GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il) Reynolds number: 500,000 Max Cl/Cd: 106.36 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe311-il-500000-n5.txt Download as CSV file: xf-goe311-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 311 (MVA H.43) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3002 0.08759 0.08506 -0.0285 0.8083 0.0073
-8.000 -0.2983 0.08350 0.08088 -0.0309 0.7866 0.0073
-7.750 -0.2956 0.07867 0.07598 -0.0351 0.7698 0.0073
-7.500 -0.2918 0.07095 0.06818 -0.0428 0.7577 0.0074
-7.250 -0.2929 0.04867 0.04558 -0.0663 0.7528 0.0074
-7.000 -0.2746 0.03226 0.02840 -0.0799 0.7454 0.0074
-6.750 -0.2512 0.02502 0.02056 -0.0839 0.7360 0.0075
-6.500 -0.2266 0.02008 0.01510 -0.0858 0.7268 0.0077
-6.250 -0.2007 0.01732 0.01196 -0.0866 0.7169 0.0082
-6.000 -0.1737 0.01597 0.01035 -0.0869 0.7067 0.0086
-5.750 -0.1465 0.01504 0.00916 -0.0870 0.6959 0.0092
-5.500 -0.1189 0.01431 0.00821 -0.0871 0.6842 0.0100
-5.250 -0.0910 0.01367 0.00737 -0.0872 0.6720 0.0107
-5.000 -0.0631 0.01310 0.00659 -0.0872 0.6582 0.0113
-4.750 -0.0351 0.01245 0.00571 -0.0872 0.6415 0.0128
-4.500 -0.0072 0.01197 0.00502 -0.0872 0.6208 0.0146
-4.250 0.0206 0.01162 0.00449 -0.0872 0.5971 0.0185
-4.000 0.0487 0.01162 0.00451 -0.0872 0.5779 0.0325
-3.750 0.0770 0.01169 0.00441 -0.0872 0.5641 0.0369
-3.500 0.1053 0.01175 0.00441 -0.0872 0.5541 0.0397
-3.250 0.1337 0.01188 0.00443 -0.0873 0.5472 0.0430
-3.000 0.1621 0.01188 0.00433 -0.0874 0.5414 0.0443
-2.750 0.1901 0.01167 0.00402 -0.0874 0.5364 0.0458
-2.500 0.2181 0.01141 0.00371 -0.0875 0.5322 0.0481
-2.250 0.2463 0.01126 0.00351 -0.0875 0.5280 0.0498
-2.000 0.2745 0.01111 0.00330 -0.0875 0.5241 0.0504
-1.750 0.3026 0.01099 0.00310 -0.0875 0.5209 0.0508
-1.500 0.3308 0.01087 0.00294 -0.0876 0.5181 0.0513
-1.250 0.3591 0.01076 0.00279 -0.0876 0.5152 0.0519
-1.000 0.3874 0.01067 0.00266 -0.0877 0.5121 0.0525
-0.750 0.4156 0.01060 0.00256 -0.0877 0.5093 0.0532
-0.500 0.4437 0.01057 0.00248 -0.0877 0.5067 0.0542
-0.250 0.4718 0.01056 0.00241 -0.0878 0.5042 0.0551
0.000 0.5002 0.01051 0.00235 -0.0878 0.5017 0.0558
0.250 0.5285 0.01046 0.00230 -0.0879 0.4991 0.0573
0.500 0.5566 0.01044 0.00226 -0.0880 0.4954 0.0597
0.750 0.5845 0.01044 0.00223 -0.0880 0.4910 0.0632
1.250 0.6406 0.01034 0.00229 -0.0882 0.4823 0.1057
1.500 0.6686 0.01037 0.00234 -0.0882 0.4781 0.1162
2.000 0.7247 0.01044 0.00245 -0.0884 0.4687 0.1292
2.250 0.7526 0.01048 0.00249 -0.0885 0.4629 0.1346
2.500 0.7804 0.01053 0.00255 -0.0885 0.4578 0.1398
2.750 0.8085 0.01054 0.00261 -0.0886 0.4514 0.1446
3.000 0.8360 0.01062 0.00266 -0.0887 0.4440 0.1492
3.250 0.8640 0.01062 0.00274 -0.0888 0.4370 0.1550
3.500 0.8916 0.01068 0.00281 -0.0888 0.4311 0.1601
3.750 0.9194 0.01072 0.00290 -0.0889 0.4252 0.1676
4.250 0.9743 0.01083 0.00313 -0.0890 0.4095 0.1946
4.500 1.0014 0.01090 0.00327 -0.0891 0.3990 0.2289
4.750 1.0283 0.01098 0.00345 -0.0891 0.3859 0.2823
5.000 1.0545 0.01096 0.00364 -0.0891 0.3700 0.4204
5.250 1.0785 0.01014 0.00385 -0.0885 0.3521 1.0000
5.500 1.1036 0.01047 0.00410 -0.0882 0.3313 1.0000
5.750 1.1282 0.01086 0.00439 -0.0879 0.3087 1.0000
6.000 1.1492 0.01165 0.00489 -0.0871 0.2592 1.0000
6.250 1.1688 0.01257 0.00550 -0.0862 0.2072 1.0000
6.500 1.1903 0.01325 0.00602 -0.0855 0.1767 1.0000
6.750 1.2114 0.01391 0.00653 -0.0848 0.1492 1.0000
7.000 1.2256 0.01522 0.00745 -0.0832 0.0858 1.0000
7.250 1.2473 0.01574 0.00797 -0.0824 0.0769 1.0000
7.500 1.2687 0.01626 0.00849 -0.0817 0.0681 1.0000
7.750 1.2821 0.01744 0.00944 -0.0799 0.0223 1.0000
8.000 1.3001 0.01816 0.01016 -0.0786 0.0154 1.0000
8.250 1.3194 0.01873 0.01080 -0.0774 0.0126 1.0000
8.500 1.3378 0.01932 0.01146 -0.0762 0.0112 1.0000
8.750 1.3541 0.02002 0.01223 -0.0747 0.0099 1.0000
9.000 1.3658 0.02087 0.01316 -0.0725 0.0089 1.0000
9.250 1.3775 0.02166 0.01404 -0.0703 0.0084 1.0000
9.500 1.3892 0.02251 0.01497 -0.0683 0.0079 1.0000
9.750 1.4002 0.02347 0.01602 -0.0665 0.0074 1.0000
10.000 1.4103 0.02453 0.01715 -0.0647 0.0068 1.0000
10.250 1.4187 0.02577 0.01846 -0.0629 0.0064 1.0000
10.500 1.4224 0.02747 0.02025 -0.0608 0.0060 1.0000
10.750 1.4278 0.02915 0.02203 -0.0592 0.0058 1.0000
11.000 1.4335 0.03090 0.02388 -0.0579 0.0056 1.0000
11.250 1.4378 0.03290 0.02600 -0.0567 0.0054 1.0000
11.500 1.4407 0.03515 0.02835 -0.0557 0.0052 1.0000
11.750 1.4424 0.03761 0.03092 -0.0549 0.0051 1.0000
12.000 1.4434 0.04024 0.03365 -0.0542 0.0049 1.0000
12.250 1.4431 0.04306 0.03657 -0.0537 0.0048 1.0000
12.500 1.4424 0.04600 0.03963 -0.0532 0.0046 1.0000
12.750 1.4411 0.04905 0.04278 -0.0529 0.0045 1.0000
13.000 1.4393 0.05223 0.04605 -0.0527 0.0044 1.0000
13.250 1.4367 0.05560 0.04951 -0.0527 0.0043 1.0000
13.500 1.4322 0.05928 0.05329 -0.0528 0.0042 1.0000
13.750 1.4239 0.06350 0.05761 -0.0529 0.0041 1.0000
14.000 1.4187 0.06739 0.06161 -0.0531 0.0040 1.0000
14.250 1.4173 0.07085 0.06517 -0.0534 0.0039 1.0000
14.500 1.4141 0.07454 0.06898 -0.0537 0.0038 1.0000
14.750 1.4105 0.07835 0.07290 -0.0541 0.0037 1.0000
15.000 1.4062 0.08229 0.07694 -0.0545 0.0036 1.0000
15.250 1.4018 0.08629 0.08105 -0.0550 0.0035 1.0000
15.500 1.3974 0.09028 0.08514 -0.0555 0.0035 1.0000
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Polar data table (+)
Polar graphs
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