GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 177 AIRFOIL (goe177-il) Reynolds number: 200,000 Max Cl/Cd: 71.51 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe177-il-200000-n5.txt Download as CSV file: xf-goe177-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 177 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3035 0.09626 0.09312 -0.0247 1.0000 0.0206
-7.250 -0.3013 0.09352 0.09044 -0.0253 1.0000 0.0207
-7.000 -0.2979 0.09066 0.08763 -0.0263 1.0000 0.0207
-6.750 -0.2945 0.08779 0.08482 -0.0272 1.0000 0.0207
-6.500 -0.2911 0.08493 0.08201 -0.0279 1.0000 0.0207
-6.250 -0.1815 0.05856 0.05579 -0.0389 0.9709 0.0167
-6.000 -0.1660 0.05324 0.05046 -0.0444 0.9591 0.0149
-5.750 -0.2240 0.06931 0.06636 -0.0427 0.9807 0.0159
-5.500 -0.1889 0.06236 0.05935 -0.0534 0.9703 0.0131
-5.250 -0.1471 0.05463 0.05151 -0.0646 0.9589 0.0113
-5.000 -0.1124 0.04910 0.04584 -0.0722 0.9464 0.0118
-4.750 -0.0804 0.04600 0.04263 -0.0768 0.9306 0.0134
-4.500 -0.0417 0.04024 0.03665 -0.0835 0.9122 0.0136
-4.250 0.0014 0.03129 0.02725 -0.0910 0.8919 0.0128
-4.000 0.0429 0.02114 0.01598 -0.0964 0.8724 0.0124
-3.750 0.0755 0.01789 0.01197 -0.0975 0.8457 0.0129
-3.500 0.1052 0.01605 0.00957 -0.0976 0.8182 0.0139
-3.250 0.1332 0.01507 0.00819 -0.0973 0.7917 0.0163
-3.000 0.1609 0.01410 0.00681 -0.0969 0.7677 0.0186
-2.750 0.1886 0.01335 0.00570 -0.0964 0.7457 0.0205
-2.500 0.2159 0.01266 0.00481 -0.0961 0.7255 0.0275
-2.250 0.2435 0.01217 0.00420 -0.0958 0.7064 0.0418
-2.000 0.2708 0.01228 0.00418 -0.0954 0.6879 0.0679
-1.750 0.2980 0.01238 0.00411 -0.0952 0.6702 0.0847
-1.500 0.3252 0.01233 0.00387 -0.0949 0.6535 0.0940
-1.250 0.3524 0.01214 0.00357 -0.0947 0.6373 0.0998
-1.000 0.3796 0.01209 0.00338 -0.0945 0.6211 0.1077
-0.750 0.4069 0.01198 0.00318 -0.0943 0.6054 0.1129
-0.500 0.4341 0.01192 0.00300 -0.0942 0.5904 0.1174
-0.250 0.4615 0.01190 0.00287 -0.0940 0.5763 0.1231
0.000 0.4887 0.01185 0.00278 -0.0938 0.5621 0.1334
0.250 0.5159 0.01182 0.00271 -0.0937 0.5475 0.1521
0.500 0.5429 0.01172 0.00271 -0.0936 0.5327 0.2064
0.750 0.5697 0.01160 0.00276 -0.0935 0.5177 0.3035
1.000 0.5961 0.01150 0.00278 -0.0934 0.5001 0.3953
1.250 0.6171 0.01038 0.00275 -0.0915 0.4812 1.0000
1.500 0.6437 0.01058 0.00276 -0.0913 0.4602 1.0000
1.750 0.6702 0.01079 0.00281 -0.0911 0.4403 1.0000
2.250 0.7232 0.01124 0.00295 -0.0906 0.4035 1.0000
2.500 0.7495 0.01147 0.00306 -0.0904 0.3851 1.0000
2.750 0.7758 0.01172 0.00318 -0.0902 0.3690 1.0000
3.000 0.8024 0.01193 0.00333 -0.0900 0.3574 1.0000
3.250 0.8289 0.01216 0.00351 -0.0898 0.3468 1.0000
3.500 0.8552 0.01240 0.00369 -0.0896 0.3364 1.0000
3.750 0.8818 0.01261 0.00389 -0.0895 0.3268 1.0000
4.000 0.9081 0.01285 0.00411 -0.0893 0.3182 1.0000
4.250 0.9345 0.01307 0.00436 -0.0891 0.3101 1.0000
4.500 0.9597 0.01342 0.00461 -0.0888 0.2867 1.0000
4.750 0.9839 0.01391 0.00490 -0.0885 0.2495 1.0000
5.000 0.9992 0.01573 0.00586 -0.0873 0.1131 1.0000
5.250 1.0202 0.01675 0.00664 -0.0865 0.0584 1.0000
5.500 1.0444 0.01725 0.00715 -0.0861 0.0489 1.0000
5.750 1.0689 0.01769 0.00765 -0.0856 0.0363 1.0000
6.000 1.0912 0.01844 0.00835 -0.0849 0.0168 1.0000
6.250 1.1149 0.01897 0.00909 -0.0842 0.0135 1.0000
6.500 1.1381 0.01956 0.00986 -0.0834 0.0124 1.0000
6.750 1.1601 0.02026 0.01075 -0.0826 0.0115 1.0000
7.000 1.1805 0.02113 0.01181 -0.0815 0.0100 1.0000
7.250 1.1993 0.02214 0.01301 -0.0803 0.0093 1.0000
7.500 1.2157 0.02335 0.01441 -0.0787 0.0088 1.0000
7.750 1.2284 0.02482 0.01607 -0.0768 0.0085 1.0000
8.000 1.2366 0.02659 0.01797 -0.0745 0.0082 1.0000
8.250 1.2406 0.02857 0.02011 -0.0716 0.0081 1.0000
8.750 1.2528 0.03168 0.02343 -0.0663 0.0074 1.0000
9.000 1.2626 0.03291 0.02480 -0.0643 0.0068 1.0000
9.250 1.2675 0.03465 0.02666 -0.0620 0.0065 1.0000
9.500 1.2717 0.03664 0.02874 -0.0598 0.0064 1.0000
9.750 1.2768 0.03870 0.03091 -0.0579 0.0063 1.0000
10.000 1.2831 0.04083 0.03315 -0.0561 0.0062 1.0000
10.250 1.2906 0.04301 0.03544 -0.0545 0.0061 1.0000
10.500 1.2989 0.04527 0.03783 -0.0529 0.0061 1.0000
10.750 1.3072 0.04765 0.04037 -0.0513 0.0061 1.0000
11.000 1.3143 0.05022 0.04312 -0.0499 0.0061 1.0000
11.250 1.3192 0.05304 0.04615 -0.0486 0.0062 1.0000
11.500 1.3215 0.05615 0.04949 -0.0474 0.0063 1.0000
11.750 1.3212 0.05953 0.05309 -0.0465 0.0064 1.0000
12.000 1.3183 0.06321 0.05701 -0.0459 0.0065 1.0000
12.250 1.3130 0.06721 0.06124 -0.0457 0.0066 1.0000
12.500 1.3055 0.07152 0.06578 -0.0458 0.0067 1.0000
12.750 1.2963 0.07615 0.07063 -0.0464 0.0068 1.0000
13.000 1.2855 0.08109 0.07578 -0.0474 0.0069 1.0000
13.250 1.2736 0.08632 0.08121 -0.0489 0.0070 1.0000
13.500 1.2610 0.09180 0.08688 -0.0507 0.0071 1.0000
13.750 1.2474 0.09760 0.09286 -0.0529 0.0072 1.0000
14.000 1.2337 0.10364 0.09907 -0.0554 0.0073 1.0000
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Polar data table (+)
Polar graphs
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