GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 388 AIRFOIL (goe388-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.21 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe388-il-1000000-n5.txt Download as CSV file: xf-goe388-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 388 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3166 0.10782 0.10321 -0.0377 0.0409 0.0116
-10.250 -0.3101 0.10479 0.10018 -0.0393 0.0403 0.0121
-9.750 -0.3182 0.09331 0.08872 -0.0451 0.0408 0.0140
-9.500 -0.3096 0.09089 0.08631 -0.0466 0.0401 0.0142
-9.250 -0.3008 0.08848 0.08391 -0.0481 0.0396 0.0143
-9.000 -0.2919 0.08605 0.08149 -0.0497 0.0394 0.0145
-8.750 -0.2829 0.08361 0.07905 -0.0513 0.0393 0.0147
-8.500 -0.2742 0.08102 0.07646 -0.0532 0.0391 0.0150
-8.250 -0.2670 0.07817 0.07362 -0.0554 0.0387 0.0154
-8.000 -0.2615 0.07469 0.07016 -0.0589 0.0385 0.0158
-7.750 -0.2525 0.06927 0.06474 -0.0658 0.0384 0.0165
-7.500 -0.2449 0.05500 0.05038 -0.0850 0.0391 0.0183
-7.250 -0.2230 0.05170 0.04701 -0.0895 0.0385 0.0186
-7.000 -0.2000 0.04753 0.04277 -0.0946 0.0381 0.0188
-6.750 -0.1760 0.04226 0.03736 -0.1002 0.0377 0.0192
-6.500 -0.1602 0.02248 0.01634 -0.1115 0.0383 0.0218
-6.250 -0.1353 0.02048 0.01403 -0.1120 0.0377 0.0222
-5.750 -0.0830 0.01836 0.01152 -0.1125 0.0371 0.0226
-5.500 -0.0564 0.01758 0.01058 -0.1127 0.0357 0.0227
-5.250 -0.0298 0.01697 0.00985 -0.1128 0.0351 0.0228
-5.000 -0.0028 0.01638 0.00912 -0.1129 0.0350 0.0229
-4.750 0.0243 0.01585 0.00847 -0.1130 0.0344 0.0230
-4.500 0.0513 0.01542 0.00793 -0.1131 0.0338 0.0231
-4.250 0.0784 0.01507 0.00750 -0.1131 0.0334 0.0231
-4.000 0.1048 0.01402 0.00626 -0.1132 0.0331 0.0238
-3.750 0.1311 0.01379 0.00596 -0.1132 0.0329 0.0241
-3.500 0.1581 0.01355 0.00566 -0.1132 0.0329 0.0244
-3.250 0.1852 0.01338 0.00545 -0.1132 0.0329 0.0247
-3.000 0.2123 0.01326 0.00530 -0.1132 0.0329 0.0250
-2.500 0.2668 0.01303 0.00499 -0.1133 0.0321 0.0258
-1.250 0.3960 0.01365 0.00545 -0.1124 0.0308 0.0277
-1.000 0.4223 0.01370 0.00547 -0.1124 0.0307 0.0281
-0.750 0.4484 0.01378 0.00552 -0.1123 0.0307 0.0284
-0.500 0.4744 0.01389 0.00559 -0.1122 0.0307 0.0287
-0.250 0.5002 0.01402 0.00570 -0.1120 0.0307 0.0290
0.000 0.5257 0.01419 0.00584 -0.1119 0.0306 0.0292
0.250 0.5510 0.01439 0.00601 -0.1117 0.0306 0.0296
0.500 0.5761 0.01460 0.00620 -0.1115 0.0305 0.0301
0.750 0.6012 0.01481 0.00637 -0.1112 0.0305 0.0316
1.000 0.6259 0.01507 0.00660 -0.1110 0.0304 0.0334
1.250 0.6506 0.01535 0.00687 -0.1107 0.0303 0.0353
1.500 0.6751 0.01564 0.00715 -0.1104 0.0301 0.0374
1.750 0.6995 0.01597 0.00746 -0.1101 0.0299 0.0420
2.000 0.7236 0.01632 0.00782 -0.1098 0.0298 0.0540
2.250 0.7479 0.01657 0.00822 -0.1096 0.0298 0.1318
2.500 0.7721 0.01694 0.00862 -0.1094 0.0297 0.1614
2.750 0.7965 0.01718 0.00908 -0.1093 0.0296 0.2748
3.000 0.8212 0.01716 0.00962 -0.1096 0.0295 0.5358
3.500 0.8644 0.01716 0.01054 -0.1080 0.0294 1.0000
3.750 0.8889 0.01770 0.01101 -0.1078 0.0294 1.0000
4.000 0.9136 0.01825 0.01151 -0.1077 0.0293 1.0000
4.250 0.9385 0.01882 0.01202 -0.1076 0.0293 1.0000
4.500 0.9635 0.01941 0.01256 -0.1076 0.0292 1.0000
4.750 0.9887 0.02002 0.01311 -0.1076 0.0292 1.0000
5.000 1.0140 0.02065 0.01370 -0.1077 0.0291 1.0000
5.250 1.0394 0.02130 0.01430 -0.1078 0.0291 1.0000
5.500 1.0649 0.02196 0.01492 -0.1079 0.0291 1.0000
5.750 1.0905 0.02265 0.01558 -0.1081 0.0290 1.0000
6.000 1.1160 0.02335 0.01624 -0.1083 0.0290 1.0000
6.250 1.1418 0.02413 0.01698 -0.1085 0.0290 1.0000
6.750 1.1627 0.01730 0.01023 -0.1039 0.0286 1.0000
7.000 1.2217 0.02754 0.02025 -0.1099 0.0286 1.0000
7.250 1.2456 0.02795 0.02067 -0.1098 0.0285 1.0000
7.500 1.2688 0.02817 0.02092 -0.1096 0.0284 1.0000
7.750 1.2911 0.02824 0.02100 -0.1092 0.0271 1.0000
8.000 1.3137 0.02859 0.02136 -0.1090 0.0253 1.0000
8.250 1.3363 0.02910 0.02187 -0.1088 0.0245 1.0000
8.500 1.3595 0.02949 0.02227 -0.1087 0.0234 1.0000
8.750 1.3813 0.02981 0.02258 -0.1084 0.0224 1.0000
9.000 1.4090 0.03100 0.02378 -0.1092 0.0195 1.0000
9.500 1.4509 0.03138 0.02407 -0.1083 0.0122 1.0000
9.750 1.4729 0.03186 0.02450 -0.1081 0.0108 1.0000
10.000 1.4960 0.03255 0.02518 -0.1082 0.0100 1.0000
10.250 1.5189 0.03324 0.02586 -0.1082 0.0092 1.0000
10.500 1.5410 0.03386 0.02645 -0.1080 0.0085 1.0000
10.750 1.5626 0.03442 0.02700 -0.1078 0.0079 1.0000
11.000 1.5851 0.03516 0.02774 -0.1078 0.0075 1.0000
11.250 1.6071 0.03587 0.02845 -0.1077 0.0072 1.0000
11.500 1.6289 0.03657 0.02916 -0.1076 0.0068 1.0000
11.750 1.6503 0.03727 0.02984 -0.1075 0.0065 1.0000
12.000 1.6713 0.03795 0.03051 -0.1073 0.0061 1.0000
12.250 1.6914 0.03857 0.03113 -0.1069 0.0058 1.0000
12.500 1.7131 0.03943 0.03200 -0.1069 0.0056 1.0000
12.750 1.7347 0.04032 0.03291 -0.1069 0.0054 1.0000
13.000 1.7558 0.04121 0.03382 -0.1068 0.0053 1.0000
13.250 1.7767 0.04213 0.03476 -0.1067 0.0051 1.0000
13.500 1.7976 0.04309 0.03574 -0.1067 0.0048 1.0000
13.750 1.8184 0.04411 0.03677 -0.1067 0.0046 1.0000
14.000 1.8388 0.04514 0.03781 -0.1066 0.0044 1.0000
14.250 1.8583 0.04615 0.03885 -0.1064 0.0043 1.0000
14.500 1.8768 0.04710 0.03982 -0.1060 0.0041 1.0000
14.750 1.8937 0.04787 0.04061 -0.1054 0.0039 1.0000
15.000 1.9110 0.04882 0.04159 -0.1049 0.0038 1.0000
15.250 1.9293 0.04998 0.04280 -0.1046 0.0038 1.0000
15.500 1.9472 0.05118 0.04405 -0.1043 0.0037 1.0000
15.750 1.9644 0.05239 0.04532 -0.1039 0.0036 1.0000
16.000 1.9811 0.05363 0.04662 -0.1035 0.0035 1.0000
16.250 1.9971 0.05490 0.04796 -0.1030 0.0034 1.0000
16.500 2.0126 0.05619 0.04932 -0.1024 0.0034 1.0000
16.750 2.0273 0.05753 0.05072 -0.1018 0.0033 1.0000
17.000 2.0413 0.05890 0.05216 -0.1011 0.0032 1.0000
17.250 2.0541 0.06031 0.05365 -0.1003 0.0031 1.0000
17.500 2.0660 0.06178 0.05520 -0.0994 0.0031 1.0000
17.750 2.0769 0.06330 0.05679 -0.0984 0.0030 1.0000
18.000 2.0866 0.06485 0.05843 -0.0973 0.0029 1.0000
18.250 2.0949 0.06646 0.06014 -0.0960 0.0029 1.0000
18.500 2.1011 0.06809 0.06186 -0.0946 0.0028 1.0000
18.750 2.1049 0.06974 0.06361 -0.0928 0.0028 1.0000
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