GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il) Reynolds number: 100,000 Max Cl/Cd: 60.19 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe124-il-100000.txt Download as CSV file: xf-goe124-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 124 (MVA H.4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2843 0.09718 0.09250 -0.0273 1.0000 0.0597
-7.500 -0.2816 0.09484 0.09023 -0.0275 1.0000 0.0612
-7.250 -0.2833 0.09298 0.08847 -0.0272 1.0000 0.0627
-7.000 -0.2898 0.09164 0.08725 -0.0263 1.0000 0.0640
-6.750 -0.3036 0.09106 0.08679 -0.0242 1.0000 0.0649
-6.500 -0.3192 0.09078 0.08661 -0.0223 1.0000 0.0657
-6.250 -0.3311 0.09075 0.08666 -0.0233 1.0000 0.0668
-6.000 -0.2998 0.08647 0.08231 -0.0363 0.9943 0.0686
-5.750 -0.2841 0.08163 0.07751 -0.0339 0.9893 0.0708
-5.500 -0.2501 0.07733 0.07316 -0.0399 0.9833 0.0746
-5.250 -0.1745 0.07318 0.06864 -0.0651 0.9724 0.0823
-5.000 -0.1616 0.06801 0.06359 -0.0625 0.9669 0.0842
-4.750 -0.1326 0.06449 0.06006 -0.0653 0.9597 0.0895
-4.500 -0.0763 0.05988 0.05523 -0.0787 0.9532 0.0990
-4.250 -0.0476 0.05668 0.05201 -0.0810 0.9453 0.1046
-4.000 0.0079 0.05239 0.04752 -0.0917 0.9411 0.1156
-3.750 0.0521 0.04950 0.04440 -0.0990 0.9320 0.1292
-3.500 0.0960 0.04639 0.04114 -0.1047 0.9266 0.1448
-3.250 0.1270 0.04390 0.03861 -0.1073 0.9178 0.1610
-3.000 0.1625 0.04127 0.03595 -0.1102 0.9114 0.1790
-2.750 0.1979 0.03949 0.03400 -0.1136 0.9022 0.2069
-2.500 0.2285 0.03714 0.03168 -0.1148 0.8953 0.2291
-2.250 0.2565 0.03557 0.03003 -0.1160 0.8848 0.2690
-1.000 0.4573 0.02527 0.01748 -0.1259 0.8350 0.1408
-0.750 0.4892 0.02378 0.01562 -0.1256 0.8260 0.1208
-0.500 0.5202 0.02291 0.01432 -0.1249 0.8172 0.1099
-0.250 0.5481 0.02207 0.01336 -0.1245 0.8067 0.1065
0.000 0.5767 0.02137 0.01247 -0.1237 0.7989 0.1073
0.250 0.6037 0.02087 0.01189 -0.1231 0.7878 0.1071
0.500 0.6308 0.02039 0.01135 -0.1223 0.7778 0.1064
0.750 0.6578 0.01988 0.01078 -0.1213 0.7693 0.1070
1.000 0.6839 0.01963 0.01054 -0.1206 0.7580 0.1089
1.250 0.7105 0.01941 0.01026 -0.1197 0.7481 0.1124
1.500 0.7379 0.01908 0.00990 -0.1189 0.7386 0.1243
2.000 0.7845 0.01724 0.00985 -0.1161 0.7162 1.0000
2.250 0.8122 0.01732 0.00958 -0.1151 0.7067 1.0000
2.500 0.8385 0.01758 0.00968 -0.1145 0.6939 1.0000
2.750 0.8649 0.01781 0.00980 -0.1139 0.6815 1.0000
3.000 0.8915 0.01801 0.00991 -0.1133 0.6694 1.0000
3.250 0.9185 0.01815 0.00992 -0.1126 0.6580 1.0000
3.500 0.9451 0.01835 0.01003 -0.1120 0.6454 1.0000
3.750 0.9713 0.01864 0.01030 -0.1115 0.6318 1.0000
4.000 0.9975 0.01896 0.01060 -0.1110 0.6187 1.0000
4.250 1.0238 0.01926 0.01088 -0.1105 0.6059 1.0000
4.500 1.0501 0.01949 0.01106 -0.1099 0.5929 1.0000
4.750 1.0766 0.01967 0.01119 -0.1093 0.5801 1.0000
5.000 1.1032 0.01983 0.01129 -0.1087 0.5676 1.0000
5.250 1.1286 0.02014 0.01164 -0.1082 0.5541 1.0000
5.500 1.1541 0.02049 0.01205 -0.1077 0.5415 1.0000
5.750 1.1798 0.02079 0.01238 -0.1072 0.5295 1.0000
6.000 1.2059 0.02104 0.01262 -0.1066 0.5183 1.0000
6.250 1.2319 0.02131 0.01293 -0.1061 0.5074 1.0000
6.500 1.2565 0.02163 0.01335 -0.1055 0.4946 1.0000
6.750 1.2811 0.02188 0.01368 -0.1048 0.4815 1.0000
7.000 1.3059 0.02219 0.01405 -0.1042 0.4693 1.0000
7.250 1.3307 0.02247 0.01441 -0.1035 0.4571 1.0000
7.500 1.3549 0.02272 0.01472 -0.1027 0.4435 1.0000
7.750 1.3780 0.02300 0.01509 -0.1018 0.4281 1.0000
8.000 1.3999 0.02330 0.01551 -0.1007 0.4107 1.0000
8.250 1.4206 0.02360 0.01592 -0.0994 0.3904 1.0000
8.500 1.4396 0.02398 0.01635 -0.0978 0.3662 1.0000
8.750 1.4546 0.02452 0.01691 -0.0957 0.3339 1.0000
9.000 1.4653 0.02534 0.01762 -0.0932 0.2947 1.0000
9.250 1.4731 0.02640 0.01859 -0.0905 0.2505 1.0000
9.500 1.4799 0.02772 0.01976 -0.0880 0.2126 1.0000
9.750 1.4844 0.02934 0.02118 -0.0853 0.1874 1.0000
10.000 1.4871 0.03113 0.02283 -0.0824 0.1701 1.0000
10.250 1.4865 0.03298 0.02462 -0.0791 0.1560 1.0000
10.500 1.4855 0.03504 0.02665 -0.0760 0.1423 1.0000
10.750 1.4830 0.03736 0.02897 -0.0733 0.1283 1.0000
11.000 1.4781 0.04004 0.03161 -0.0707 0.1134 1.0000
11.250 1.4717 0.04302 0.03452 -0.0683 0.0985 1.0000
11.500 1.4668 0.04598 0.03752 -0.0664 0.0858 1.0000
11.750 1.4665 0.04876 0.04038 -0.0646 0.0762 1.0000
12.000 1.4700 0.05135 0.04296 -0.0629 0.0697 1.0000
12.250 1.4731 0.05384 0.04553 -0.0616 0.0645 1.0000
12.500 1.4800 0.05628 0.04793 -0.0601 0.0602 1.0000
12.750 1.4852 0.05891 0.05081 -0.0588 0.0568 1.0000
13.000 1.4931 0.06136 0.05335 -0.0575 0.0541 1.0000
13.250 1.5146 0.06379 0.05566 -0.0558 0.0512 1.0000
13.500 1.5126 0.06720 0.05944 -0.0547 0.0502 1.0000
13.750 1.5085 0.07093 0.06351 -0.0538 0.0491 1.0000
14.000 1.5017 0.07493 0.06781 -0.0533 0.0479 1.0000
14.250 1.4936 0.07916 0.07230 -0.0531 0.0470 1.0000
14.500 1.4837 0.08364 0.07704 -0.0532 0.0462 1.0000
14.750 1.4717 0.08854 0.08219 -0.0537 0.0457 1.0000
15.000 1.4551 0.09420 0.08813 -0.0549 0.0456 1.0000
15.250 1.4338 0.10069 0.09492 -0.0569 0.0457 1.0000
15.500 1.4079 0.10831 0.10283 -0.0602 0.0460 1.0000
15.750 1.3782 0.11721 0.11204 -0.0649 0.0465 1.0000
16.000 1.3450 0.12777 0.12287 -0.0714 0.0474 1.0000
16.250 1.3106 0.13988 0.13521 -0.0794 0.0487 1.0000
16.500 1.2796 0.15245 0.14790 -0.0878 0.0500 1.0000
16.750 1.2557 0.16426 0.15977 -0.0954 0.0509 1.0000
17.000 1.1865 0.20116 0.19659 -0.1181 0.0619 1.0000
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Polar data table (+)
Polar graphs
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