GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 573 AIRFOIL (goe573-il) Reynolds number: 500,000 Max Cl/Cd: 99.85 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe573-il-500000.txt Download as CSV file: xf-goe573-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.2492 0.14773 0.14550 -0.0343 1.0000 0.0177
-13.000 -0.2499 0.14461 0.14241 -0.0360 1.0000 0.0178
-12.750 -0.2509 0.14158 0.13941 -0.0375 1.0000 0.0178
-12.500 -0.2412 0.13782 0.13566 -0.0367 1.0000 0.0180
-12.250 -0.2348 0.13502 0.13288 -0.0365 1.0000 0.0181
-12.000 -0.2282 0.13244 0.13032 -0.0366 0.9999 0.0184
-11.750 -0.2071 0.12813 0.12600 -0.0417 0.9980 0.0189
-11.500 -0.1868 0.12372 0.12157 -0.0469 0.9952 0.0192
-11.250 -0.1692 0.11940 0.11725 -0.0515 0.9916 0.0206
-11.000 -0.1579 0.11450 0.11235 -0.0581 0.9863 0.0215
-10.250 -0.0903 0.09925 0.09699 -0.0753 0.9119 0.0224
-10.000 -0.0248 0.09184 0.08938 -0.0932 0.8913 0.0233
-9.750 0.0225 0.08425 0.08153 -0.1133 0.8582 0.0260
-9.500 0.0425 0.07957 0.07659 -0.1215 0.8126 0.0262
-9.250 0.0469 0.07611 0.07295 -0.1244 0.7772 0.0262
-9.000 0.0532 0.07319 0.06988 -0.1233 0.7494 0.0266
-8.750 0.0629 0.07136 0.06794 -0.1226 0.7258 0.0269
-8.500 0.0696 0.06940 0.06588 -0.1226 0.7062 0.0274
-8.250 0.0737 0.06726 0.06366 -0.1231 0.6899 0.0280
-8.000 0.0738 0.06481 0.06117 -0.1239 0.6765 0.0285
-7.750 0.0681 0.06220 0.05852 -0.1243 0.6652 0.0291
-7.500 0.0613 0.05985 0.05612 -0.1236 0.6549 0.0297
-7.250 0.0616 0.04083 0.03710 -0.1205 0.6303 0.0316
-7.000 0.0528 0.03612 0.03233 -0.1193 0.6239 0.0320
-6.750 0.0467 0.04722 0.04314 -0.1249 0.6321 0.0322
-6.500 0.0563 0.04587 0.04173 -0.1233 0.6228 0.0326
-6.250 0.0665 0.04427 0.04006 -0.1220 0.6143 0.0331
-6.000 0.0766 0.04251 0.03820 -0.1206 0.6063 0.0338
-5.750 0.0870 0.04044 0.03602 -0.1192 0.5986 0.0350
-5.500 0.0971 0.03740 0.03247 -0.1162 0.5924 0.0383
-5.250 0.0956 0.03294 0.02784 -0.1131 0.5865 0.0392
-5.000 0.1111 0.03178 0.02666 -0.1118 0.5785 0.0398
-4.750 0.1270 0.03082 0.02561 -0.1104 0.5712 0.0407
-4.500 0.1427 0.02954 0.02422 -0.1086 0.5637 0.0422
-4.250 0.1636 0.02932 0.02355 -0.1058 0.5569 0.0465
-4.000 0.1663 0.02526 0.01920 -0.1021 0.5513 0.0479
-3.750 0.1848 0.02416 0.01807 -0.1008 0.5442 0.0489
-3.500 0.2038 0.02336 0.01720 -0.0995 0.5376 0.0502
-3.250 0.2231 0.02251 0.01621 -0.0978 0.5309 0.0527
-3.000 0.2488 0.02357 0.01694 -0.0962 0.5244 0.0570
-2.750 0.2590 0.02011 0.01328 -0.0935 0.5191 0.0595
-2.500 0.2788 0.01761 0.01019 -0.0904 0.5140 0.0475
-2.250 0.3017 0.01636 0.00881 -0.0893 0.5087 0.0450
-2.000 0.3257 0.01534 0.00764 -0.0883 0.5036 0.0442
-1.750 0.3501 0.01467 0.00682 -0.0875 0.4986 0.0441
-1.500 0.3747 0.01419 0.00619 -0.0867 0.4940 0.0443
-1.250 0.3999 0.01378 0.00573 -0.0861 0.4898 0.0450
-1.000 0.4247 0.01353 0.00542 -0.0854 0.4856 0.0459
-0.750 0.4491 0.01329 0.00509 -0.0846 0.4817 0.0464
-0.500 0.4735 0.01305 0.00479 -0.0838 0.4780 0.0469
-0.250 0.4960 0.01254 0.00428 -0.0827 0.4748 0.0481
0.000 0.5185 0.01228 0.00402 -0.0816 0.4712 0.0496
0.250 0.5415 0.01216 0.00388 -0.0806 0.4678 0.0512
0.500 0.5650 0.01213 0.00380 -0.0797 0.4645 0.0537
0.750 0.5891 0.01209 0.00373 -0.0790 0.4618 0.0562
1.000 0.6122 0.01197 0.00361 -0.0780 0.4592 0.0598
1.250 0.6358 0.01190 0.00356 -0.0771 0.4565 0.0661
1.500 0.6587 0.01180 0.00354 -0.0761 0.4539 0.0941
1.750 0.6529 0.01030 0.00367 -0.0695 0.4521 0.6919
2.000 0.9373 0.01101 0.00465 -0.1260 0.4446 1.0000
2.250 0.9603 0.01111 0.00474 -0.1251 0.4424 1.0000
2.500 0.9832 0.01122 0.00482 -0.1243 0.4402 1.0000
2.750 1.0060 0.01134 0.00491 -0.1234 0.4381 1.0000
3.000 1.0289 0.01148 0.00502 -0.1225 0.4359 1.0000
3.250 1.0524 0.01167 0.00515 -0.1218 0.4336 1.0000
3.500 1.0753 0.01183 0.00530 -0.1210 0.4311 1.0000
3.750 1.0968 0.01192 0.00542 -0.1198 0.4287 1.0000
4.000 1.1181 0.01201 0.00552 -0.1186 0.4256 1.0000
4.250 1.1396 0.01212 0.00562 -0.1175 0.4229 1.0000
4.500 1.1613 0.01226 0.00574 -0.1164 0.4203 1.0000
4.750 1.1843 0.01249 0.00592 -0.1157 0.4177 1.0000
5.000 1.2063 0.01265 0.00611 -0.1147 0.4156 1.0000
5.250 1.2273 0.01277 0.00628 -0.1135 0.4138 1.0000
5.500 1.2486 0.01291 0.00646 -0.1124 0.4119 1.0000
5.750 1.2697 0.01305 0.00663 -0.1112 0.4098 1.0000
6.000 1.2908 0.01321 0.00680 -0.1101 0.4078 1.0000
6.250 1.3118 0.01337 0.00698 -0.1090 0.4058 1.0000
6.500 1.3331 0.01358 0.00718 -0.1079 0.4032 1.0000
6.750 1.3531 0.01378 0.00741 -0.1066 0.4002 1.0000
7.000 1.3676 0.01383 0.00754 -0.1041 0.3963 1.0000
7.250 1.3839 0.01392 0.00767 -0.1020 0.3926 1.0000
7.500 1.4007 0.01407 0.00783 -0.1000 0.3893 1.0000
7.750 1.4187 0.01430 0.00805 -0.0983 0.3856 1.0000
8.000 1.4306 0.01436 0.00821 -0.0953 0.3819 1.0000
8.250 1.4409 0.01443 0.00834 -0.0919 0.3779 1.0000
8.500 1.4512 0.01455 0.00849 -0.0886 0.3743 1.0000
8.750 1.4625 0.01474 0.00868 -0.0856 0.3703 1.0000
9.000 1.4720 0.01481 0.00886 -0.0822 0.3659 1.0000
9.250 1.4805 0.01494 0.00902 -0.0786 0.3596 1.0000
9.500 1.4903 0.01513 0.00926 -0.0755 0.3534 1.0000
9.750 1.5005 0.01533 0.00951 -0.0725 0.3454 1.0000
10.000 1.5101 0.01561 0.00982 -0.0694 0.3357 1.0000
10.250 1.5162 0.01601 0.01022 -0.0659 0.3206 1.0000
10.500 1.5147 0.01677 0.01088 -0.0613 0.2967 1.0000
10.750 1.5004 0.01824 0.01215 -0.0553 0.2615 1.0000
11.000 1.4790 0.02039 0.01410 -0.0491 0.2286 1.0000
11.250 1.4598 0.02282 0.01638 -0.0440 0.2003 1.0000
11.500 1.4292 0.02643 0.01979 -0.0389 0.1590 1.0000
11.750 1.4040 0.03022 0.02345 -0.0353 0.1273 1.0000
12.000 1.3748 0.03480 0.02795 -0.0325 0.1005 1.0000
12.250 1.3489 0.03948 0.03259 -0.0304 0.0754 1.0000
12.500 1.3192 0.04481 0.03787 -0.0287 0.0510 1.0000
12.750 1.2977 0.04955 0.04260 -0.0276 0.0358 1.0000
13.000 1.2835 0.05367 0.04675 -0.0268 0.0286 1.0000
13.250 1.2737 0.05745 0.05059 -0.0263 0.0253 1.0000
13.500 1.2668 0.06095 0.05418 -0.0259 0.0232 1.0000
13.750 1.2620 0.06429 0.05760 -0.0256 0.0225 1.0000
14.000 1.2560 0.06785 0.06124 -0.0254 0.0217 1.0000
14.250 1.2472 0.07180 0.06527 -0.0253 0.0207 1.0000
14.500 1.2387 0.07578 0.06935 -0.0253 0.0198 1.0000
14.750 1.2346 0.07926 0.07292 -0.0253 0.0196 1.0000
15.000 1.2303 0.08281 0.07655 -0.0254 0.0190 1.0000
15.250 1.2247 0.08654 0.08037 -0.0256 0.0184 1.0000
15.500 1.2194 0.09029 0.08420 -0.0258 0.0180 1.0000
15.750 1.2138 0.09413 0.08813 -0.0261 0.0176 1.0000
16.000 1.2064 0.09828 0.09235 -0.0266 0.0172 1.0000
16.250 1.2012 0.10210 0.09623 -0.0270 0.0168 1.0000
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Polar data table (+)
Polar graphs
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