74.2 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe308-il-200000.txt Download as CSV file: xf-goe308-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 308 (MVA H.40) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3282 0.09065 0.08750 -0.0243 1.0000 0.0373
-7.250 -0.3422 0.08937 0.08631 -0.0215 1.0000 0.0374
-7.000 -0.3512 0.08787 0.08487 -0.0189 1.0000 0.0383
-6.750 -0.3618 0.08638 0.08344 -0.0167 1.0000 0.0388
-6.500 -0.3706 0.08477 0.08188 -0.0149 0.9999 0.0395
-6.250 -0.3361 0.07965 0.07669 -0.0244 0.9938 0.0426
-6.000 -0.2786 0.07456 0.07134 -0.0444 0.9841 0.0454
-5.750 -0.2693 0.06847 0.06533 -0.0440 0.9789 0.0468
-5.500 -0.2443 0.06506 0.06190 -0.0461 0.9739 0.0487
-5.250 -0.1936 0.06174 0.05823 -0.0577 0.9652 0.0567
-5.000 -0.1740 0.05614 0.05266 -0.0599 0.9600 0.0583
-4.250 -0.0765 0.04563 0.04179 -0.0706 0.9433 0.0713
-4.000 -0.0499 0.04355 0.03962 -0.0716 0.9343 0.0780
-3.750 -0.0106 0.03961 0.03541 -0.0758 0.9300 0.0836
-3.500 0.0171 0.03727 0.03300 -0.0768 0.9221 0.0872
-3.250 0.0581 0.03421 0.02948 -0.0800 0.9165 0.0958
-3.000 0.0856 0.03186 0.02716 -0.0808 0.9087 0.0990
-2.750 0.1260 0.03055 0.02521 -0.0823 0.9013 0.1083
-2.500 0.1500 0.02217 0.01611 -0.0807 0.8919 0.0670
-2.250 0.1859 0.01959 0.01312 -0.0819 0.8850 0.0660
-2.000 0.2149 0.01757 0.01073 -0.0815 0.8730 0.0648
-1.750 0.2464 0.01589 0.00868 -0.0816 0.8611 0.0643
-1.500 0.2785 0.01474 0.00728 -0.0818 0.8480 0.0651
-1.250 0.3092 0.01390 0.00627 -0.0819 0.8334 0.0668
-1.000 0.3380 0.01329 0.00555 -0.0816 0.8175 0.0698
-0.750 0.3655 0.01297 0.00520 -0.0811 0.8004 0.0742
-0.500 0.3922 0.01262 0.00475 -0.0804 0.7823 0.0795
-0.250 0.4169 0.01236 0.00447 -0.0793 0.7621 0.0884
0.000 0.4406 0.01205 0.00415 -0.0780 0.7407 0.1141
0.250 0.4644 0.01191 0.00396 -0.0769 0.7182 0.1421
0.500 0.4884 0.01194 0.00390 -0.0759 0.6939 0.1617
0.750 0.5121 0.01202 0.00387 -0.0748 0.6689 0.1783
1.000 0.5356 0.01208 0.00380 -0.0737 0.6461 0.1893
1.250 0.5585 0.01213 0.00376 -0.0726 0.6239 0.2008
1.500 0.5815 0.01221 0.00376 -0.0715 0.6046 0.2199
1.750 0.7140 0.01090 0.00394 -0.0941 0.5750 1.0000
2.000 0.7364 0.01112 0.00401 -0.0929 0.5604 1.0000
2.250 0.7589 0.01134 0.00410 -0.0917 0.5470 1.0000
2.500 0.7812 0.01156 0.00422 -0.0906 0.5346 1.0000
2.750 0.8035 0.01178 0.00434 -0.0894 0.5230 1.0000
3.000 0.8257 0.01202 0.00445 -0.0882 0.5118 1.0000
3.250 0.8476 0.01223 0.00460 -0.0870 0.5005 1.0000
3.500 0.8695 0.01244 0.00478 -0.0858 0.4898 1.0000
3.750 0.8921 0.01271 0.00497 -0.0847 0.4815 1.0000
4.000 0.9144 0.01293 0.00519 -0.0836 0.4731 1.0000
4.250 0.9369 0.01321 0.00542 -0.0826 0.4655 1.0000
4.500 0.9591 0.01345 0.00567 -0.0815 0.4574 1.0000
4.750 0.9812 0.01373 0.00594 -0.0804 0.4496 1.0000
5.000 1.0034 0.01399 0.00621 -0.0792 0.4421 1.0000
5.250 1.0255 0.01428 0.00652 -0.0781 0.4349 1.0000
5.500 1.0474 0.01455 0.00683 -0.0770 0.4274 1.0000
5.750 1.0691 0.01485 0.00717 -0.0758 0.4200 1.0000
6.000 1.0897 0.01511 0.00740 -0.0744 0.4102 1.0000
6.250 1.1074 0.01525 0.00761 -0.0724 0.3973 1.0000
6.500 1.1250 0.01541 0.00783 -0.0704 0.3841 1.0000
6.750 1.1424 0.01555 0.00803 -0.0684 0.3705 1.0000
7.000 1.1595 0.01570 0.00823 -0.0663 0.3562 1.0000
7.250 1.1760 0.01586 0.00843 -0.0641 0.3402 1.0000
7.500 1.1917 0.01606 0.00866 -0.0618 0.3219 1.0000
7.750 1.2062 0.01628 0.00890 -0.0593 0.2957 1.0000
8.000 1.2160 0.01678 0.00921 -0.0560 0.2523 1.0000
8.250 1.2192 0.01783 0.00986 -0.0519 0.1923 1.0000
8.500 1.2195 0.01925 0.01085 -0.0475 0.1309 1.0000
8.750 1.2048 0.02146 0.01240 -0.0410 0.0483 1.0000
9.000 1.2070 0.02259 0.01353 -0.0367 0.0395 1.0000
9.250 1.2106 0.02370 0.01474 -0.0330 0.0356 1.0000
9.500 1.2155 0.02478 0.01598 -0.0296 0.0333 1.0000
9.750 1.2202 0.02590 0.01727 -0.0264 0.0319 1.0000
10.000 1.2223 0.02723 0.01874 -0.0232 0.0306 1.0000
10.250 1.2227 0.02873 0.02037 -0.0201 0.0299 1.0000
10.500 1.2210 0.03047 0.02224 -0.0172 0.0292 1.0000
10.750 1.2169 0.03254 0.02441 -0.0145 0.0285 1.0000
11.000 1.2140 0.03471 0.02667 -0.0123 0.0281 1.0000
11.250 1.2077 0.03734 0.02937 -0.0103 0.0273 1.0000
11.500 1.2033 0.04000 0.03209 -0.0085 0.0267 1.0000
11.750 1.2022 0.04261 0.03471 -0.0066 0.0258 1.0000
12.000 1.2085 0.04447 0.03671 -0.0055 0.0252 1.0000
12.250 1.2171 0.04628 0.03858 -0.0041 0.0250 1.0000
12.500 1.2285 0.04799 0.04036 -0.0027 0.0247 1.0000
12.750 1.2434 0.04966 0.04212 -0.0013 0.0247 1.0000
13.000 1.2584 0.05157 0.04415 0.0001 0.0246 1.0000
13.250 1.2748 0.05379 0.04653 0.0014 0.0246 1.0000
13.500 1.2870 0.05638 0.04932 0.0025 0.0247 1.0000
13.750 1.2904 0.05919 0.05234 0.0034 0.0246 1.0000
14.000 1.2886 0.06222 0.05559 0.0041 0.0243 1.0000
14.250 1.2842 0.06555 0.05913 0.0045 0.0240 1.0000
14.500 1.2818 0.06934 0.06314 0.0049 0.0244 1.0000
14.750 1.2759 0.07368 0.06771 0.0050 0.0248 1.0000
15.000 1.2995 0.07685 0.07099 0.0062 0.0267 1.0000
15.250 1.2818 0.08036 0.07478 0.0055 0.0274 1.0000
15.500 1.2505 0.08625 0.08105 0.0031 0.0285 1.0000
15.750 1.2225 0.09317 0.08829 0.0001 0.0292 1.0000
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Polar data table (+)
Polar graphs
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