GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il) Reynolds number: 500,000 Max Cl/Cd: 97.95 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe182-il-500000-n5.txt Download as CSV file: xf-goe182-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 182 (MVA H.27) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3287 0.08861 0.08643 -0.0220 1.0000 0.0151
-8.250 -0.3276 0.08488 0.08273 -0.0238 1.0000 0.0158
-8.000 -0.3291 0.07785 0.07573 -0.0304 0.9879 0.0171
-7.750 -0.3068 0.07507 0.07294 -0.0350 0.9766 0.0175
-7.500 -0.2849 0.07178 0.06963 -0.0401 0.9619 0.0179
-7.250 -0.2662 0.06779 0.06560 -0.0455 0.9406 0.0186
-6.750 -0.2095 0.02013 0.01609 -0.1023 0.9014 0.0256
-6.500 -0.1864 0.01799 0.01349 -0.1023 0.8564 0.0263
-6.250 -0.1635 0.01756 0.01270 -0.1012 0.7924 0.0267
-6.000 -0.1385 0.01725 0.01209 -0.1007 0.7496 0.0272
-5.750 -0.1123 0.01669 0.01124 -0.1005 0.7220 0.0278
-5.500 -0.0856 0.01591 0.01019 -0.1004 0.7012 0.0283
-5.250 -0.0584 0.01516 0.00919 -0.1004 0.6833 0.0288
-5.000 -0.0310 0.01447 0.00827 -0.1003 0.6680 0.0294
-4.750 -0.0034 0.01396 0.00756 -0.1002 0.6523 0.0301
-4.500 0.0243 0.01349 0.00690 -0.1001 0.6356 0.0307
-4.250 0.0520 0.01303 0.00625 -0.0999 0.6178 0.0310
-4.000 0.0796 0.01266 0.00569 -0.0997 0.5981 0.0314
-3.750 0.1072 0.01224 0.00510 -0.0996 0.5773 0.0317
-3.500 0.1347 0.01178 0.00448 -0.0994 0.5576 0.0324
-3.250 0.1623 0.01152 0.00409 -0.0992 0.5395 0.0330
-3.000 0.1901 0.01134 0.00380 -0.0991 0.5231 0.0337
-2.750 0.2179 0.01120 0.00356 -0.0989 0.5072 0.0344
-2.500 0.2458 0.01109 0.00335 -0.0987 0.4914 0.0355
-2.250 0.2736 0.01098 0.00314 -0.0986 0.4749 0.0364
-2.000 0.3015 0.01088 0.00293 -0.0984 0.4579 0.0373
-1.750 0.3294 0.01080 0.00274 -0.0982 0.4404 0.0381
-1.500 0.3572 0.01074 0.00258 -0.0981 0.4221 0.0389
-1.250 0.3850 0.01067 0.00242 -0.0979 0.4028 0.0408
-1.000 0.4127 0.01068 0.00234 -0.0978 0.3834 0.0429
-0.750 0.4404 0.01071 0.00228 -0.0976 0.3656 0.0455
-0.500 0.4681 0.01074 0.00223 -0.0974 0.3500 0.0494
-0.250 0.4958 0.01079 0.00223 -0.0973 0.3365 0.0555
0.000 0.5235 0.01082 0.00223 -0.0971 0.3253 0.0624
0.250 0.5512 0.01090 0.00223 -0.0970 0.3154 0.0685
0.500 0.5789 0.01092 0.00223 -0.0968 0.3064 0.0762
0.750 0.6066 0.01097 0.00225 -0.0967 0.2990 0.0846
1.000 0.6343 0.01093 0.00232 -0.0966 0.2918 0.1235
1.250 0.6618 0.01098 0.00240 -0.0964 0.2855 0.1579
1.500 0.6895 0.01099 0.00248 -0.0963 0.2801 0.1887
1.750 0.7170 0.01102 0.00258 -0.0962 0.2747 0.2250
2.000 0.7443 0.01105 0.00269 -0.0961 0.2699 0.2770
2.250 0.7719 0.01103 0.00281 -0.0960 0.2662 0.3346
2.500 0.7991 0.01096 0.00298 -0.0959 0.2624 0.4437
2.750 0.8260 0.01092 0.00312 -0.0957 0.2588 0.5344
3.250 0.8800 0.01033 0.00336 -0.0952 0.2516 1.0000
3.500 0.9073 0.01048 0.00348 -0.0950 0.2482 1.0000
3.750 0.9345 0.01065 0.00362 -0.0948 0.2451 1.0000
4.000 0.9615 0.01084 0.00377 -0.0946 0.2423 1.0000
4.250 0.9883 0.01104 0.00394 -0.0943 0.2397 1.0000
4.500 1.0150 0.01124 0.00413 -0.0941 0.2374 1.0000
4.750 1.0421 0.01140 0.00429 -0.0939 0.2361 1.0000
5.000 1.0690 0.01157 0.00448 -0.0936 0.2347 1.0000
5.250 1.0957 0.01175 0.00467 -0.0934 0.2334 1.0000
5.500 1.1224 0.01194 0.00488 -0.0932 0.2321 1.0000
5.750 1.1489 0.01213 0.00508 -0.0929 0.2302 1.0000
6.000 1.1752 0.01235 0.00529 -0.0926 0.2267 1.0000
6.250 1.2011 0.01259 0.00553 -0.0923 0.2237 1.0000
6.500 1.2270 0.01285 0.00579 -0.0920 0.2218 1.0000
6.750 1.2533 0.01304 0.00603 -0.0917 0.2202 1.0000
7.000 1.2796 0.01322 0.00627 -0.0915 0.2184 1.0000
7.250 1.3056 0.01343 0.00652 -0.0912 0.2168 1.0000
7.500 1.3314 0.01364 0.00678 -0.0909 0.2138 1.0000
7.750 1.3567 0.01390 0.00704 -0.0905 0.2091 1.0000
8.000 1.3821 0.01415 0.00730 -0.0902 0.2034 1.0000
8.250 1.4075 0.01437 0.00755 -0.0898 0.1966 1.0000
8.500 1.4322 0.01467 0.00786 -0.0894 0.1889 1.0000
9.000 1.4680 0.01677 0.00945 -0.0872 0.1021 1.0000
9.250 1.4828 0.01811 0.01059 -0.0856 0.0621 1.0000
9.500 1.5006 0.01905 0.01149 -0.0844 0.0490 1.0000
9.750 1.5203 0.01973 0.01221 -0.0834 0.0424 1.0000
10.000 1.5386 0.02051 0.01302 -0.0822 0.0362 1.0000
10.250 1.5562 0.02130 0.01381 -0.0810 0.0301 1.0000
10.500 1.5727 0.02212 0.01464 -0.0796 0.0245 1.0000
10.750 1.5877 0.02300 0.01555 -0.0781 0.0200 1.0000
11.000 1.6014 0.02391 0.01650 -0.0764 0.0173 1.0000
11.250 1.6112 0.02487 0.01751 -0.0742 0.0155 1.0000
11.500 1.6195 0.02593 0.01864 -0.0718 0.0143 1.0000
11.750 1.6276 0.02704 0.01984 -0.0697 0.0134 1.0000
12.000 1.6337 0.02835 0.02124 -0.0676 0.0127 1.0000
12.250 1.6377 0.02992 0.02290 -0.0657 0.0121 1.0000
12.500 1.6391 0.03187 0.02497 -0.0641 0.0115 1.0000
12.750 1.6389 0.03421 0.02742 -0.0629 0.0111 1.0000
13.000 1.6403 0.03664 0.02997 -0.0623 0.0107 1.0000
13.250 1.6395 0.03956 0.03303 -0.0622 0.0104 1.0000
13.500 1.6364 0.04296 0.03656 -0.0624 0.0101 1.0000
13.750 1.6306 0.04686 0.04059 -0.0630 0.0098 1.0000
14.000 1.6217 0.05133 0.04520 -0.0638 0.0096 1.0000
14.250 1.6099 0.05641 0.05042 -0.0651 0.0094 1.0000
14.500 1.5949 0.06203 0.05619 -0.0665 0.0093 1.0000
14.750 1.5773 0.06815 0.06246 -0.0682 0.0092 1.0000
15.000 1.5577 0.07459 0.06904 -0.0699 0.0091 1.0000
15.250 1.5375 0.08125 0.07583 -0.0718 0.0091 1.0000
15.500 1.5179 0.08793 0.08265 -0.0737 0.0090 1.0000
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Polar data table (+)
Polar graphs
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