GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 427 AIRFOIL (goe427-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.98 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe427-il-1000000-n5.txt Download as CSV file: xf-goe427-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 427 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3551 0.12408 0.12240 -0.0226 1.0000 0.0035
-10.500 -0.3515 0.12142 0.11976 -0.0227 1.0000 0.0036
-10.250 -0.3480 0.11858 0.11693 -0.0227 1.0000 0.0040
-10.000 -0.3389 0.11537 0.11372 -0.0246 0.9996 0.0039
-9.750 -0.3263 0.11156 0.10992 -0.0276 0.9987 0.0040
-9.500 -0.3137 0.10796 0.10632 -0.0305 0.9976 0.0040
-9.250 -0.3017 0.10424 0.10260 -0.0335 0.9960 0.0041
-9.000 -0.2904 0.10067 0.09903 -0.0362 0.9942 0.0041
-8.750 -0.2787 0.09739 0.09575 -0.0387 0.9922 0.0041
-8.500 -0.2658 0.09408 0.09245 -0.0416 0.9901 0.0041
-8.250 -0.2516 0.09011 0.08849 -0.0454 0.9878 0.0041
-8.000 -0.2400 0.08685 0.08523 -0.0480 0.9843 0.0040
-7.750 -0.2257 0.08323 0.08162 -0.0518 0.9802 0.0041
-7.500 -0.2102 0.07996 0.07834 -0.0556 0.9778 0.0037
-7.250 -0.1938 0.07725 0.07563 -0.0590 0.9724 0.0054
-6.750 -0.1384 0.06895 0.06730 -0.0734 0.9661 0.0065
-6.250 -0.0841 0.05913 0.05741 -0.0877 0.9543 0.0039
-5.750 -0.0313 0.05146 0.04965 -0.0985 0.9375 0.0037
-4.750 0.0938 0.01118 0.00720 -0.1261 0.8843 0.0041
-4.500 0.1191 0.00962 0.00522 -0.1258 0.8727 0.0044
-4.250 0.1453 0.00912 0.00456 -0.1255 0.8591 0.0050
-4.000 0.1713 0.00874 0.00401 -0.1251 0.8441 0.0055
-3.750 0.1972 0.00828 0.00335 -0.1246 0.8290 0.0061
-3.500 0.2233 0.00793 0.00283 -0.1242 0.8157 0.0066
-3.000 0.2756 0.00733 0.00198 -0.1233 0.7915 0.0094
-2.750 0.3016 0.00717 0.00171 -0.1228 0.7776 0.0121
-2.500 0.3276 0.00716 0.00167 -0.1224 0.7613 0.0170
-2.250 0.3535 0.00720 0.00160 -0.1219 0.7435 0.0190
-2.000 0.3795 0.00713 0.00146 -0.1214 0.7278 0.0220
-1.750 0.4059 0.00713 0.00140 -0.1211 0.7153 0.0249
-1.500 0.4323 0.00716 0.00138 -0.1208 0.7026 0.0284
-1.250 0.4588 0.00721 0.00137 -0.1204 0.6890 0.0303
-1.000 0.4851 0.00723 0.00132 -0.1201 0.6745 0.0309
-0.750 0.5111 0.00726 0.00128 -0.1197 0.6557 0.0313
-0.500 0.5359 0.00726 0.00113 -0.1190 0.6230 0.0320
-0.250 0.5571 0.00759 0.00108 -0.1177 0.5476 0.0326
0.000 0.5813 0.00775 0.00106 -0.1170 0.5120 0.0332
0.250 0.6068 0.00783 0.00103 -0.1166 0.4911 0.0339
0.500 0.6324 0.00792 0.00102 -0.1162 0.4694 0.0353
0.750 0.6580 0.00802 0.00102 -0.1157 0.4457 0.0359
1.000 0.6837 0.00812 0.00103 -0.1154 0.4247 0.0369
1.250 0.7090 0.00827 0.00107 -0.1149 0.3970 0.0398
1.500 0.7339 0.00844 0.00115 -0.1144 0.3671 0.0532
1.750 0.7577 0.00865 0.00130 -0.1138 0.3293 0.1068
2.250 0.8048 0.00926 0.00169 -0.1124 0.2423 0.1767
2.500 0.8239 0.01005 0.00212 -0.1111 0.1369 0.2371
2.750 0.8460 0.01046 0.00245 -0.1103 0.0783 0.3279
3.000 0.8692 0.01071 0.00274 -0.1096 0.0402 0.4263
3.500 0.9235 0.01009 0.00322 -0.1099 0.0291 1.0000
3.750 0.9486 0.01030 0.00343 -0.1094 0.0278 1.0000
4.000 0.9736 0.01052 0.00368 -0.1089 0.0271 1.0000
4.250 0.9985 0.01074 0.00393 -0.1084 0.0268 1.0000
4.500 1.0231 0.01099 0.00420 -0.1079 0.0264 1.0000
4.750 1.0472 0.01130 0.00455 -0.1073 0.0248 1.0000
5.250 1.0968 0.01170 0.00498 -0.1064 0.0236 1.0000
5.500 1.1218 0.01186 0.00515 -0.1060 0.0226 1.0000
5.750 1.1464 0.01207 0.00539 -0.1055 0.0203 1.0000
6.000 1.1698 0.01240 0.00567 -0.1049 0.0117 1.0000
6.250 1.1925 0.01280 0.00604 -0.1041 0.0075 1.0000
6.500 1.2147 0.01324 0.00651 -0.1032 0.0058 1.0000
6.750 1.2368 0.01369 0.00701 -0.1023 0.0048 1.0000
7.000 1.2587 0.01414 0.00750 -0.1014 0.0042 1.0000
7.250 1.2797 0.01466 0.00806 -0.1003 0.0036 1.0000
7.500 1.2999 0.01525 0.00873 -0.0991 0.0031 1.0000
7.750 1.3205 0.01577 0.00934 -0.0980 0.0028 1.0000
8.000 1.3402 0.01636 0.01000 -0.0967 0.0026 1.0000
8.250 1.3593 0.01696 0.01067 -0.0954 0.0024 1.0000
8.500 1.3775 0.01763 0.01140 -0.0939 0.0022 1.0000
8.750 1.3927 0.01855 0.01241 -0.0920 0.0020 1.0000
9.000 1.4061 0.01960 0.01359 -0.0897 0.0019 1.0000
9.250 1.4224 0.02032 0.01441 -0.0880 0.0018 1.0000
9.500 1.4352 0.02127 0.01547 -0.0857 0.0017 1.0000
9.750 1.4447 0.02231 0.01664 -0.0828 0.0016 1.0000
10.000 1.4537 0.02336 0.01782 -0.0798 0.0015 1.0000
10.250 1.4615 0.02453 0.01913 -0.0769 0.0015 1.0000
10.500 1.4685 0.02579 0.02053 -0.0740 0.0014 1.0000
10.750 1.4763 0.02700 0.02190 -0.0713 0.0013 1.0000
11.000 1.4841 0.02819 0.02321 -0.0689 0.0013 1.0000
11.250 1.4922 0.02936 0.02449 -0.0666 0.0012 1.0000
11.500 1.4988 0.03069 0.02594 -0.0643 0.0011 1.0000
11.750 1.5049 0.03207 0.02743 -0.0622 0.0011 1.0000
12.000 1.5053 0.03411 0.02964 -0.0596 0.0011 1.0000
12.250 1.5062 0.03613 0.03181 -0.0574 0.0010 1.0000
12.500 1.5009 0.03893 0.03481 -0.0550 0.0010 1.0000
12.750 1.4955 0.04185 0.03793 -0.0530 0.0010 1.0000
13.000 1.4838 0.04571 0.04203 -0.0512 0.0009 1.0000
13.250 1.4681 0.05034 0.04691 -0.0500 0.0009 1.0000
13.500 1.4543 0.05495 0.05175 -0.0496 0.0009 1.0000
13.750 1.4392 0.06012 0.05714 -0.0499 0.0009 1.0000
14.000 1.4295 0.06475 0.06193 -0.0508 0.0009 1.0000
14.250 1.4109 0.07124 0.06863 -0.0527 0.0009 1.0000
14.500 1.3921 0.07838 0.07596 -0.0555 0.0009 1.0000
14.750 1.3753 0.08556 0.08330 -0.0589 0.0009 1.0000
15.000 1.3483 0.09542 0.09336 -0.0639 0.0009 1.0000
15.250 1.3327 0.10342 0.10149 -0.0682 0.0009 1.0000
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Polar data table (+)
Polar graphs
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