GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 178 AIRFOIL (goe178-il) Reynolds number: 50,000 Max Cl/Cd: 37.82 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe178-il-50000.txt Download as CSV file: xf-goe178-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 178 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3674 0.10221 0.09582 -0.0166 1.0000 0.1764
-7.250 -0.3509 0.09698 0.09057 -0.0150 1.0000 0.1826
-7.000 -0.3543 0.09561 0.08931 -0.0180 1.0000 0.1908
-6.750 -0.3422 0.09129 0.08503 -0.0162 1.0000 0.1991
-6.500 -0.3476 0.09030 0.08418 -0.0225 1.0000 0.2072
-6.250 -0.3344 0.08600 0.07991 -0.0187 1.0000 0.2184
-6.000 -0.3288 0.08281 0.07680 -0.0188 1.0000 0.2265
-5.750 -0.3275 0.08063 0.07471 -0.0215 1.0000 0.2378
-5.500 -0.3233 0.07847 0.07262 -0.0235 1.0000 0.2515
-5.000 -0.3117 0.07296 0.06725 -0.0222 1.0000 0.2814
-4.750 -0.3068 0.06985 0.06421 -0.0189 1.0000 0.2980
-4.500 -0.3026 0.06725 0.06170 -0.0151 1.0000 0.3187
-4.250 -0.3005 0.06504 0.05958 -0.0135 1.0000 0.3448
-4.000 -0.2989 0.06296 0.05760 -0.0112 1.0000 0.3734
-3.750 -0.2984 0.06086 0.05560 -0.0078 1.0000 0.4031
-3.500 -0.2996 0.05876 0.05362 -0.0031 1.0000 0.4344
-3.250 -0.3027 0.05689 0.05188 0.0023 1.0000 0.4702
-3.000 -0.3107 0.05551 0.05063 0.0081 1.0000 0.5195
-2.750 -0.3190 0.05354 0.04882 0.0157 1.0000 0.5559
-2.500 -0.3282 0.05215 0.04755 0.0213 1.0000 0.5971
-2.250 -0.0466 0.03866 0.03118 -0.0650 0.9874 0.1967
-2.000 0.0336 0.03455 0.02610 -0.0761 0.9722 0.1703
-1.750 0.1043 0.03183 0.02263 -0.0846 0.9551 0.1675
-1.500 0.1655 0.03009 0.02029 -0.0910 0.9344 0.1764
-1.250 0.2250 0.02823 0.01817 -0.0967 0.9164 0.1875
-1.000 0.2816 0.02656 0.01625 -0.1011 0.8998 0.2183
-0.750 0.3293 0.02495 0.01487 -0.1041 0.8828 0.2985
-0.500 0.3671 0.02357 0.01419 -0.1055 0.8647 0.4282
-0.250 0.4007 0.02169 0.01317 -0.1043 0.8486 1.0000
0.000 0.4355 0.02195 0.01296 -0.1051 0.8321 1.0000
0.250 0.4676 0.02229 0.01296 -0.1054 0.8166 1.0000
0.500 0.4974 0.02271 0.01312 -0.1055 0.8021 1.0000
0.750 0.5259 0.02321 0.01340 -0.1055 0.7886 1.0000
1.000 0.5539 0.02373 0.01374 -0.1054 0.7760 1.0000
1.250 0.5825 0.02418 0.01403 -0.1052 0.7646 1.0000
1.500 0.6086 0.02483 0.01455 -0.1050 0.7527 1.0000
1.750 0.6332 0.02560 0.01523 -0.1048 0.7405 1.0000
2.000 0.6581 0.02635 0.01591 -0.1045 0.7290 1.0000
2.250 0.6845 0.02693 0.01642 -0.1040 0.7182 1.0000
2.500 0.7113 0.02741 0.01682 -0.1033 0.7073 1.0000
2.750 0.7344 0.02825 0.01764 -0.1028 0.6948 1.0000
3.000 0.7577 0.02910 0.01848 -0.1023 0.6828 1.0000
3.250 0.7820 0.02985 0.01925 -0.1016 0.6717 1.0000
3.500 0.8101 0.03019 0.01954 -0.1007 0.6621 1.0000
3.750 0.8313 0.03136 0.02077 -0.1003 0.6500 1.0000
4.000 0.8525 0.03259 0.02208 -0.1000 0.6385 1.0000
4.250 0.8757 0.03360 0.02316 -0.0994 0.6280 1.0000
4.500 0.9027 0.03415 0.02374 -0.0985 0.6184 1.0000
4.750 0.9208 0.03582 0.02554 -0.0982 0.6063 1.0000
5.000 0.9395 0.03746 0.02730 -0.0977 0.5947 1.0000
5.250 0.9611 0.03877 0.02875 -0.0971 0.5844 1.0000
5.500 0.9844 0.03997 0.03005 -0.0965 0.5748 1.0000
5.750 0.9955 0.04266 0.03293 -0.0963 0.5631 1.0000
6.000 1.0094 0.04506 0.03547 -0.0960 0.5528 1.0000
6.250 1.0353 0.04604 0.03661 -0.0952 0.5447 1.0000
6.500 1.0276 0.05123 0.04198 -0.0959 0.5343 1.0000
6.750 1.0578 0.05194 0.04285 -0.0950 0.5285 1.0000
7.000 1.0210 0.06047 0.05146 -0.0969 0.5189 1.0000
7.250 1.0490 0.06156 0.05273 -0.0960 0.5132 1.0000
7.500 0.9927 0.07202 0.06309 -0.0988 0.5114 1.0000
7.750 0.9757 0.07801 0.06910 -0.1000 0.5117 1.0000
8.000 0.9705 0.08295 0.07411 -0.1010 0.5127 1.0000
8.750 1.2864 0.03401 0.02628 -0.0684 0.3273 1.0000
9.000 1.2782 0.03409 0.02562 -0.0627 0.2091 1.0000
9.250 1.2656 0.03756 0.02837 -0.0592 0.1454 1.0000
9.500 1.2534 0.04091 0.03138 -0.0561 0.1279 1.0000
9.750 1.2416 0.04432 0.03465 -0.0537 0.1185 1.0000
10.000 1.2343 0.04767 0.03800 -0.0520 0.1104 1.0000
10.250 1.2272 0.05116 0.04137 -0.0506 0.1046 1.0000
10.500 1.2293 0.05394 0.04430 -0.0490 0.0987 1.0000
10.750 1.2440 0.05564 0.04576 -0.0456 0.0928 1.0000
11.000 1.2778 0.05677 0.04714 -0.0426 0.0877 1.0000
11.250 1.3428 0.05945 0.04968 -0.0420 0.0799 1.0000
11.500 1.3586 0.06284 0.05349 -0.0407 0.0787 1.0000
11.750 1.3687 0.06665 0.05773 -0.0394 0.0785 1.0000
12.000 1.3704 0.07064 0.06208 -0.0379 0.0786 1.0000
12.250 1.3662 0.07483 0.06661 -0.0365 0.0789 1.0000
12.500 1.3578 0.07928 0.07135 -0.0355 0.0794 1.0000
12.750 1.3470 0.08407 0.07640 -0.0350 0.0798 1.0000
13.000 1.3362 0.08926 0.08182 -0.0351 0.0804 1.0000
13.250 1.3183 0.09450 0.08733 -0.0359 0.0809 1.0000
13.500 1.2792 0.10060 0.09375 -0.0394 0.0817 1.0000
13.750 1.2196 0.11108 0.10451 -0.0481 0.0831 1.0000
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Polar data table (+)
Polar graphs
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