GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 528 AIRFOIL (goe528-il) Reynolds number: 100,000 Max Cl/Cd: 55.67 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe528-il-100000-n5.txt Download as CSV file: xf-goe528-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 528 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1729 0.10994 0.10518 -0.0540 0.9759 0.0587
-9.500 -0.1702 0.10708 0.10234 -0.0619 0.9640 0.0606
-9.250 -0.1569 0.10265 0.09793 -0.0653 0.9555 0.0614
-9.000 -0.1306 0.09866 0.09390 -0.0653 0.9505 0.0636
-8.750 -0.1133 0.09517 0.09040 -0.0687 0.9422 0.0656
-8.500 -0.0962 0.09142 0.08662 -0.0739 0.9348 0.0683
-8.250 -0.0916 0.08818 0.08339 -0.0833 0.9209 0.0709
-8.000 -0.0849 0.08439 0.07957 -0.0914 0.9070 0.0713
-7.750 -0.0591 0.07991 0.07507 -0.0897 0.9034 0.0729
-7.500 -0.0373 0.07702 0.07215 -0.0902 0.8955 0.0755
-7.250 -0.0228 0.07388 0.06896 -0.0935 0.8853 0.0778
-6.750 -0.0170 0.05883 0.05356 -0.1124 0.8576 0.0519
-6.500 -0.0016 0.05389 0.04841 -0.1168 0.8486 0.0520
-6.250 0.0111 0.05022 0.04459 -0.1185 0.8379 0.0519
-6.000 0.0281 0.04721 0.04144 -0.1196 0.8292 0.0515
-5.750 0.0444 0.04388 0.03791 -0.1208 0.8197 0.0511
-5.500 0.0613 0.04038 0.03412 -0.1219 0.8106 0.0507
-5.250 0.0794 0.03617 0.02932 -0.1232 0.8019 0.0515
-5.000 0.0984 0.03324 0.02587 -0.1232 0.7929 0.0520
-4.750 0.1210 0.03098 0.02325 -0.1232 0.7847 0.0522
-4.500 0.1427 0.02916 0.02112 -0.1227 0.7756 0.0524
-4.250 0.1675 0.02754 0.01920 -0.1224 0.7675 0.0529
-4.000 0.1907 0.02644 0.01792 -0.1218 0.7581 0.0539
-3.750 0.2170 0.02544 0.01670 -0.1216 0.7501 0.0555
-3.500 0.2409 0.02444 0.01544 -0.1209 0.7405 0.0569
-3.250 0.2683 0.02331 0.01399 -0.1205 0.7327 0.0577
-3.000 0.2927 0.02243 0.01288 -0.1197 0.7229 0.0586
-2.750 0.3208 0.02158 0.01176 -0.1194 0.7154 0.0596
-2.500 0.3452 0.02100 0.01099 -0.1185 0.7052 0.0609
-2.250 0.3722 0.02036 0.01035 -0.1183 0.6975 0.0633
-2.000 0.3965 0.01996 0.00991 -0.1175 0.6876 0.0660
-1.750 0.4233 0.01948 0.00932 -0.1170 0.6797 0.0683
-1.500 0.4480 0.01912 0.00888 -0.1162 0.6703 0.0707
-1.250 0.4738 0.01872 0.00843 -0.1156 0.6625 0.0739
-1.000 0.4986 0.01847 0.00816 -0.1149 0.6535 0.0796
-0.750 0.5247 0.01820 0.00784 -0.1143 0.6457 0.0884
-0.500 0.5499 0.01796 0.00759 -0.1137 0.6372 0.1027
-0.250 0.5768 0.01759 0.00734 -0.1134 0.6299 0.1460
0.000 0.6019 0.01710 0.00738 -0.1131 0.6215 0.3102
0.500 0.6765 0.01572 0.00734 -0.1164 0.6059 1.0000
0.750 0.7032 0.01587 0.00724 -0.1160 0.5996 1.0000
1.000 0.7267 0.01609 0.00735 -0.1151 0.5914 1.0000
1.250 0.7528 0.01627 0.00733 -0.1146 0.5848 1.0000
1.500 0.7769 0.01650 0.00745 -0.1139 0.5774 1.0000
1.750 0.8020 0.01671 0.00752 -0.1133 0.5706 1.0000
2.000 0.8274 0.01693 0.00762 -0.1127 0.5641 1.0000
2.250 0.8513 0.01718 0.00779 -0.1119 0.5568 1.0000
2.500 0.8777 0.01740 0.00786 -0.1116 0.5511 1.0000
2.750 0.9006 0.01769 0.00812 -0.1107 0.5438 1.0000
3.000 0.9255 0.01794 0.00828 -0.1101 0.5373 1.0000
3.250 0.9504 0.01821 0.00847 -0.1096 0.5312 1.0000
3.500 0.9733 0.01851 0.00875 -0.1087 0.5239 1.0000
3.750 0.9991 0.01876 0.00890 -0.1083 0.5181 1.0000
4.000 1.0211 0.01909 0.00924 -0.1073 0.5110 1.0000
4.250 1.0449 0.01938 0.00950 -0.1066 0.5043 1.0000
4.500 1.0691 0.01967 0.00974 -0.1059 0.4981 1.0000
4.750 1.0904 0.02002 0.01012 -0.1049 0.4907 1.0000
5.000 1.1153 0.02029 0.01032 -0.1043 0.4846 1.0000
5.250 1.1353 0.02066 0.01076 -0.1031 0.4771 1.0000
5.500 1.1580 0.02097 0.01105 -0.1023 0.4704 1.0000
5.750 1.1798 0.02132 0.01140 -0.1013 0.4637 1.0000
6.000 1.1999 0.02168 0.01183 -0.1001 0.4562 1.0000
6.250 1.2236 0.02198 0.01207 -0.0994 0.4503 1.0000
6.500 1.2407 0.02242 0.01262 -0.0978 0.4424 1.0000
6.750 1.2626 0.02274 0.01295 -0.0968 0.4360 1.0000
7.000 1.2805 0.02319 0.01347 -0.0953 0.4288 1.0000
7.250 1.2997 0.02358 0.01391 -0.0940 0.4220 1.0000
7.500 1.3192 0.02399 0.01436 -0.0928 0.4157 1.0000
7.750 1.3354 0.02448 0.01494 -0.0911 0.4084 1.0000
8.000 1.3565 0.02483 0.01526 -0.0901 0.4026 1.0000
8.250 1.3688 0.02544 0.01601 -0.0879 0.3949 1.0000
8.500 1.3861 0.02587 0.01648 -0.0863 0.3886 1.0000
8.750 1.3987 0.02644 0.01714 -0.0841 0.3819 1.0000
9.000 1.4113 0.02700 0.01777 -0.0819 0.3751 1.0000
9.250 1.4256 0.02754 0.01834 -0.0801 0.3687 1.0000
9.500 1.4346 0.02827 0.01919 -0.0776 0.3613 1.0000
9.750 1.4492 0.02879 0.01970 -0.0758 0.3548 1.0000
10.000 1.4540 0.02972 0.02077 -0.0730 0.3467 1.0000
10.250 1.4672 0.03031 0.02133 -0.0713 0.3398 1.0000
10.500 1.4701 0.03145 0.02264 -0.0686 0.3319 1.0000
10.750 1.4810 0.03222 0.02343 -0.0668 0.3250 1.0000
11.000 1.4849 0.03348 0.02483 -0.0646 0.3180 1.0000
11.250 1.4933 0.03453 0.02596 -0.0628 0.3118 1.0000
11.500 1.5013 0.03567 0.02718 -0.0611 0.3059 1.0000
11.750 1.5048 0.03714 0.02880 -0.0593 0.2995 1.0000
12.000 1.5153 0.03815 0.02983 -0.0579 0.2938 1.0000
12.250 1.5144 0.04006 0.03193 -0.0560 0.2873 1.0000
12.500 1.5180 0.04161 0.03355 -0.0545 0.2806 1.0000
12.750 1.5184 0.04353 0.03559 -0.0530 0.2739 1.0000
13.000 1.5175 0.04563 0.03781 -0.0517 0.2672 1.0000
13.250 1.5218 0.04735 0.03960 -0.0506 0.2615 1.0000
13.500 1.5165 0.05011 0.04255 -0.0495 0.2551 1.0000
13.750 1.5194 0.05200 0.04447 -0.0485 0.2488 1.0000
14.000 1.5095 0.05546 0.04812 -0.0478 0.2417 1.0000
14.250 1.5077 0.05803 0.05076 -0.0472 0.2350 1.0000
14.500 1.4996 0.06160 0.05450 -0.0469 0.2284 1.0000
14.750 1.4938 0.06495 0.05795 -0.0467 0.2215 1.0000
15.000 1.4856 0.06878 0.06192 -0.0468 0.2147 1.0000
15.250 1.4765 0.07284 0.06611 -0.0472 0.2073 1.0000
15.500 1.4656 0.07732 0.07072 -0.0477 0.1999 1.0000
15.750 1.4561 0.08168 0.07516 -0.0484 0.1917 1.0000
16.000 1.4392 0.08739 0.08103 -0.0497 0.1834 1.0000
16.250 1.4285 0.09214 0.08581 -0.0508 0.1740 1.0000
16.500 1.4115 0.09815 0.09194 -0.0525 0.1643 1.0000
16.750 1.3951 0.10422 0.09810 -0.0544 0.1540 1.0000
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