GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 123 AIRFOIL (goe123-il) Reynolds number: 500,000 Max Cl/Cd: 102.15 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe123-il-500000-n5.txt Download as CSV file: xf-goe123-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 123 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 -0.2765 0.09304 0.09078 -0.0358 0.9577 0.0094
-8.000 -0.2710 0.08884 0.08656 -0.0384 0.9442 0.0097
-7.750 -0.2620 0.08646 0.08416 -0.0397 0.9335 0.0099
-7.500 -0.2507 0.08445 0.08214 -0.0412 0.9246 0.0102
-7.250 -0.2373 0.08200 0.07967 -0.0435 0.9172 0.0108
-7.000 -0.2226 0.07887 0.07650 -0.0469 0.9095 0.0114
-6.750 -0.2067 0.07523 0.07283 -0.0511 0.9027 0.0117
-6.500 -0.1879 0.07117 0.06873 -0.0561 0.8954 0.0121
-6.250 -0.1649 0.06574 0.06322 -0.0633 0.8891 0.0128
-6.000 -0.1443 0.06386 0.06133 -0.0656 0.8834 0.0131
-5.750 -0.1218 0.06159 0.05901 -0.0686 0.8777 0.0140
-5.500 -0.0959 0.05815 0.05550 -0.0732 0.8721 0.0149
-5.250 -0.0659 0.05377 0.05103 -0.0792 0.8652 0.0156
-5.000 -0.0344 0.04956 0.04669 -0.0849 0.8587 0.0166
-4.750 -0.0104 0.04803 0.04512 -0.0865 0.8506 0.0173
-4.250 0.0514 0.04195 0.03880 -0.0940 0.8377 0.0193
-4.000 0.0924 0.03715 0.03377 -0.0998 0.8324 0.0211
-3.750 0.1143 0.03646 0.03307 -0.1000 0.8270 0.0220
-3.500 0.1430 0.03485 0.03138 -0.1017 0.8211 0.0241
-3.250 0.1756 0.03196 0.02831 -0.1043 0.8156 0.0239
-3.000 0.2081 0.02931 0.02550 -0.1064 0.8102 0.0241
-2.750 0.2403 0.02684 0.02284 -0.1081 0.8035 0.0246
-2.500 0.2728 0.02435 0.02011 -0.1095 0.7960 0.0253
-2.250 0.3041 0.02190 0.01742 -0.1105 0.7859 0.0253
-2.000 0.3349 0.01973 0.01498 -0.1112 0.7748 0.0256
-1.750 0.3651 0.01761 0.01259 -0.1118 0.7647 0.0258
-1.250 0.4246 0.01429 0.00868 -0.1125 0.7481 0.0264
-1.000 0.4534 0.01300 0.00712 -0.1127 0.7400 0.0263
-0.750 0.4819 0.01224 0.00615 -0.1128 0.7314 0.0264
-0.500 0.5101 0.01143 0.00512 -0.1129 0.7221 0.0267
-0.250 0.5382 0.01051 0.00402 -0.1129 0.7123 0.0273
0.000 0.5660 0.01007 0.00348 -0.1129 0.7028 0.0279
0.250 0.5936 0.00977 0.00311 -0.1128 0.6915 0.0283
0.750 0.6483 0.00939 0.00259 -0.1126 0.6597 0.0293
1.000 0.6751 0.00932 0.00243 -0.1123 0.6350 0.0303
1.250 0.7014 0.00931 0.00228 -0.1120 0.6026 0.0308
1.500 0.7271 0.00940 0.00217 -0.1116 0.5622 0.0309
1.750 0.7530 0.00951 0.00212 -0.1113 0.5292 0.0311
2.000 0.7793 0.00962 0.00211 -0.1111 0.5030 0.0315
2.250 0.8057 0.00974 0.00214 -0.1108 0.4799 0.0320
2.500 0.8324 0.00984 0.00217 -0.1107 0.4601 0.0329
2.750 0.8588 0.01000 0.00223 -0.1105 0.4372 0.0339
3.000 0.8847 0.01022 0.00233 -0.1102 0.4086 0.0349
3.250 0.9105 0.01045 0.00245 -0.1099 0.3833 0.0370
3.500 0.9366 0.01066 0.00259 -0.1097 0.3624 0.0420
3.750 0.9628 0.01080 0.00280 -0.1095 0.3456 0.0946
4.000 0.9889 0.01099 0.00302 -0.1093 0.3317 0.1314
4.250 1.0147 0.01121 0.00322 -0.1091 0.3161 0.1497
4.500 1.0401 0.01147 0.00344 -0.1088 0.2977 0.1705
5.000 1.0869 0.01064 0.00397 -0.1075 0.2734 1.0000
5.250 1.1126 0.01090 0.00420 -0.1072 0.2623 1.0000
5.500 1.1379 0.01119 0.00444 -0.1069 0.2490 1.0000
5.750 1.1627 0.01155 0.00473 -0.1065 0.2286 1.0000
6.000 1.1862 0.01203 0.00506 -0.1060 0.1998 1.0000
6.250 1.2091 0.01257 0.00545 -0.1054 0.1716 1.0000
6.500 1.2318 0.01314 0.00588 -0.1047 0.1456 1.0000
6.750 1.2504 0.01416 0.00657 -0.1036 0.0900 1.0000
7.000 1.2728 0.01473 0.00709 -0.1028 0.0752 1.0000
7.250 1.2934 0.01548 0.00770 -0.1019 0.0454 1.0000
7.500 1.3134 0.01627 0.00838 -0.1009 0.0304 1.0000
7.750 1.3357 0.01678 0.00893 -0.1001 0.0255 1.0000
8.000 1.3570 0.01736 0.00955 -0.0992 0.0210 1.0000
8.250 1.3781 0.01794 0.01017 -0.0983 0.0178 1.0000
8.500 1.3990 0.01851 0.01078 -0.0974 0.0155 1.0000
8.750 1.4182 0.01923 0.01152 -0.0962 0.0136 1.0000
9.000 1.4374 0.01991 0.01229 -0.0950 0.0125 1.0000
9.250 1.4562 0.02056 0.01301 -0.0938 0.0115 1.0000
9.500 1.4742 0.02124 0.01375 -0.0925 0.0105 1.0000
9.750 1.4899 0.02208 0.01464 -0.0909 0.0096 1.0000
10.000 1.5020 0.02310 0.01574 -0.0887 0.0090 1.0000
10.250 1.5143 0.02392 0.01666 -0.0865 0.0086 1.0000
10.500 1.5252 0.02486 0.01772 -0.0842 0.0082 1.0000
10.750 1.5350 0.02590 0.01886 -0.0819 0.0079 1.0000
11.000 1.5441 0.02703 0.02008 -0.0797 0.0075 1.0000
11.250 1.5527 0.02822 0.02136 -0.0776 0.0072 1.0000
11.500 1.5606 0.02950 0.02273 -0.0756 0.0069 1.0000
11.750 1.5657 0.03107 0.02438 -0.0735 0.0066 1.0000
12.000 1.5645 0.03325 0.02668 -0.0710 0.0063 1.0000
12.250 1.5707 0.03485 0.02839 -0.0694 0.0061 1.0000
12.500 1.5749 0.03670 0.03038 -0.0677 0.0059 1.0000
12.750 1.5771 0.03881 0.03263 -0.0661 0.0058 1.0000
13.000 1.5777 0.04115 0.03510 -0.0647 0.0056 1.0000
13.250 1.5776 0.04369 0.03777 -0.0634 0.0055 1.0000
13.500 1.5764 0.04641 0.04062 -0.0624 0.0053 1.0000
13.750 1.5742 0.04936 0.04370 -0.0615 0.0052 1.0000
14.000 1.5712 0.05252 0.04700 -0.0609 0.0051 1.0000
14.250 1.5673 0.05590 0.05051 -0.0605 0.0050 1.0000
14.500 1.5625 0.05953 0.05427 -0.0604 0.0049 1.0000
14.750 1.5568 0.06349 0.05837 -0.0607 0.0048 1.0000
15.000 1.5505 0.06767 0.06269 -0.0612 0.0048 1.0000
15.250 1.5434 0.07217 0.06733 -0.0620 0.0047 1.0000
15.500 1.5353 0.07699 0.07229 -0.0631 0.0046 1.0000
15.750 1.5261 0.08211 0.07755 -0.0645 0.0046 1.0000
16.000 1.5161 0.08749 0.08305 -0.0661 0.0045 1.0000
16.250 1.5053 0.09312 0.08882 -0.0680 0.0045 1.0000
16.500 1.4938 0.09899 0.09483 -0.0700 0.0045 1.0000
16.750 1.4818 0.10504 0.10101 -0.0723 0.0044 1.0000
17.000 1.4694 0.11124 0.10735 -0.0747 0.0044 1.0000
17.250 1.4567 0.11763 0.11387 -0.0774 0.0043 1.0000
17.500 1.4443 0.12411 0.12047 -0.0802 0.0043 1.0000
17.750 1.4318 0.13069 0.12719 -0.0833 0.0043 1.0000
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Polar data table (+)
Polar graphs
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