GOE 692 AIRFOIL (goe692-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 692 AIRFOIL (goe692-il) Reynolds number: 100,000 Max Cl/Cd: 49.64 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe692-il-100000-n5.txt Download as CSV file: xf-goe692-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 692 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2423 0.09443 0.08886 -0.0853 0.9608 0.0597
-10.000 -0.2446 0.08723 0.08164 -0.0915 0.9569 0.0599
-9.500 -0.4207 0.04858 0.04225 -0.1179 0.9210 0.0598
-9.250 -0.4369 0.04195 0.03481 -0.1190 0.9124 0.0609
-9.000 -0.4253 0.04001 0.03266 -0.1183 0.9054 0.0620
-8.750 -0.4044 0.03893 0.03152 -0.1183 0.8996 0.0632
-8.500 -0.3808 0.03712 0.02948 -0.1193 0.8956 0.0649
-8.250 -0.3665 0.03520 0.02722 -0.1185 0.8887 0.0667
-8.000 -0.3499 0.03302 0.02455 -0.1179 0.8824 0.0686
-7.750 -0.3220 0.03174 0.02317 -0.1187 0.8787 0.0703
-7.500 -0.2959 0.03085 0.02220 -0.1189 0.8743 0.0723
-7.250 -0.2776 0.02997 0.02113 -0.1177 0.8667 0.0749
-7.000 -0.2501 0.02869 0.01954 -0.1182 0.8624 0.0783
-6.750 -0.2184 0.02790 0.01876 -0.1193 0.8592 0.0812
-6.500 -0.2006 0.02733 0.01806 -0.1177 0.8512 0.0842
-6.250 -0.1738 0.02645 0.01697 -0.1178 0.8462 0.0882
-6.000 -0.1428 0.02586 0.01640 -0.1186 0.8426 0.0923
-5.750 -0.1187 0.02533 0.01570 -0.1180 0.8365 0.0971
-5.500 -0.0946 0.02491 0.01528 -0.1175 0.8299 0.1014
-5.250 -0.0643 0.02442 0.01470 -0.1180 0.8258 0.1072
-5.000 -0.0316 0.02387 0.01408 -0.1190 0.8227 0.1132
-4.750 -0.0138 0.02378 0.01397 -0.1173 0.8140 0.1183
-4.500 0.0152 0.02334 0.01343 -0.1175 0.8091 0.1249
-4.250 0.0473 0.02293 0.01300 -0.1183 0.8055 0.1318
-4.000 0.0683 0.02275 0.01274 -0.1171 0.7980 0.1382
-3.750 0.0949 0.02247 0.01248 -0.1169 0.7923 0.1450
-3.500 0.1264 0.02205 0.01197 -0.1174 0.7884 0.1538
-3.250 0.1501 0.02187 0.01182 -0.1168 0.7820 0.1613
-3.000 0.1748 0.02167 0.01158 -0.1162 0.7756 0.1707
-2.750 0.2049 0.02134 0.01125 -0.1165 0.7713 0.1813
-2.500 0.2317 0.02111 0.01102 -0.1163 0.7659 0.1918
-2.250 0.2541 0.02106 0.01095 -0.1154 0.7588 0.2033
-2.000 0.2835 0.02076 0.01068 -0.1156 0.7542 0.2159
-1.750 0.3124 0.02052 0.01045 -0.1157 0.7495 0.2293
-1.500 0.3331 0.02055 0.01050 -0.1144 0.7419 0.2428
-1.250 0.3620 0.02030 0.01028 -0.1146 0.7371 0.2597
-0.750 0.4113 0.02005 0.01023 -0.1135 0.7250 0.3050
-0.500 0.4396 0.01975 0.01008 -0.1136 0.7202 0.3444
-0.250 0.4702 0.01929 0.00988 -0.1140 0.7163 0.4153
0.000 0.4863 0.01912 0.01019 -0.1120 0.7086 0.5281
0.250 0.5074 0.01854 0.01030 -0.1097 0.7037 0.7296
0.500 0.5578 0.01822 0.01021 -0.1128 0.7002 0.9183
0.750 0.6044 0.01845 0.01039 -0.1169 0.6933 0.9897
1.000 0.6353 0.01852 0.01034 -0.1176 0.6876 1.0000
1.250 0.6648 0.01847 0.01013 -0.1178 0.6834 1.0000
1.500 0.6800 0.01879 0.01041 -0.1156 0.6760 1.0000
1.750 0.7044 0.01889 0.01041 -0.1149 0.6703 1.0000
2.000 0.7356 0.01885 0.01023 -0.1154 0.6660 1.0000
2.250 0.7506 0.01923 0.01060 -0.1132 0.6583 1.0000
2.500 0.7765 0.01933 0.01062 -0.1128 0.6526 1.0000
2.750 0.8084 0.01931 0.01048 -0.1134 0.6481 1.0000
3.000 0.8226 0.01974 0.01093 -0.1111 0.6400 1.0000
3.250 0.8502 0.01983 0.01094 -0.1110 0.6342 1.0000
3.500 0.8766 0.01997 0.01102 -0.1107 0.6284 1.0000
3.750 0.8949 0.02031 0.01136 -0.1091 0.6206 1.0000
4.000 0.9254 0.02032 0.01130 -0.1094 0.6147 1.0000
4.250 0.9425 0.02067 0.01166 -0.1076 0.6062 1.0000
4.500 0.9689 0.02074 0.01167 -0.1072 0.5983 1.0000
4.750 0.9880 0.02101 0.01194 -0.1057 0.5894 1.0000
5.000 1.0117 0.02115 0.01204 -0.1049 0.5810 1.0000
5.250 1.0314 0.02143 0.01232 -0.1035 0.5727 1.0000
5.500 1.0522 0.02168 0.01258 -0.1023 0.5645 1.0000
5.750 1.0740 0.02192 0.01281 -0.1012 0.5568 1.0000
6.000 1.0910 0.02227 0.01319 -0.0994 0.5480 1.0000
6.250 1.1130 0.02250 0.01340 -0.0984 0.5401 1.0000
6.500 1.1273 0.02287 0.01380 -0.0962 0.5302 1.0000
6.750 1.1422 0.02319 0.01413 -0.0939 0.5204 1.0000
7.000 1.1605 0.02338 0.01428 -0.0922 0.5098 1.0000
7.250 1.1684 0.02392 0.01486 -0.0890 0.4973 1.0000
7.500 1.1811 0.02435 0.01528 -0.0866 0.4848 1.0000
7.750 1.1962 0.02473 0.01562 -0.0846 0.4727 1.0000
8.000 1.2094 0.02524 0.01612 -0.0825 0.4605 1.0000
8.250 1.2208 0.02592 0.01683 -0.0803 0.4490 1.0000
8.500 1.2357 0.02649 0.01738 -0.0785 0.4383 1.0000
8.750 1.2488 0.02716 0.01804 -0.0766 0.4271 1.0000
9.000 1.2597 0.02798 0.01890 -0.0746 0.4157 1.0000
9.250 1.2724 0.02873 0.01964 -0.0728 0.4045 1.0000
9.500 1.2834 0.02959 0.02050 -0.0709 0.3926 1.0000
9.750 1.2917 0.03066 0.02159 -0.0688 0.3802 1.0000
10.000 1.3008 0.03170 0.02264 -0.0669 0.3679 1.0000
10.250 1.3097 0.03279 0.02371 -0.0649 0.3556 1.0000
10.500 1.3166 0.03405 0.02498 -0.0630 0.3429 1.0000
10.750 1.3230 0.03541 0.02636 -0.0611 0.3304 1.0000
11.000 1.3297 0.03677 0.02773 -0.0593 0.3186 1.0000
11.250 1.3366 0.03815 0.02907 -0.0576 0.3074 1.0000
11.500 1.3421 0.03971 0.03067 -0.0560 0.2961 1.0000
11.750 1.3482 0.04125 0.03222 -0.0544 0.2859 1.0000
12.000 1.3544 0.04279 0.03372 -0.0529 0.2764 1.0000
12.250 1.3599 0.04449 0.03548 -0.0515 0.2669 1.0000
12.500 1.3665 0.04606 0.03701 -0.0501 0.2587 1.0000
12.750 1.3722 0.04784 0.03888 -0.0489 0.2503 1.0000
13.000 1.3793 0.04944 0.04042 -0.0477 0.2432 1.0000
13.250 1.3850 0.05131 0.04239 -0.0466 0.2357 1.0000
13.500 1.3915 0.05304 0.04412 -0.0455 0.2291 1.0000
13.750 1.3986 0.05478 0.04591 -0.0446 0.2229 1.0000
14.000 1.4047 0.05668 0.04789 -0.0437 0.2168 1.0000
14.250 1.4139 0.05819 0.04937 -0.0428 0.2119 1.0000
14.500 1.4221 0.05993 0.05120 -0.0420 0.2072 1.0000
14.750 1.4291 0.06182 0.05321 -0.0413 0.2025 1.0000
15.000 1.4381 0.06345 0.05488 -0.0405 0.1985 1.0000
15.250 1.4511 0.06461 0.05600 -0.0398 0.1948 1.0000
15.500 1.4541 0.06703 0.05862 -0.0392 0.1907 1.0000
15.750 1.4583 0.06928 0.06098 -0.0387 0.1865 1.0000
16.000 1.4646 0.07122 0.06297 -0.0382 0.1825 1.0000
16.250 1.4692 0.07339 0.06519 -0.0377 0.1784 1.0000
16.500 1.4660 0.07662 0.06861 -0.0375 0.1739 1.0000
16.750 1.4665 0.07934 0.07142 -0.0374 0.1696 1.0000
17.000 1.4729 0.08123 0.07327 -0.0371 0.1656 1.0000
17.250 1.4647 0.08530 0.07760 -0.0373 0.1616 1.0000
17.500 1.4602 0.08885 0.08129 -0.0376 0.1572 1.0000
17.750 1.4619 0.09146 0.08389 -0.0378 0.1529 1.0000
18.000 1.4533 0.09574 0.08835 -0.0385 0.1488 1.0000
18.250 1.4440 0.10021 0.09299 -0.0395 0.1445 1.0000
18.500 1.4421 0.10349 0.09629 -0.0402 0.1400 1.0000
18.750 1.4343 0.10787 0.10080 -0.0413 0.1360 1.0000
19.000 1.4221 0.11308 0.10622 -0.0430 0.1320 1.0000
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