GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.65 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe140-il-1000000.txt Download as CSV file: xf-goe140-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 140 (MVA H.17) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3035 0.09522 0.09373 -0.0190 1.0000 0.0141
-8.000 -0.2967 0.09247 0.09100 -0.0203 1.0000 0.0146
-7.750 -0.2914 0.08962 0.08817 -0.0216 1.0000 0.0156
-7.500 -0.2791 0.08491 0.08347 -0.0294 0.9880 0.0164
-7.250 -0.1966 0.06443 0.06279 -0.0378 0.8741 0.0167
-7.000 -0.1888 0.06160 0.05987 -0.0385 0.8501 0.0169
-6.750 -0.1785 0.05885 0.05704 -0.0401 0.8303 0.0172
-6.500 -0.1669 0.05570 0.05382 -0.0427 0.8128 0.0175
-6.250 -0.1535 0.05235 0.05040 -0.0459 0.7966 0.0181
-6.000 -0.1377 0.04867 0.04664 -0.0498 0.7815 0.0193
-5.750 -0.1084 0.04258 0.04042 -0.0608 0.7700 0.0206
-5.500 -0.0867 0.03803 0.03574 -0.0651 0.7560 0.0207
-4.500 -0.0115 0.04021 0.03734 -0.0791 0.7254 0.0223
-4.250 0.0164 0.03798 0.03496 -0.0811 0.7054 0.0234
-4.000 0.0545 0.03543 0.03212 -0.0835 0.6857 0.0259
-3.750 0.0852 0.03271 0.02917 -0.0851 0.6662 0.0261
-3.500 0.1165 0.02655 0.02260 -0.0882 0.6500 0.0268
-3.250 0.1433 0.02520 0.02110 -0.0891 0.6294 0.0272
-3.000 0.1708 0.02409 0.01983 -0.0897 0.6102 0.0278
-2.750 0.1990 0.02295 0.01851 -0.0904 0.5921 0.0285
-2.500 0.2282 0.02169 0.01707 -0.0910 0.5744 0.0296
-2.250 0.2592 0.02096 0.01613 -0.0909 0.5563 0.0326
-2.000 0.2894 0.02002 0.01495 -0.0911 0.5383 0.0331
-1.750 0.3208 0.01618 0.01066 -0.0926 0.5228 0.0348
-1.500 0.3491 0.01571 0.01008 -0.0929 0.5057 0.0356
-1.000 0.4100 0.01251 0.00626 -0.0934 0.4762 0.0320
-0.750 0.4393 0.01141 0.00493 -0.0936 0.4627 0.0315
-0.500 0.4683 0.01072 0.00408 -0.0938 0.4500 0.0314
-0.250 0.4970 0.01027 0.00351 -0.0939 0.4380 0.0316
0.000 0.5257 0.01003 0.00318 -0.0940 0.4267 0.0323
0.250 0.5543 0.00988 0.00296 -0.0941 0.4159 0.0327
0.500 0.5829 0.00978 0.00282 -0.0943 0.4067 0.0331
0.750 0.6116 0.00956 0.00251 -0.0945 0.3976 0.0336
1.000 0.6405 0.00940 0.00228 -0.0947 0.3881 0.0343
1.250 0.6692 0.00933 0.00216 -0.0948 0.3789 0.0353
1.500 0.6977 0.00933 0.00212 -0.0950 0.3703 0.0373
1.750 0.7263 0.00932 0.00209 -0.0951 0.3635 0.0394
2.000 0.7547 0.00937 0.00209 -0.0952 0.3560 0.0419
2.250 0.7833 0.00937 0.00216 -0.0953 0.3497 0.0603
2.500 0.8115 0.00946 0.00224 -0.0954 0.3428 0.0748
2.750 0.8397 0.00953 0.00230 -0.0955 0.3368 0.0820
3.000 0.8679 0.00960 0.00236 -0.0956 0.3306 0.0877
3.250 0.8959 0.00970 0.00245 -0.0957 0.3243 0.0955
3.500 0.9242 0.00973 0.00254 -0.0959 0.3184 0.1181
4.000 0.9749 0.00841 0.00290 -0.0954 0.3013 1.0000
4.250 1.0026 0.00858 0.00301 -0.0955 0.2939 1.0000
4.500 1.0304 0.00872 0.00312 -0.0956 0.2868 1.0000
4.750 1.0580 0.00891 0.00325 -0.0956 0.2781 1.0000
5.000 1.0854 0.00910 0.00340 -0.0956 0.2689 1.0000
5.250 1.1127 0.00930 0.00354 -0.0956 0.2579 1.0000
5.500 1.1396 0.00954 0.00372 -0.0956 0.2447 1.0000
5.750 1.1656 0.00992 0.00396 -0.0955 0.2228 1.0000
6.000 1.1843 0.01136 0.00478 -0.0946 0.1227 1.0000
6.500 1.2256 0.01363 0.00648 -0.0929 0.0157 1.0000
6.750 1.2512 0.01397 0.00685 -0.0926 0.0144 1.0000
7.000 1.2763 0.01434 0.00727 -0.0923 0.0135 1.0000
7.250 1.3009 0.01477 0.00775 -0.0919 0.0125 1.0000
7.500 1.3245 0.01531 0.00834 -0.0913 0.0117 1.0000
7.750 1.3460 0.01610 0.00923 -0.0905 0.0109 1.0000
8.000 1.3688 0.01666 0.00984 -0.0898 0.0106 1.0000
8.250 1.3915 0.01719 0.01042 -0.0892 0.0103 1.0000
8.500 1.4134 0.01779 0.01107 -0.0884 0.0099 1.0000
8.750 1.4344 0.01843 0.01175 -0.0876 0.0093 1.0000
9.000 1.4541 0.01915 0.01253 -0.0866 0.0088 1.0000
9.250 1.4718 0.02001 0.01346 -0.0853 0.0085 1.0000
9.500 1.4849 0.02119 0.01471 -0.0834 0.0082 1.0000
9.750 1.4882 0.02297 0.01661 -0.0801 0.0079 1.0000
10.000 1.4908 0.02448 0.01821 -0.0767 0.0078 1.0000
10.250 1.5001 0.02532 0.01911 -0.0742 0.0077 1.0000
10.500 1.5058 0.02648 0.02036 -0.0715 0.0076 1.0000
10.750 1.5100 0.02790 0.02186 -0.0690 0.0074 1.0000
11.000 1.5134 0.02955 0.02360 -0.0670 0.0073 1.0000
11.250 1.5154 0.03155 0.02569 -0.0653 0.0071 1.0000
11.500 1.5153 0.03398 0.02821 -0.0641 0.0070 1.0000
11.750 1.5153 0.03664 0.03096 -0.0633 0.0069 1.0000
12.000 1.5140 0.03961 0.03402 -0.0628 0.0068 1.0000
12.250 1.5123 0.04278 0.03729 -0.0626 0.0067 1.0000
12.500 1.5108 0.04603 0.04062 -0.0626 0.0065 1.0000
12.750 1.5093 0.04936 0.04404 -0.0627 0.0064 1.0000
13.000 1.5077 0.05276 0.04752 -0.0630 0.0063 1.0000
13.250 1.5052 0.05627 0.05110 -0.0633 0.0061 1.0000
13.500 1.5022 0.05990 0.05480 -0.0636 0.0060 1.0000
13.750 1.4983 0.06361 0.05858 -0.0640 0.0059 1.0000
14.000 1.4941 0.06734 0.06238 -0.0643 0.0058 1.0000
14.250 1.4903 0.07098 0.06608 -0.0645 0.0058 1.0000
14.500 1.4874 0.07435 0.06949 -0.0644 0.0057 1.0000
14.750 1.4868 0.07703 0.07220 -0.0634 0.0056 1.0000
15.000 1.4944 0.07758 0.07273 -0.0597 0.0055 1.0000
15.250 1.5089 0.07750 0.07266 -0.0553 0.0054 1.0000
15.500 1.5007 0.08230 0.07761 -0.0572 0.0054 1.0000
15.750 1.4959 0.08659 0.08203 -0.0588 0.0053 1.0000
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Polar data table (+)
Polar graphs
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