GOE 624 AIRFOIL (goe624-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 624 AIRFOIL (goe624-il) Reynolds number: 100,000 Max Cl/Cd: 39.85 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe624-il-100000.txt Download as CSV file: xf-goe624-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 624 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3002 0.12481 0.12031 -0.0303 1.0000 0.1181
-9.750 -0.2876 0.12109 0.11658 -0.0351 0.9957 0.1226
-9.500 -0.3231 0.11839 0.11396 -0.0506 0.9851 0.1263
-9.250 -0.2683 0.11188 0.10737 -0.0474 0.9846 0.1283
-9.000 -0.2361 0.10782 0.10327 -0.0503 0.9813 0.1316
-8.750 -0.2211 0.10415 0.09960 -0.0548 0.9739 0.1368
-8.500 -0.2642 0.10034 0.09587 -0.0700 0.9579 0.1415
-8.250 -0.1943 0.09559 0.09104 -0.0653 0.9605 0.1453
-8.000 -0.1684 0.09176 0.08718 -0.0703 0.9556 0.1521
-7.750 -0.1967 0.08661 0.08206 -0.0832 0.9394 0.1582
-7.500 -0.1422 0.08304 0.07845 -0.0814 0.9392 0.1619
-7.250 -0.1295 0.08019 0.07559 -0.0832 0.9279 0.1672
-7.000 -0.1528 0.07522 0.07056 -0.0929 0.9116 0.1756
-6.750 -0.1154 0.07225 0.06760 -0.0922 0.9074 0.1792
-6.500 -0.1846 0.05250 0.04638 -0.1068 0.8888 0.1124
-6.250 -0.1627 0.04989 0.04392 -0.1069 0.8809 0.1140
-6.000 -0.1447 0.04597 0.03964 -0.1074 0.8728 0.1098
-5.750 -0.1178 0.04163 0.03486 -0.1092 0.8684 0.1074
-5.500 -0.1095 0.03926 0.03212 -0.1071 0.8568 0.1064
-5.250 -0.0795 0.03623 0.02858 -0.1080 0.8519 0.1070
-5.000 -0.0621 0.03475 0.02670 -0.1066 0.8423 0.1095
-4.750 -0.0332 0.03280 0.02425 -0.1067 0.8359 0.1132
-4.500 0.0019 0.03119 0.02260 -0.1077 0.8318 0.1179
-4.250 0.0189 0.03054 0.02176 -0.1059 0.8205 0.1224
-4.000 0.0519 0.02912 0.02017 -0.1063 0.8155 0.1308
-3.750 0.0742 0.02867 0.01953 -0.1052 0.8062 0.1403
-3.500 0.1036 0.02766 0.01855 -0.1051 0.7994 0.1523
-3.250 0.1378 0.02664 0.01749 -0.1055 0.7951 0.1677
-3.000 0.1565 0.02646 0.01733 -0.1041 0.7835 0.1802
-2.750 0.1890 0.02569 0.01654 -0.1042 0.7783 0.1976
-2.500 0.2103 0.02558 0.01643 -0.1032 0.7679 0.2127
-2.250 0.2412 0.02488 0.01572 -0.1030 0.7617 0.2302
-2.000 0.2659 0.02453 0.01543 -0.1022 0.7529 0.2479
-1.750 0.2936 0.02387 0.01492 -0.1017 0.7452 0.2717
-1.500 0.3232 0.02304 0.01429 -0.1013 0.7394 0.3138
-1.250 0.3431 0.02249 0.01427 -0.1000 0.7289 0.4004
-1.000 0.3622 0.02078 0.01401 -0.0963 0.7241 0.7420
-0.750 0.4631 0.02051 0.01381 -0.1082 0.7142 1.0000
-0.500 0.4888 0.02031 0.01334 -0.1074 0.7074 1.0000
-0.250 0.5062 0.02064 0.01352 -0.1058 0.6971 1.0000
0.000 0.5325 0.02053 0.01320 -0.1051 0.6904 1.0000
0.250 0.5514 0.02089 0.01343 -0.1037 0.6809 1.0000
0.500 0.5773 0.02088 0.01323 -0.1030 0.6736 1.0000
0.750 0.5993 0.02115 0.01338 -0.1019 0.6653 1.0000
1.000 0.6233 0.02131 0.01340 -0.1011 0.6573 1.0000
1.250 0.6528 0.02129 0.01319 -0.1010 0.6520 1.0000
1.500 0.6696 0.02194 0.01382 -0.0995 0.6419 1.0000
1.750 0.7002 0.02188 0.01357 -0.0995 0.6365 1.0000
2.000 0.7179 0.02256 0.01424 -0.0982 0.6274 1.0000
2.250 0.7452 0.02272 0.01428 -0.0979 0.6212 1.0000
2.500 0.7732 0.02293 0.01437 -0.0978 0.6158 1.0000
2.750 0.7903 0.02368 0.01515 -0.0964 0.6071 1.0000
3.000 0.8208 0.02372 0.01505 -0.0966 0.6020 1.0000
3.250 0.8405 0.02445 0.01578 -0.0956 0.5950 1.0000
3.500 0.8628 0.02497 0.01628 -0.0949 0.5882 1.0000
3.750 0.8950 0.02496 0.01615 -0.0953 0.5837 1.0000
4.000 0.9098 0.02597 0.01723 -0.0938 0.5761 1.0000
4.250 0.9338 0.02641 0.01764 -0.0933 0.5700 1.0000
4.500 0.9674 0.02635 0.01747 -0.0939 0.5659 1.0000
4.750 0.9781 0.02760 0.01883 -0.0919 0.5580 1.0000
5.000 1.0035 0.02796 0.01916 -0.0916 0.5522 1.0000
5.250 1.0396 0.02774 0.01883 -0.0924 0.5482 1.0000
5.500 1.0454 0.02922 0.02047 -0.0899 0.5397 1.0000
5.750 1.0750 0.02923 0.02042 -0.0900 0.5341 1.0000
6.000 1.1071 0.02918 0.02029 -0.0903 0.5288 1.0000
6.250 1.1158 0.03033 0.02158 -0.0880 0.5203 1.0000
6.500 1.1532 0.02988 0.02101 -0.0890 0.5152 1.0000
6.750 1.1645 0.03099 0.02224 -0.0870 0.5078 1.0000
7.000 1.1876 0.03134 0.02261 -0.0864 0.5013 1.0000
7.250 1.2289 0.03084 0.02198 -0.0879 0.4970 1.0000
7.500 1.2266 0.03265 0.02401 -0.0844 0.4886 1.0000
7.750 1.2578 0.03259 0.02393 -0.0847 0.4830 1.0000
8.000 1.2866 0.03279 0.02411 -0.0847 0.4774 1.0000
8.250 1.2900 0.03417 0.02565 -0.0818 0.4692 1.0000
8.500 1.3335 0.03352 0.02490 -0.0836 0.4641 1.0000
8.750 1.3316 0.03525 0.02681 -0.0801 0.4561 1.0000
9.000 1.3581 0.03546 0.02704 -0.0799 0.4497 1.0000
9.250 1.3940 0.03535 0.02688 -0.0808 0.4439 1.0000
9.500 1.3851 0.03722 0.02895 -0.0765 0.4353 1.0000
9.750 1.4390 0.03614 0.02773 -0.0795 0.4294 1.0000
10.000 1.4179 0.03857 0.03042 -0.0738 0.4207 1.0000
10.250 1.4594 0.03804 0.02982 -0.0752 0.4141 1.0000
10.500 1.4576 0.03966 0.03159 -0.0719 0.4066 1.0000
10.750 1.4680 0.04049 0.03248 -0.0697 0.3992 1.0000
11.000 1.5042 0.04032 0.03229 -0.0707 0.3920 1.0000
11.250 1.4717 0.04300 0.03517 -0.0639 0.3842 1.0000
11.500 1.5409 0.04096 0.03296 -0.0681 0.3763 1.0000
11.750 1.4807 0.04531 0.03761 -0.0593 0.3689 1.0000
12.000 1.5723 0.04170 0.03374 -0.0650 0.3606 1.0000
12.250 1.4909 0.04764 0.04007 -0.0554 0.3539 1.0000
12.500 1.5710 0.04399 0.03621 -0.0590 0.3459 1.0000
12.750 1.3687 0.06263 0.05539 -0.0479 0.3369 1.0000
13.000 1.5255 0.04998 0.04253 -0.0513 0.3324 1.0000
13.250 1.5446 0.05048 0.04306 -0.0506 0.3261 1.0000
13.500 1.3759 0.06896 0.06191 -0.0453 0.3165 1.0000
13.750 1.5974 0.05023 0.04278 -0.0499 0.3127 1.0000
14.250 1.4164 0.07179 0.06492 -0.0432 0.2995 1.0000
14.500 0.9838 0.14731 0.14041 -0.0657 0.2593 1.0000
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