GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Reynolds number: 500,000 Max Cl/Cd: 101.46 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe173-il-500000-n5.txt Download as CSV file: xf-goe173-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 173 (ALBATROS 6020) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2653 0.11002 0.10783 -0.0263 1.0000 0.0078
-9.000 -0.2611 0.10741 0.10525 -0.0266 1.0000 0.0080
-8.750 -0.2574 0.10486 0.10273 -0.0268 1.0000 0.0082
-8.500 -0.2479 0.10170 0.09957 -0.0288 0.9982 0.0087
-8.250 -0.2315 0.09781 0.09569 -0.0331 0.9936 0.0095
-7.750 -0.0932 0.06911 0.06681 -0.0544 0.8561 0.0100
-7.500 -0.1854 0.08661 0.08450 -0.0462 0.9572 0.0097
-7.250 -0.1620 0.08233 0.08018 -0.0531 0.9271 0.0097
-7.000 -0.1402 0.07825 0.07595 -0.0588 0.8811 0.0098
-6.750 -0.1253 0.07488 0.07239 -0.0620 0.8406 0.0098
-6.500 -0.0644 0.05405 0.05134 -0.0597 0.7606 0.0091
-6.250 -0.0994 0.06886 0.06612 -0.0653 0.7932 0.0091
-6.000 -0.0803 0.06540 0.06257 -0.0695 0.7759 0.0084
-5.750 -0.0574 0.06130 0.05837 -0.0750 0.7615 0.0078
-5.500 -0.0311 0.05676 0.05373 -0.0811 0.7493 0.0075
-5.250 -0.0028 0.05255 0.04940 -0.0869 0.7378 0.0075
-5.000 0.0272 0.04854 0.04528 -0.0923 0.7270 0.0077
-4.750 0.0590 0.04444 0.04105 -0.0977 0.7170 0.0080
-4.250 0.1328 0.03388 0.03004 -0.1092 0.6979 0.0095
-4.000 0.1702 0.02796 0.02376 -0.1138 0.6897 0.0100
-3.750 0.1999 0.02573 0.02131 -0.1152 0.6795 0.0106
-3.500 0.2393 0.01633 0.01089 -0.1185 0.6727 0.0138
-3.250 0.2664 0.01618 0.01061 -0.1185 0.6611 0.0145
-3.000 0.2940 0.01572 0.00997 -0.1186 0.6492 0.0155
-2.750 0.3234 0.01406 0.00782 -0.1187 0.6378 0.0188
-2.500 0.3512 0.01324 0.00675 -0.1187 0.6248 0.0202
-2.250 0.3786 0.01306 0.00647 -0.1187 0.6126 0.0212
-2.000 0.4061 0.01286 0.00616 -0.1187 0.6020 0.0230
-1.750 0.4340 0.01238 0.00548 -0.1186 0.5907 0.0245
-1.500 0.4618 0.01207 0.00500 -0.1185 0.5787 0.0259
-1.250 0.4894 0.01206 0.00485 -0.1183 0.5665 0.0269
-1.000 0.5170 0.01144 0.00406 -0.1182 0.5552 0.0277
-0.750 0.5444 0.01098 0.00350 -0.1182 0.5437 0.0284
-0.500 0.5718 0.01070 0.00314 -0.1181 0.5315 0.0291
-0.250 0.5991 0.01052 0.00291 -0.1180 0.5188 0.0302
0.000 0.6265 0.01038 0.00268 -0.1179 0.5052 0.0304
0.250 0.6537 0.01027 0.00249 -0.1178 0.4900 0.0306
0.500 0.6808 0.01023 0.00236 -0.1176 0.4719 0.0310
0.750 0.7076 0.01024 0.00226 -0.1175 0.4492 0.0317
1.000 0.7339 0.01034 0.00221 -0.1172 0.4203 0.0327
1.250 0.7599 0.01052 0.00222 -0.1169 0.3891 0.0339
1.500 0.7859 0.01070 0.00226 -0.1167 0.3656 0.0350
1.750 0.8123 0.01086 0.00232 -0.1165 0.3487 0.0359
2.000 0.8388 0.01102 0.00239 -0.1163 0.3362 0.0365
2.250 0.8653 0.01117 0.00248 -0.1161 0.3261 0.0388
2.500 0.8921 0.01129 0.00257 -0.1159 0.3183 0.0422
2.750 0.9186 0.01144 0.00270 -0.1157 0.3111 0.0459
3.000 0.9462 0.01058 0.00307 -0.1165 0.3054 0.6593
3.500 0.9927 0.01031 0.00334 -0.1145 0.2951 1.0000
3.750 1.0195 0.01047 0.00349 -0.1143 0.2908 1.0000
4.000 1.0459 0.01065 0.00366 -0.1141 0.2862 1.0000
4.250 1.0720 0.01087 0.00385 -0.1139 0.2818 1.0000
4.500 1.0983 0.01106 0.00403 -0.1137 0.2781 1.0000
4.750 1.1246 0.01124 0.00423 -0.1135 0.2743 1.0000
5.000 1.1507 0.01144 0.00444 -0.1133 0.2707 1.0000
5.250 1.1762 0.01169 0.00468 -0.1130 0.2667 1.0000
5.500 1.2022 0.01188 0.00488 -0.1128 0.2601 1.0000
5.750 1.2275 0.01213 0.00513 -0.1125 0.2529 1.0000
6.000 1.2530 0.01235 0.00535 -0.1122 0.2445 1.0000
6.250 1.2777 0.01265 0.00561 -0.1118 0.2345 1.0000
6.500 1.3022 0.01296 0.00588 -0.1114 0.2217 1.0000
6.750 1.3257 0.01335 0.00620 -0.1109 0.1996 1.0000
7.000 1.3354 0.01515 0.00733 -0.1085 0.0989 1.0000
7.250 1.3434 0.01714 0.00885 -0.1057 0.0163 1.0000
7.500 1.3642 0.01775 0.00952 -0.1047 0.0116 1.0000
7.750 1.3856 0.01827 0.01013 -0.1038 0.0101 1.0000
8.000 1.4062 0.01883 0.01079 -0.1028 0.0089 1.0000
8.250 1.4253 0.01950 0.01154 -0.1016 0.0078 1.0000
8.500 1.4426 0.02029 0.01244 -0.1001 0.0069 1.0000
8.750 1.4604 0.02098 0.01323 -0.0987 0.0064 1.0000
9.000 1.4764 0.02177 0.01412 -0.0970 0.0060 1.0000
9.250 1.4904 0.02264 0.01507 -0.0951 0.0056 1.0000
9.500 1.5007 0.02355 0.01609 -0.0926 0.0052 1.0000
9.750 1.5070 0.02473 0.01736 -0.0897 0.0049 1.0000
10.000 1.5133 0.02594 0.01868 -0.0869 0.0046 1.0000
10.250 1.5210 0.02709 0.01994 -0.0845 0.0043 1.0000
10.500 1.5253 0.02855 0.02152 -0.0820 0.0041 1.0000
10.750 1.5279 0.03026 0.02335 -0.0797 0.0040 1.0000
11.000 1.5293 0.03222 0.02543 -0.0777 0.0038 1.0000
11.250 1.5297 0.03445 0.02778 -0.0760 0.0037 1.0000
11.500 1.5298 0.03691 0.03036 -0.0748 0.0036 1.0000
11.750 1.5283 0.03970 0.03327 -0.0739 0.0035 1.0000
12.000 1.5256 0.04279 0.03647 -0.0733 0.0034 1.0000
12.250 1.5212 0.04620 0.04003 -0.0729 0.0033 1.0000
12.500 1.5145 0.04999 0.04394 -0.0727 0.0032 1.0000
12.750 1.5055 0.05421 0.04828 -0.0727 0.0032 1.0000
13.000 1.4944 0.05878 0.05298 -0.0729 0.0031 1.0000
13.250 1.4817 0.06365 0.05798 -0.0732 0.0031 1.0000
13.500 1.4722 0.06824 0.06269 -0.0736 0.0031 1.0000
13.750 1.4640 0.07273 0.06731 -0.0741 0.0030 1.0000
14.000 1.4561 0.07728 0.07198 -0.0747 0.0030 1.0000
14.250 1.4488 0.08182 0.07664 -0.0754 0.0030 1.0000
14.500 1.4418 0.08632 0.08126 -0.0760 0.0029 1.0000
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Polar data table (+)
Polar graphs
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