GOE 625 AIRFOIL (goe625-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 625 AIRFOIL (goe625-il) Reynolds number: 200,000 Max Cl/Cd: 57.43 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe625-il-200000-n5.txt Download as CSV file: xf-goe625-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 625 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5345 0.04022 0.03492 -0.1411 0.9127 0.0620
-12.500 -0.5596 0.03674 0.03105 -0.1398 0.9009 0.0629
-12.250 -0.5715 0.03437 0.02828 -0.1376 0.8914 0.0640
-12.000 -0.5535 0.03382 0.02775 -0.1367 0.8841 0.0646
-11.750 -0.5359 0.03318 0.02705 -0.1358 0.8776 0.0655
-11.500 -0.5217 0.03240 0.02619 -0.1346 0.8694 0.0664
-11.250 -0.5075 0.03136 0.02496 -0.1336 0.8626 0.0677
-11.000 -0.4949 0.03010 0.02343 -0.1324 0.8559 0.0691
-10.750 -0.4831 0.02880 0.02175 -0.1310 0.8482 0.0705
-10.500 -0.4605 0.02814 0.02109 -0.1304 0.8421 0.0713
-10.250 -0.4388 0.02762 0.02056 -0.1297 0.8345 0.0723
-10.000 -0.4176 0.02702 0.01988 -0.1289 0.8262 0.0735
-9.750 -0.3958 0.02630 0.01897 -0.1283 0.8197 0.0750
-9.500 -0.3757 0.02555 0.01803 -0.1274 0.8121 0.0764
-9.250 -0.3543 0.02481 0.01701 -0.1267 0.8063 0.0778
-9.000 -0.3292 0.02416 0.01636 -0.1264 0.8015 0.0790
-8.750 -0.3055 0.02371 0.01593 -0.1259 0.7947 0.0802
-8.500 -0.2811 0.02324 0.01540 -0.1255 0.7880 0.0816
-8.250 -0.2559 0.02270 0.01471 -0.1251 0.7823 0.0831
-8.000 -0.2322 0.02218 0.01405 -0.1246 0.7748 0.0847
-7.750 -0.2073 0.02165 0.01334 -0.1241 0.7678 0.0860
-7.500 -0.1814 0.02109 0.01277 -0.1239 0.7618 0.0872
-7.250 -0.1564 0.02069 0.01238 -0.1234 0.7540 0.0884
-7.000 -0.1303 0.02029 0.01191 -0.1231 0.7469 0.0898
-6.750 -0.1044 0.01988 0.01143 -0.1228 0.7396 0.0912
-6.500 -0.0787 0.01948 0.01093 -0.1224 0.7312 0.0925
-6.250 -0.0522 0.01909 0.01041 -0.1221 0.7233 0.0938
-6.000 -0.0267 0.01871 0.00997 -0.1216 0.7134 0.0951
-5.750 -0.0006 0.01835 0.00958 -0.1213 0.7040 0.0964
-5.500 0.0251 0.01805 0.00924 -0.1208 0.6929 0.0976
-5.250 0.0512 0.01777 0.00890 -0.1204 0.6820 0.0990
-5.000 0.0772 0.01752 0.00857 -0.1200 0.6701 0.1007
-4.750 0.1030 0.01729 0.00826 -0.1196 0.6576 0.1025
-4.500 0.1288 0.01708 0.00794 -0.1191 0.6445 0.1041
-4.250 0.1540 0.01687 0.00768 -0.1185 0.6305 0.1058
-4.000 0.1791 0.01672 0.00748 -0.1180 0.6151 0.1077
-3.750 0.2042 0.01661 0.00728 -0.1174 0.5997 0.1099
-3.500 0.2290 0.01652 0.00708 -0.1168 0.5844 0.1126
-3.250 0.2534 0.01645 0.00692 -0.1161 0.5695 0.1156
-3.000 0.2775 0.01644 0.00683 -0.1153 0.5552 0.1191
-2.750 0.3020 0.01642 0.00673 -0.1147 0.5419 0.1237
-2.500 0.3265 0.01641 0.00666 -0.1140 0.5306 0.1284
-2.250 0.3509 0.01644 0.00662 -0.1134 0.5207 0.1344
-2.000 0.3759 0.01645 0.00659 -0.1129 0.5124 0.1411
-1.750 0.4009 0.01649 0.00658 -0.1123 0.5046 0.1488
-1.500 0.4256 0.01655 0.00658 -0.1118 0.4983 0.1564
-1.250 0.4514 0.01659 0.00660 -0.1114 0.4923 0.1647
-1.000 0.4767 0.01663 0.00661 -0.1110 0.4867 0.1721
-0.750 0.5018 0.01671 0.00664 -0.1106 0.4819 0.1797
-0.500 0.5276 0.01679 0.00667 -0.1102 0.4777 0.1866
-0.250 0.5532 0.01680 0.00672 -0.1099 0.4732 0.1939
0.000 0.5787 0.01688 0.00676 -0.1096 0.4688 0.2016
0.250 0.6040 0.01695 0.00682 -0.1092 0.4649 0.2100
0.500 0.6296 0.01706 0.00690 -0.1089 0.4616 0.2211
0.750 0.6556 0.01710 0.00699 -0.1087 0.4587 0.2341
1.000 0.6815 0.01713 0.00709 -0.1085 0.4557 0.2507
1.250 0.7070 0.01713 0.00722 -0.1083 0.4527 0.2813
1.500 0.7319 0.01702 0.00737 -0.1080 0.4499 0.3563
1.750 0.7556 0.01682 0.00755 -0.1075 0.4470 0.4793
2.000 0.7765 0.01649 0.00779 -0.1063 0.4443 0.6586
2.250 0.7960 0.01634 0.00810 -0.1039 0.4418 0.8438
2.500 0.8401 0.01651 0.00838 -0.1070 0.4392 0.9663
2.750 0.8771 0.01674 0.00857 -0.1092 0.4366 1.0000
3.000 0.8993 0.01694 0.00873 -0.1083 0.4338 1.0000
3.250 0.9210 0.01715 0.00889 -0.1073 0.4305 1.0000
3.500 0.9431 0.01739 0.00904 -0.1064 0.4270 1.0000
3.750 0.9664 0.01766 0.00920 -0.1058 0.4234 1.0000
4.000 0.9878 0.01791 0.00941 -0.1048 0.4200 1.0000
4.250 1.0074 0.01813 0.00964 -0.1035 0.4163 1.0000
4.500 1.0275 0.01837 0.00986 -0.1023 0.4132 1.0000
4.750 1.0483 0.01863 0.01009 -0.1012 0.4103 1.0000
5.000 1.0698 0.01891 0.01032 -0.1003 0.4077 1.0000
5.250 1.0928 0.01921 0.01056 -0.0997 0.4051 1.0000
5.500 1.1175 0.01953 0.01081 -0.0995 0.4027 1.0000
5.750 1.1367 0.01983 0.01116 -0.0982 0.4004 1.0000
6.000 1.1564 0.02015 0.01151 -0.0972 0.3978 1.0000
6.250 1.1762 0.02048 0.01187 -0.0961 0.3950 1.0000
6.500 1.1957 0.02083 0.01222 -0.0950 0.3921 1.0000
6.750 1.2157 0.02118 0.01256 -0.0941 0.3892 1.0000
7.000 1.2369 0.02154 0.01288 -0.0934 0.3865 1.0000
7.250 1.2587 0.02192 0.01322 -0.0928 0.3838 1.0000
7.500 1.2754 0.02237 0.01375 -0.0914 0.3810 1.0000
7.750 1.2928 0.02282 0.01426 -0.0902 0.3779 1.0000
8.000 1.3102 0.02329 0.01477 -0.0891 0.3748 1.0000
8.250 1.3278 0.02376 0.01526 -0.0880 0.3717 1.0000
8.500 1.3465 0.02422 0.01570 -0.0871 0.3689 1.0000
8.750 1.3655 0.02470 0.01616 -0.0862 0.3660 1.0000
9.000 1.3788 0.02536 0.01693 -0.0847 0.3623 1.0000
9.250 1.3927 0.02602 0.01767 -0.0834 0.3584 1.0000
9.500 1.4070 0.02667 0.01835 -0.0821 0.3545 1.0000
9.750 1.4222 0.02731 0.01897 -0.0809 0.3511 1.0000
10.000 1.4362 0.02805 0.01976 -0.0797 0.3474 1.0000
10.250 1.4473 0.02895 0.02078 -0.0783 0.3427 1.0000
10.500 1.4586 0.02985 0.02171 -0.0770 0.3379 1.0000
10.750 1.4703 0.03072 0.02257 -0.0757 0.3336 1.0000
11.000 1.4799 0.03184 0.02379 -0.0743 0.3283 1.0000
11.250 1.4886 0.03301 0.02502 -0.0730 0.3227 1.0000
11.500 1.4973 0.03417 0.02618 -0.0716 0.3179 1.0000
11.750 1.5053 0.03552 0.02761 -0.0704 0.3125 1.0000
12.000 1.5123 0.03695 0.02910 -0.0692 0.3067 1.0000
12.250 1.5187 0.03844 0.03057 -0.0679 0.3017 1.0000
12.500 1.5248 0.04009 0.03232 -0.0669 0.2961 1.0000
12.750 1.5296 0.04186 0.03412 -0.0657 0.2905 1.0000
13.000 1.5341 0.04368 0.03593 -0.0647 0.2858 1.0000
13.250 1.5387 0.04563 0.03797 -0.0638 0.2809 1.0000
13.500 1.5424 0.04766 0.04004 -0.0629 0.2761 1.0000
13.750 1.5455 0.04975 0.04213 -0.0620 0.2720 1.0000
14.000 1.5486 0.05195 0.04441 -0.0612 0.2679 1.0000
14.250 1.5505 0.05434 0.04686 -0.0605 0.2634 1.0000
14.500 1.5518 0.05678 0.04932 -0.0599 0.2592 1.0000
14.750 1.5552 0.05895 0.05147 -0.0593 0.2556 1.0000
15.000 1.5557 0.06164 0.05428 -0.0588 0.2520 1.0000
15.250 1.5557 0.06439 0.05712 -0.0584 0.2484 1.0000
15.500 1.5566 0.06703 0.05980 -0.0580 0.2449 1.0000
15.750 1.5597 0.06938 0.06213 -0.0577 0.2416 1.0000
16.000 1.5591 0.07226 0.06508 -0.0575 0.2383 1.0000
16.250 1.5557 0.07559 0.06854 -0.0574 0.2348 1.0000
16.500 1.5537 0.07872 0.07174 -0.0573 0.2313 1.0000
16.750 1.5551 0.08140 0.07444 -0.0573 0.2280 1.0000
17.000 1.5611 0.08344 0.07645 -0.0572 0.2249 1.0000
17.250 1.5529 0.08752 0.08070 -0.0575 0.2219 1.0000
17.500 1.5465 0.09137 0.08468 -0.0578 0.2186 1.0000
17.750 1.5444 0.09463 0.08800 -0.0581 0.2154 1.0000
18.000 1.5481 0.09705 0.09043 -0.0583 0.2122 1.0000
18.250 1.5479 0.10006 0.09347 -0.0587 0.2089 1.0000
18.500 1.5341 0.10510 0.09869 -0.0595 0.2053 1.0000
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