GOE 625 AIRFOIL (goe625-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 625 AIRFOIL (goe625-il) Reynolds number: 100,000 Max Cl/Cd: 42.44 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe625-il-100000-n5.txt Download as CSV file: xf-goe625-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 625 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.0748 0.10789 0.10224 -0.0965 0.9368 0.0749
-11.250 -0.0743 0.10299 0.09731 -0.0997 0.9300 0.0758
-11.000 -0.0962 0.09467 0.08896 -0.1050 0.9225 0.0779
-10.750 -0.0729 0.09337 0.08763 -0.1060 0.9161 0.0790
-10.500 -0.0653 0.09094 0.08519 -0.1066 0.9056 0.0803
-10.250 -0.0628 0.08668 0.08088 -0.1092 0.8986 0.0818
-10.000 -0.2563 0.05473 0.04858 -0.1316 0.8826 0.0862
-9.750 -0.2390 0.05426 0.04812 -0.1308 0.8737 0.0871
-9.500 -0.2358 0.05236 0.04613 -0.1302 0.8642 0.0882
-9.250 -0.2463 0.04893 0.04248 -0.1298 0.8556 0.0896
-9.000 -0.2630 0.04489 0.03805 -0.1284 0.8460 0.0916
-8.750 -0.2772 0.03949 0.03181 -0.1274 0.8401 0.0943
-8.500 -0.2648 0.03879 0.03110 -0.1255 0.8307 0.0955
-8.250 -0.2406 0.03815 0.03045 -0.1252 0.8247 0.0969
-8.000 -0.2182 0.03701 0.02916 -0.1250 0.8194 0.0987
-7.750 -0.2065 0.03577 0.02772 -0.1232 0.8102 0.1004
-7.500 -0.1884 0.03383 0.02535 -0.1227 0.8042 0.1029
-7.250 -0.1691 0.03252 0.02380 -0.1218 0.7975 0.1046
-7.000 -0.1477 0.03197 0.02323 -0.1209 0.7893 0.1060
-6.750 -0.1200 0.03112 0.02228 -0.1210 0.7836 0.1077
-6.500 -0.1007 0.03042 0.02146 -0.1198 0.7745 0.1095
-6.250 -0.0763 0.02941 0.02021 -0.1193 0.7669 0.1117
-6.000 -0.0523 0.02835 0.01884 -0.1188 0.7593 0.1138
-5.750 -0.0294 0.02769 0.01812 -0.1180 0.7499 0.1153
-5.500 -0.0002 0.02708 0.01746 -0.1181 0.7430 0.1172
-5.250 0.0209 0.02668 0.01702 -0.1169 0.7322 0.1191
-5.000 0.0505 0.02596 0.01612 -0.1171 0.7250 0.1217
-4.750 0.0717 0.02544 0.01548 -0.1159 0.7133 0.1239
-4.500 0.1004 0.02475 0.01460 -0.1158 0.7046 0.1262
-4.250 0.1234 0.02441 0.01429 -0.1150 0.6924 0.1283
-4.000 0.1494 0.02403 0.01385 -0.1145 0.6812 0.1312
-3.750 0.1764 0.02359 0.01328 -0.1141 0.6698 0.1348
-3.500 0.2007 0.02322 0.01275 -0.1134 0.6568 0.1384
-3.250 0.2269 0.02285 0.01238 -0.1130 0.6451 0.1414
-3.000 0.2528 0.02256 0.01202 -0.1125 0.6330 0.1456
-2.750 0.2777 0.02233 0.01166 -0.1118 0.6205 0.1512
-2.500 0.3041 0.02206 0.01136 -0.1115 0.6095 0.1567
-2.250 0.3290 0.02191 0.01113 -0.1109 0.5977 0.1638
-2.000 0.3544 0.02173 0.01088 -0.1104 0.5870 0.1711
-1.750 0.3801 0.02160 0.01067 -0.1100 0.5769 0.1792
-1.500 0.4051 0.02151 0.01052 -0.1094 0.5673 0.1881
-1.250 0.4307 0.02144 0.01039 -0.1090 0.5586 0.1977
-1.000 0.4561 0.02140 0.01030 -0.1086 0.5509 0.2077
-0.750 0.4813 0.02138 0.01025 -0.1082 0.5435 0.2182
-0.500 0.5083 0.02135 0.01015 -0.1081 0.5377 0.2290
-0.250 0.5333 0.02139 0.01019 -0.1077 0.5316 0.2415
0.000 0.5585 0.02139 0.01025 -0.1074 0.5258 0.2576
0.250 0.5852 0.02137 0.01026 -0.1073 0.5209 0.2813
0.500 0.6118 0.02131 0.01032 -0.1072 0.5162 0.3191
0.750 0.6355 0.02121 0.01052 -0.1068 0.5109 0.3907
1.000 0.6579 0.02088 0.01072 -0.1059 0.5062 0.5351
1.250 0.6773 0.02049 0.01101 -0.1034 0.5024 0.7540
1.500 0.7284 0.02060 0.01123 -0.1072 0.4986 0.9428
1.750 0.7732 0.02095 0.01150 -0.1109 0.4942 1.0000
2.000 0.7944 0.02125 0.01170 -0.1099 0.4903 1.0000
2.250 0.8171 0.02154 0.01186 -0.1092 0.4866 1.0000
2.500 0.8418 0.02183 0.01200 -0.1088 0.4832 1.0000
2.750 0.8697 0.02213 0.01212 -0.1089 0.4803 1.0000
3.000 0.8898 0.02252 0.01248 -0.1078 0.4770 1.0000
3.250 0.9107 0.02291 0.01285 -0.1069 0.4736 1.0000
3.500 0.9329 0.02328 0.01317 -0.1061 0.4700 1.0000
3.750 0.9569 0.02364 0.01345 -0.1057 0.4667 1.0000
4.000 0.9830 0.02398 0.01368 -0.1056 0.4636 1.0000
4.250 1.0113 0.02434 0.01389 -0.1059 0.4606 1.0000
4.500 1.0250 0.02483 0.01445 -0.1038 0.4560 1.0000
4.750 1.0426 0.02525 0.01487 -0.1023 0.4512 1.0000
5.000 1.0649 0.02559 0.01513 -0.1016 0.4467 1.0000
5.250 1.0918 0.02590 0.01531 -0.1017 0.4429 1.0000
5.500 1.1115 0.02638 0.01578 -0.1007 0.4394 1.0000
5.750 1.1250 0.02696 0.01643 -0.0986 0.4356 1.0000
6.000 1.1417 0.02748 0.01698 -0.0972 0.4319 1.0000
6.250 1.1618 0.02794 0.01742 -0.0962 0.4284 1.0000
6.500 1.1860 0.02831 0.01773 -0.0960 0.4252 1.0000
6.750 1.2164 0.02866 0.01797 -0.0967 0.4223 1.0000
7.000 1.2183 0.02943 0.01888 -0.0929 0.4186 1.0000
7.250 1.2252 0.03021 0.01975 -0.0901 0.4147 1.0000
7.500 1.2385 0.03087 0.02045 -0.0883 0.4111 1.0000
7.750 1.2581 0.03138 0.02095 -0.0875 0.4077 1.0000
8.000 1.2844 0.03171 0.02121 -0.0876 0.4047 1.0000
8.250 1.2978 0.03245 0.02198 -0.0859 0.4013 1.0000
8.500 1.2922 0.03379 0.02351 -0.0819 0.3968 1.0000
8.750 1.2981 0.03482 0.02461 -0.0796 0.3926 1.0000
9.000 1.3147 0.03543 0.02522 -0.0786 0.3888 1.0000
9.250 1.3410 0.03567 0.02540 -0.0786 0.3857 1.0000
9.500 1.3394 0.03715 0.02701 -0.0757 0.3816 1.0000
9.750 1.3264 0.03934 0.02939 -0.0720 0.3765 1.0000
10.000 1.3326 0.04060 0.03071 -0.0702 0.3723 1.0000
10.250 1.3531 0.04105 0.03114 -0.0698 0.3690 1.0000
10.500 1.3706 0.04171 0.03180 -0.0691 0.3656 1.0000
10.750 1.3247 0.04659 0.03701 -0.0639 0.3584 1.0000
11.000 1.3294 0.04818 0.03864 -0.0625 0.3538 1.0000
11.250 1.3551 0.04815 0.03857 -0.0624 0.3507 1.0000
11.500 1.2810 0.05678 0.04755 -0.0579 0.3408 1.0000
11.750 1.2892 0.05834 0.04913 -0.0572 0.3364 1.0000
12.000 1.3188 0.05779 0.04854 -0.0571 0.3340 1.0000
12.500 1.2487 0.07073 0.06178 -0.0547 0.3182 1.0000
13.000 1.1936 0.08378 0.07503 -0.0545 0.3023 1.0000
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Polar data table (+)
Polar graphs
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