GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 123 AIRFOIL (goe123-il) Reynolds number: 200,000 Max Cl/Cd: 85.02 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe123-il-200000-n5.txt Download as CSV file: xf-goe123-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 123 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3007 0.10722 0.10375 -0.0298 1.0000 0.0205
-8.500 -0.3017 0.10556 0.10215 -0.0307 1.0000 0.0205
-8.250 -0.3084 0.10437 0.10104 -0.0299 0.9987 0.0206
-8.000 -0.2927 0.09962 0.09629 -0.0330 0.9936 0.0207
-7.750 -0.2778 0.09499 0.09164 -0.0335 0.9906 0.0211
-7.500 -0.2609 0.09136 0.08801 -0.0368 0.9847 0.0216
-7.250 -0.2424 0.08784 0.08448 -0.0410 0.9781 0.0223
-7.000 -0.2226 0.08433 0.08096 -0.0458 0.9712 0.0233
-6.750 -0.1972 0.08083 0.07743 -0.0528 0.9642 0.0255
-6.500 -0.1576 0.07757 0.07408 -0.0669 0.9557 0.0263
-6.250 -0.1311 0.07377 0.07022 -0.0732 0.9483 0.0264
-6.000 -0.1034 0.06982 0.06618 -0.0789 0.9425 0.0265
-5.750 -0.0858 0.06519 0.06153 -0.0815 0.9360 0.0268
-5.500 -0.0758 0.06200 0.05836 -0.0796 0.9318 0.0277
-5.250 -0.0569 0.05954 0.05588 -0.0811 0.9248 0.0295
-5.000 -0.0289 0.05655 0.05281 -0.0853 0.9195 0.0319
-4.750 0.0218 0.05395 0.04995 -0.0953 0.9125 0.0347
-4.500 0.0547 0.05098 0.04680 -0.0993 0.9070 0.0349
-4.250 0.0698 0.04647 0.04230 -0.1003 0.9009 0.0361
-4.000 0.0895 0.04411 0.03991 -0.1007 0.8932 0.0372
-3.750 0.1155 0.04179 0.03749 -0.1023 0.8865 0.0388
-3.500 0.1443 0.03951 0.03507 -0.1044 0.8790 0.0412
-3.250 0.1941 0.03807 0.03317 -0.1090 0.8743 0.0458
-3.000 0.2127 0.03442 0.02957 -0.1099 0.8676 0.0473
-2.750 0.2376 0.03259 0.02767 -0.1106 0.8619 0.0489
-2.500 0.2660 0.03084 0.02579 -0.1117 0.8565 0.0510
-2.250 0.3068 0.03027 0.02475 -0.1131 0.8502 0.0571
-2.000 0.3332 0.02610 0.02047 -0.1143 0.8452 0.0444
-1.750 0.3630 0.02430 0.01846 -0.1150 0.8387 0.0444
-1.500 0.3918 0.02258 0.01655 -0.1154 0.8320 0.0433
-1.250 0.4210 0.02083 0.01457 -0.1157 0.8233 0.0409
-1.000 0.4514 0.01877 0.01213 -0.1157 0.8139 0.0386
-0.750 0.4816 0.01666 0.00958 -0.1157 0.8029 0.0373
-0.500 0.5100 0.01550 0.00816 -0.1155 0.7938 0.0372
-0.250 0.5380 0.01466 0.00709 -0.1153 0.7855 0.0375
0.000 0.5655 0.01406 0.00637 -0.1151 0.7764 0.0384
0.250 0.5929 0.01365 0.00586 -0.1148 0.7681 0.0405
0.500 0.6202 0.01315 0.00527 -0.1146 0.7580 0.0411
0.750 0.6474 0.01271 0.00475 -0.1142 0.7481 0.0411
1.000 0.6745 0.01235 0.00432 -0.1139 0.7378 0.0414
1.250 0.7016 0.01208 0.00402 -0.1136 0.7262 0.0418
1.500 0.7285 0.01187 0.00379 -0.1133 0.7138 0.0424
1.750 0.7554 0.01172 0.00361 -0.1130 0.7001 0.0434
2.000 0.7823 0.01162 0.00348 -0.1126 0.6854 0.0447
2.250 0.8090 0.01157 0.00340 -0.1123 0.6690 0.0466
2.500 0.8353 0.01155 0.00334 -0.1118 0.6487 0.0516
2.750 0.8610 0.01158 0.00335 -0.1113 0.6209 0.0711
3.000 0.8858 0.01171 0.00343 -0.1105 0.5873 0.1268
3.250 0.9103 0.01194 0.00352 -0.1098 0.5535 0.1583
3.500 0.9347 0.01218 0.00365 -0.1092 0.5243 0.1855
4.000 0.9794 0.01152 0.00407 -0.1070 0.4730 1.0000
4.250 1.0037 0.01189 0.00429 -0.1064 0.4483 1.0000
4.500 1.0284 0.01224 0.00454 -0.1059 0.4252 1.0000
4.750 1.0527 0.01261 0.00482 -0.1054 0.4042 1.0000
5.000 1.0769 0.01298 0.00513 -0.1048 0.3845 1.0000
5.250 1.1011 0.01336 0.00545 -0.1043 0.3667 1.0000
5.500 1.1249 0.01377 0.00580 -0.1037 0.3485 1.0000
5.750 1.1483 0.01422 0.00620 -0.1030 0.3296 1.0000
6.000 1.1716 0.01467 0.00660 -0.1024 0.3128 1.0000
6.250 1.1953 0.01507 0.00701 -0.1018 0.2993 1.0000
6.500 1.2185 0.01551 0.00744 -0.1012 0.2835 1.0000
6.750 1.2408 0.01601 0.00792 -0.1004 0.2618 1.0000
7.000 1.2622 0.01658 0.00841 -0.0995 0.2354 1.0000
7.250 1.2826 0.01724 0.00895 -0.0986 0.2015 1.0000
7.500 1.3014 0.01807 0.00960 -0.0975 0.1661 1.0000
7.750 1.3165 0.01930 0.01049 -0.0959 0.1064 1.0000
8.000 1.3298 0.02072 0.01166 -0.0941 0.0704 1.0000
8.250 1.3432 0.02208 0.01280 -0.0922 0.0383 1.0000
8.500 1.3587 0.02316 0.01393 -0.0905 0.0311 1.0000
8.750 1.3723 0.02435 0.01520 -0.0886 0.0265 1.0000
9.000 1.3874 0.02531 0.01632 -0.0868 0.0240 1.0000
9.250 1.3995 0.02641 0.01756 -0.0847 0.0218 1.0000
9.500 1.4066 0.02773 0.01901 -0.0820 0.0200 1.0000
9.750 1.4112 0.02926 0.02065 -0.0791 0.0186 1.0000
10.000 1.4202 0.03049 0.02203 -0.0768 0.0175 1.0000
10.250 1.4261 0.03201 0.02368 -0.0744 0.0166 1.0000
10.500 1.4310 0.03366 0.02547 -0.0721 0.0158 1.0000
10.750 1.4351 0.03545 0.02738 -0.0699 0.0152 1.0000
11.000 1.4387 0.03734 0.02938 -0.0679 0.0146 1.0000
11.250 1.4408 0.03944 0.03158 -0.0660 0.0139 1.0000
11.500 1.4392 0.04200 0.03425 -0.0640 0.0133 1.0000
11.750 1.4395 0.04450 0.03687 -0.0622 0.0128 1.0000
12.000 1.4434 0.04666 0.03921 -0.0609 0.0123 1.0000
12.250 1.4452 0.04913 0.04184 -0.0595 0.0119 1.0000
12.500 1.4461 0.05178 0.04465 -0.0582 0.0115 1.0000
12.750 1.4465 0.05455 0.04758 -0.0570 0.0112 1.0000
13.000 1.4463 0.05747 0.05065 -0.0560 0.0109 1.0000
13.250 1.4452 0.06055 0.05390 -0.0551 0.0107 1.0000
13.500 1.4429 0.06384 0.05736 -0.0545 0.0105 1.0000
13.750 1.4394 0.06734 0.06103 -0.0541 0.0103 1.0000
14.000 1.4348 0.07110 0.06498 -0.0540 0.0101 1.0000
14.250 1.4291 0.07508 0.06915 -0.0542 0.0099 1.0000
14.500 1.4226 0.07931 0.07354 -0.0548 0.0098 1.0000
14.750 1.4154 0.08383 0.07822 -0.0557 0.0096 1.0000
15.000 1.4075 0.08860 0.08314 -0.0569 0.0095 1.0000
15.250 1.3983 0.09373 0.08842 -0.0585 0.0093 1.0000
15.500 1.3873 0.09934 0.09420 -0.0604 0.0092 1.0000
16.000 1.3613 0.11213 0.10737 -0.0659 0.0090 1.0000
16.250 1.3482 0.11904 0.11449 -0.0696 0.0090 1.0000
16.500 1.3347 0.12632 0.12198 -0.0736 0.0090 1.0000
16.750 1.3209 0.13399 0.12984 -0.0782 0.0089 1.0000
17.000 1.3071 0.14201 0.13804 -0.0831 0.0089 1.0000
17.250 1.2931 0.15045 0.14665 -0.0885 0.0089 1.0000
17.500 1.2791 0.15922 0.15557 -0.0941 0.0090 1.0000
17.750 1.2651 0.16844 0.16493 -0.1002 0.0090 1.0000
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