GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 123 AIRFOIL (goe123-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.84 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe123-il-1000000-n5.txt Download as CSV file: xf-goe123-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2989 0.09183 0.09001 -0.0309 0.9022 0.0064
-8.000 -0.2928 0.08810 0.08626 -0.0332 0.8942 0.0067
-7.750 -0.2878 0.08276 0.08090 -0.0377 0.8865 0.0072
-7.500 -0.2725 0.08003 0.07814 -0.0409 0.8801 0.0074
-7.000 -0.2378 0.07470 0.07275 -0.0477 0.8686 0.0079
-6.750 -0.2186 0.07161 0.06963 -0.0517 0.8628 0.0084
-6.500 -0.1971 0.06670 0.06467 -0.0581 0.8569 0.0092
-6.250 -0.1724 0.06166 0.05957 -0.0649 0.8499 0.0099
-6.000 -0.1485 0.05925 0.05710 -0.0683 0.8431 0.0101
-5.750 -0.1233 0.05670 0.05450 -0.0719 0.8356 0.0105
-5.500 -0.0965 0.05371 0.05144 -0.0760 0.8282 0.0113
-5.250 -0.0603 0.04704 0.04463 -0.0847 0.8209 0.0128
-5.000 -0.0334 0.04517 0.04268 -0.0872 0.8143 0.0131
-4.750 -0.0055 0.04323 0.04069 -0.0897 0.8085 0.0135
-4.500 0.0238 0.04097 0.03835 -0.0924 0.8026 0.0142
-4.250 0.0675 0.03377 0.03086 -0.1000 0.7975 0.0163
-4.000 0.0953 0.03239 0.02942 -0.1014 0.7916 0.0167
-3.750 0.1223 0.03133 0.02828 -0.1025 0.7851 0.0170
-3.500 0.1511 0.02979 0.02665 -0.1038 0.7772 0.0175
-3.250 0.1817 0.02761 0.02431 -0.1055 0.7675 0.0180
-3.000 0.2134 0.02506 0.02156 -0.1072 0.7558 0.0186
-2.500 0.2845 0.01375 0.00918 -0.1115 0.7366 0.0210
-2.250 0.3132 0.01229 0.00744 -0.1119 0.7267 0.0212
-2.000 0.3414 0.01162 0.00664 -0.1122 0.7191 0.0215
-1.750 0.3696 0.01105 0.00592 -0.1123 0.7103 0.0217
-1.500 0.3980 0.01027 0.00495 -0.1125 0.7013 0.0218
-1.250 0.4262 0.00977 0.00432 -0.1126 0.6921 0.0220
-1.000 0.4544 0.00938 0.00383 -0.1126 0.6826 0.0223
-0.750 0.4824 0.00907 0.00342 -0.1127 0.6717 0.0227
-0.500 0.5102 0.00883 0.00307 -0.1126 0.6548 0.0231
-0.250 0.5374 0.00870 0.00280 -0.1125 0.6276 0.0236
0.000 0.5644 0.00864 0.00256 -0.1124 0.5934 0.0241
0.250 0.5912 0.00863 0.00239 -0.1122 0.5591 0.0245
0.500 0.6181 0.00863 0.00224 -0.1121 0.5293 0.0248
0.750 0.6451 0.00865 0.00212 -0.1120 0.5016 0.0250
1.000 0.6722 0.00866 0.00202 -0.1119 0.4778 0.0252
1.250 0.6994 0.00868 0.00196 -0.1118 0.4561 0.0255
1.500 0.7262 0.00879 0.00195 -0.1117 0.4298 0.0259
1.750 0.7531 0.00890 0.00195 -0.1116 0.4038 0.0261
2.000 0.7800 0.00898 0.00193 -0.1115 0.3801 0.0262
2.250 0.8067 0.00911 0.00196 -0.1114 0.3563 0.0263
2.500 0.8335 0.00923 0.00200 -0.1113 0.3352 0.0265
2.750 0.8606 0.00930 0.00199 -0.1112 0.3209 0.0273
3.000 0.8876 0.00938 0.00203 -0.1111 0.3091 0.0288
3.250 0.9146 0.00949 0.00211 -0.1110 0.2980 0.0303
3.500 0.9414 0.00964 0.00221 -0.1109 0.2848 0.0316
3.750 0.9676 0.00985 0.00235 -0.1107 0.2665 0.0328
4.000 0.9943 0.01001 0.00248 -0.1106 0.2541 0.0344
4.250 1.0209 0.01016 0.00263 -0.1104 0.2429 0.0459
4.500 1.0473 0.01029 0.00284 -0.1103 0.2305 0.1186
4.750 1.0734 0.01050 0.00304 -0.1101 0.2163 0.1382
5.000 1.0989 0.01077 0.00326 -0.1099 0.1970 0.1486
5.250 1.1235 0.01115 0.00353 -0.1095 0.1717 0.1617
5.500 1.1439 0.01032 0.00402 -0.1086 0.1475 1.0000
5.750 1.1655 0.01110 0.00451 -0.1078 0.0941 1.0000
6.000 1.1900 0.01150 0.00484 -0.1074 0.0814 1.0000
6.250 1.2151 0.01180 0.00512 -0.1071 0.0745 1.0000
6.500 1.2400 0.01213 0.00543 -0.1067 0.0669 1.0000
6.750 1.2613 0.01288 0.00598 -0.1058 0.0337 1.0000
7.000 1.2854 0.01328 0.00636 -0.1053 0.0272 1.0000
7.250 1.3096 0.01363 0.00672 -0.1049 0.0236 1.0000
7.500 1.3330 0.01407 0.00715 -0.1043 0.0186 1.0000
7.750 1.3565 0.01447 0.00755 -0.1037 0.0158 1.0000
8.000 1.3794 0.01493 0.00800 -0.1031 0.0130 1.0000
8.250 1.4026 0.01532 0.00842 -0.1025 0.0118 1.0000
8.500 1.4249 0.01579 0.00889 -0.1018 0.0103 1.0000
8.750 1.4466 0.01631 0.00943 -0.1010 0.0090 1.0000
9.000 1.4687 0.01675 0.00993 -0.1002 0.0085 1.0000
9.250 1.4901 0.01724 0.01045 -0.0994 0.0079 1.0000
9.500 1.5108 0.01777 0.01101 -0.0985 0.0073 1.0000
9.750 1.5303 0.01838 0.01165 -0.0974 0.0067 1.0000
10.000 1.5489 0.01904 0.01236 -0.0961 0.0062 1.0000
10.250 1.5681 0.01959 0.01298 -0.0950 0.0059 1.0000
10.500 1.5863 0.02019 0.01364 -0.0937 0.0055 1.0000
10.750 1.6032 0.02084 0.01434 -0.0923 0.0052 1.0000
11.000 1.6177 0.02151 0.01507 -0.0904 0.0050 1.0000
11.250 1.6300 0.02226 0.01587 -0.0882 0.0047 1.0000
11.500 1.6409 0.02313 0.01680 -0.0860 0.0045 1.0000
11.750 1.6487 0.02424 0.01801 -0.0834 0.0043 1.0000
12.000 1.6581 0.02527 0.01913 -0.0812 0.0042 1.0000
12.250 1.6677 0.02633 0.02027 -0.0792 0.0041 1.0000
12.500 1.6762 0.02749 0.02152 -0.0772 0.0040 1.0000
12.750 1.6838 0.02878 0.02291 -0.0752 0.0039 1.0000
13.000 1.6903 0.03020 0.02442 -0.0733 0.0038 1.0000
13.250 1.6961 0.03174 0.02605 -0.0715 0.0036 1.0000
13.500 1.7009 0.03341 0.02783 -0.0698 0.0035 1.0000
13.750 1.7047 0.03524 0.02976 -0.0682 0.0035 1.0000
14.000 1.7078 0.03721 0.03183 -0.0667 0.0034 1.0000
14.250 1.7102 0.03931 0.03402 -0.0654 0.0033 1.0000
14.500 1.7118 0.04158 0.03639 -0.0642 0.0032 1.0000
14.750 1.7118 0.04410 0.03901 -0.0632 0.0031 1.0000
15.000 1.7109 0.04679 0.04180 -0.0624 0.0030 1.0000
15.250 1.7078 0.04987 0.04499 -0.0617 0.0030 1.0000
15.500 1.7026 0.05333 0.04856 -0.0613 0.0029 1.0000
15.750 1.6944 0.05736 0.05271 -0.0613 0.0028 1.0000
16.000 1.6843 0.06190 0.05739 -0.0616 0.0028 1.0000
16.250 1.6716 0.06705 0.06269 -0.0624 0.0027 1.0000
16.500 1.6571 0.07271 0.06849 -0.0636 0.0027 1.0000
16.750 1.6461 0.07804 0.07397 -0.0650 0.0027 1.0000
17.000 1.6335 0.08378 0.07984 -0.0667 0.0027 1.0000
17.250 1.6196 0.08980 0.08599 -0.0686 0.0026 1.0000
17.500 1.6042 0.09623 0.09256 -0.0708 0.0026 1.0000
17.750 1.5884 0.10288 0.09934 -0.0733 0.0026 1.0000
18.000 1.5721 0.10968 0.10627 -0.0759 0.0026 1.0000
18.250 1.5550 0.11674 0.11345 -0.0788 0.0026 1.0000
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