GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 573 AIRFOIL (goe573-il) Reynolds number: 200,000 Max Cl/Cd: 64.7 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe573-il-200000.txt Download as CSV file: xf-goe573-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 573 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2069 0.12490 0.12172 -0.0397 1.0000 0.0339
-10.750 -0.2059 0.12245 0.11933 -0.0395 1.0000 0.0349
-10.500 -0.2069 0.12029 0.11725 -0.0390 1.0000 0.0354
-10.250 -0.1893 0.11598 0.11294 -0.0471 0.9953 0.0378
-10.000 -0.1779 0.11206 0.10903 -0.0575 0.9865 0.0382
-9.750 -0.1594 0.10596 0.10294 -0.0605 0.9755 0.0388
-9.500 -0.1419 0.10193 0.09892 -0.0608 0.9465 0.0394
-9.250 -0.1163 0.09745 0.09439 -0.0649 0.9274 0.0405
-9.000 -0.0851 0.09246 0.08933 -0.0726 0.9131 0.0422
-8.750 -0.0476 0.08670 0.08345 -0.0850 0.8980 0.0451
-8.500 -0.0113 0.07954 0.07607 -0.1136 0.8709 0.0467
-8.250 0.0443 0.07360 0.07000 -0.1134 0.8538 0.0491
-8.000 0.0744 0.06976 0.06594 -0.1203 0.8223 0.0510
-7.750 0.0820 0.06684 0.06285 -0.1235 0.7942 0.0531
-7.500 0.0773 0.06454 0.06042 -0.1240 0.7710 0.0544
-7.250 0.0675 0.06234 0.05804 -0.1264 0.7530 0.0564
-7.000 0.0589 0.06060 0.05596 -0.1270 0.7379 0.0571
-6.750 0.0637 0.05581 0.05116 -0.1260 0.7249 0.0580
-6.500 0.0755 0.05352 0.04885 -0.1243 0.7119 0.0591
-6.000 0.0947 0.04987 0.04500 -0.1217 0.6882 0.0633
-5.750 0.0985 0.04948 0.04397 -0.1204 0.6790 0.0695
-5.500 0.1050 0.04460 0.03908 -0.1194 0.6701 0.0708
-5.250 0.1182 0.04246 0.03695 -0.1181 0.6600 0.0722
-5.000 0.1327 0.04082 0.03519 -0.1169 0.6514 0.0745
-4.750 0.1458 0.03924 0.03346 -0.1151 0.6419 0.0790
-4.500 0.1558 0.03710 0.03089 -0.1129 0.6349 0.0855
-4.250 0.1713 0.03550 0.02931 -0.1115 0.6256 0.0884
-3.750 0.2008 0.03254 0.02584 -0.1075 0.6106 0.1012
-3.500 0.2199 0.03116 0.02434 -0.1065 0.6040 0.1054
-3.250 0.2343 0.03010 0.02298 -0.1039 0.5967 0.1164
-3.000 0.2540 0.02871 0.02154 -0.1029 0.5904 0.1218
-2.750 0.2712 0.02761 0.02025 -0.1012 0.5842 0.1344
-2.500 0.2891 0.02665 0.01912 -0.0994 0.5780 0.1486
-2.250 0.3093 0.02570 0.01796 -0.0982 0.5731 0.1639
-2.000 0.3434 0.02196 0.01321 -0.0952 0.5682 0.0779
-1.750 0.3676 0.02087 0.01186 -0.0941 0.5625 0.0759
-1.500 0.3954 0.01982 0.01042 -0.0935 0.5578 0.0728
-1.250 0.4213 0.01915 0.00961 -0.0928 0.5526 0.0718
-1.000 0.4476 0.01855 0.00891 -0.0923 0.5476 0.0719
-0.750 0.4752 0.01805 0.00832 -0.0922 0.5434 0.0730
-0.500 0.5020 0.01779 0.00802 -0.0920 0.5396 0.0760
-0.250 0.5257 0.01753 0.00778 -0.0911 0.5351 0.0790
0.000 0.5505 0.01727 0.00749 -0.0904 0.5311 0.0813
0.250 0.5757 0.01703 0.00719 -0.0899 0.5277 0.0842
0.500 0.5997 0.01684 0.00701 -0.0891 0.5244 0.0904
0.750 0.6205 0.01675 0.00698 -0.0877 0.5204 0.1008
1.000 0.8371 0.01505 0.00715 -0.1285 0.5127 1.0000
1.250 0.8626 0.01528 0.00723 -0.1282 0.5101 1.0000
1.500 0.8839 0.01550 0.00744 -0.1270 0.5070 1.0000
1.750 0.9055 0.01571 0.00764 -0.1259 0.5037 1.0000
2.000 0.9282 0.01591 0.00778 -0.1250 0.5005 1.0000
2.250 0.9522 0.01612 0.00792 -0.1244 0.4977 1.0000
2.500 0.9776 0.01637 0.00807 -0.1241 0.4953 1.0000
2.750 1.0006 0.01669 0.00836 -0.1233 0.4929 1.0000
3.000 1.0204 0.01697 0.00870 -0.1219 0.4900 1.0000
3.250 1.0415 0.01723 0.00898 -0.1208 0.4870 1.0000
3.500 1.0640 0.01748 0.00921 -0.1199 0.4842 1.0000
3.750 1.0881 0.01774 0.00943 -0.1194 0.4818 1.0000
4.000 1.1141 0.01804 0.00966 -0.1192 0.4795 1.0000
4.250 1.1346 0.01840 0.01006 -0.1180 0.4769 1.0000
4.500 1.1523 0.01873 0.01048 -0.1163 0.4738 1.0000
4.750 1.1722 0.01900 0.01079 -0.1149 0.4703 1.0000
5.000 1.1949 0.01919 0.01096 -0.1141 0.4671 1.0000
5.250 1.2218 0.01942 0.01110 -0.1141 0.4640 1.0000
5.500 1.2404 0.01980 0.01156 -0.1126 0.4611 1.0000
5.750 1.2564 0.02018 0.01206 -0.1106 0.4579 1.0000
6.000 1.2754 0.02052 0.01246 -0.1091 0.4550 1.0000
6.250 1.2968 0.02080 0.01277 -0.1082 0.4522 1.0000
6.500 1.3218 0.02108 0.01304 -0.1079 0.4498 1.0000
6.750 1.3474 0.02149 0.01343 -0.1078 0.4472 1.0000
7.000 1.3582 0.02196 0.01408 -0.1048 0.4441 1.0000
7.250 1.3732 0.02238 0.01462 -0.1027 0.4409 1.0000
7.500 1.3920 0.02274 0.01507 -0.1013 0.4381 1.0000
7.750 1.4146 0.02303 0.01538 -0.1006 0.4354 1.0000
8.000 1.4437 0.02323 0.01551 -0.1011 0.4317 1.0000
8.250 1.4467 0.02360 0.01609 -0.0967 0.4269 1.0000
8.500 1.4631 0.02358 0.01612 -0.0946 0.4215 1.0000
8.750 1.4920 0.02340 0.01583 -0.0949 0.4159 1.0000
9.000 1.4931 0.02376 0.01640 -0.0901 0.4111 1.0000
9.250 1.5081 0.02369 0.01635 -0.0878 0.4055 1.0000
9.500 1.5307 0.02367 0.01630 -0.0870 0.4003 1.0000
9.750 1.5268 0.02392 0.01675 -0.0812 0.3946 1.0000
10.000 1.5411 0.02382 0.01664 -0.0788 0.3888 1.0000
10.250 1.5463 0.02398 0.01688 -0.0748 0.3834 1.0000
10.500 1.5381 0.02412 0.01714 -0.0682 0.3775 1.0000
10.750 1.5471 0.02396 0.01694 -0.0648 0.3707 1.0000
11.000 1.5344 0.02443 0.01762 -0.0581 0.3641 1.0000
11.250 1.5346 0.02455 0.01772 -0.0537 0.3554 1.0000
11.500 1.5247 0.02529 0.01863 -0.0484 0.3457 1.0000
11.750 1.5168 0.02618 0.01961 -0.0439 0.3330 1.0000
12.000 1.5070 0.02750 0.02097 -0.0398 0.3170 1.0000
12.250 1.4932 0.02946 0.02290 -0.0360 0.2956 1.0000
12.500 1.4725 0.03234 0.02568 -0.0325 0.2709 1.0000
12.750 1.4503 0.03590 0.02915 -0.0297 0.2479 1.0000
13.000 1.4271 0.03994 0.03313 -0.0275 0.2296 1.0000
13.250 1.4011 0.04460 0.03773 -0.0257 0.2094 1.0000
13.500 1.3725 0.04984 0.04291 -0.0244 0.1884 1.0000
13.750 1.3490 0.05483 0.04786 -0.0236 0.1659 1.0000
14.000 1.3217 0.06046 0.05341 -0.0230 0.1413 1.0000
14.250 1.2927 0.06653 0.05937 -0.0228 0.1186 1.0000
14.500 1.2626 0.07292 0.06565 -0.0228 0.0939 1.0000
14.750 1.2373 0.07893 0.07156 -0.0229 0.0691 1.0000
15.000 1.2153 0.08470 0.07727 -0.0232 0.0550 1.0000
15.250 1.1969 0.09018 0.08274 -0.0237 0.0467 1.0000
15.500 1.1859 0.09477 0.08740 -0.0241 0.0426 1.0000
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