GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 457 AIRFOIL (goe457-il) Reynolds number: 100,000 Max Cl/Cd: 54.53 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe457-il-100000.txt Download as CSV file: xf-goe457-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 457 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3566 0.09383 0.08913 -0.0216 1.0000 0.0792
-7.250 -0.3685 0.09250 0.08791 -0.0209 1.0000 0.0810
-7.000 -0.3787 0.09140 0.08690 -0.0252 1.0000 0.0825
-6.750 -0.3805 0.08982 0.08530 -0.0327 1.0000 0.0832
-6.500 -0.3777 0.08431 0.07991 -0.0263 1.0000 0.0845
-6.250 -0.3724 0.08117 0.07680 -0.0218 1.0000 0.0866
-6.000 -0.3683 0.07856 0.07422 -0.0207 1.0000 0.0899
-5.750 -0.3626 0.07583 0.07149 -0.0237 1.0000 0.0951
-5.500 -0.3515 0.07178 0.06735 -0.0313 1.0000 0.0989
-5.250 -0.3483 0.06897 0.06464 -0.0263 1.0000 0.1015
-5.000 -0.3389 0.06622 0.06189 -0.0260 1.0000 0.1059
-4.750 -0.3163 0.06192 0.05738 -0.0340 1.0000 0.1140
-4.500 -0.3095 0.05919 0.05474 -0.0309 1.0000 0.1168
-4.250 -0.2837 0.05569 0.05097 -0.0367 1.0000 0.1287
-4.000 -0.2760 0.05304 0.04844 -0.0336 1.0000 0.1323
-3.750 -0.2563 0.05014 0.04543 -0.0355 1.0000 0.1458
-3.500 -0.2368 0.04757 0.04275 -0.0366 1.0000 0.1599
-3.250 -0.2174 0.04515 0.04025 -0.0372 1.0000 0.1746
-3.000 -0.1989 0.04294 0.03799 -0.0373 1.0000 0.1900
-2.000 -0.0659 0.02855 0.02160 -0.0456 1.0000 0.1176
-1.750 -0.0223 0.02611 0.01853 -0.0482 0.9954 0.1065
-1.500 0.0307 0.02407 0.01579 -0.0523 0.9863 0.1009
-1.250 0.0822 0.02274 0.01406 -0.0564 0.9755 0.1000
-1.000 0.1324 0.02164 0.01288 -0.0605 0.9634 0.1052
-0.750 0.1829 0.02070 0.01176 -0.0643 0.9504 0.1111
-0.500 0.2318 0.01949 0.01067 -0.0679 0.9369 0.1187
-0.250 0.2809 0.01838 0.00969 -0.0713 0.9226 0.1395
0.000 0.3480 0.01504 0.00877 -0.0780 0.9166 1.0000
0.250 0.4028 0.01457 0.00800 -0.0823 0.9009 1.0000
0.500 0.4481 0.01411 0.00736 -0.0846 0.8785 1.0000
0.750 0.4957 0.01357 0.00667 -0.0873 0.8561 1.0000
1.000 0.5323 0.01320 0.00616 -0.0879 0.8230 1.0000
1.250 0.5704 0.01290 0.00568 -0.0888 0.7870 1.0000
1.500 0.6080 0.01278 0.00529 -0.0897 0.7513 1.0000
1.750 0.6401 0.01294 0.00518 -0.0898 0.7168 1.0000
2.000 0.6690 0.01325 0.00523 -0.0894 0.6872 1.0000
2.250 0.6962 0.01364 0.00539 -0.0889 0.6616 1.0000
2.500 0.7221 0.01404 0.00562 -0.0882 0.6386 1.0000
2.750 0.7481 0.01447 0.00588 -0.0876 0.6186 1.0000
3.000 0.7731 0.01491 0.00621 -0.0868 0.5994 1.0000
3.250 0.7985 0.01537 0.00657 -0.0862 0.5822 1.0000
3.500 0.8238 0.01585 0.00696 -0.0855 0.5660 1.0000
3.750 0.8489 0.01636 0.00741 -0.0848 0.5505 1.0000
4.000 0.8737 0.01687 0.00787 -0.0841 0.5355 1.0000
4.250 0.8980 0.01736 0.00831 -0.0832 0.5196 1.0000
4.500 0.9218 0.01782 0.00873 -0.0823 0.5030 1.0000
4.750 0.9452 0.01823 0.00908 -0.0812 0.4862 1.0000
5.000 0.9685 0.01861 0.00940 -0.0801 0.4697 1.0000
5.250 0.9908 0.01894 0.00975 -0.0789 0.4533 1.0000
5.500 1.0135 0.01926 0.01013 -0.0778 0.4377 1.0000
5.750 1.0358 0.01956 0.01047 -0.0766 0.4221 1.0000
6.000 1.0578 0.01985 0.01081 -0.0753 0.4064 1.0000
6.250 1.0792 0.02011 0.01114 -0.0740 0.3899 1.0000
6.500 1.1001 0.02035 0.01147 -0.0725 0.3723 1.0000
6.750 1.1206 0.02061 0.01177 -0.0710 0.3538 1.0000
7.000 1.1397 0.02090 0.01211 -0.0693 0.3320 1.0000
7.250 1.1567 0.02124 0.01245 -0.0672 0.3047 1.0000
7.500 1.1713 0.02181 0.01299 -0.0648 0.2691 1.0000
7.750 1.1853 0.02274 0.01370 -0.0624 0.2357 1.0000
8.000 1.2011 0.02377 0.01463 -0.0605 0.2102 1.0000
8.250 1.2177 0.02476 0.01548 -0.0587 0.1928 1.0000
8.500 1.2345 0.02570 0.01636 -0.0571 0.1782 1.0000
8.750 1.2521 0.02657 0.01734 -0.0556 0.1666 1.0000
9.000 1.2698 0.02752 0.01838 -0.0542 0.1571 1.0000
9.250 1.2861 0.02847 0.01935 -0.0527 0.1481 1.0000
9.500 1.3025 0.02939 0.02035 -0.0511 0.1404 1.0000
9.750 1.3200 0.03050 0.02158 -0.0498 0.1345 1.0000
10.000 1.3347 0.03145 0.02268 -0.0481 0.1274 1.0000
10.250 1.3457 0.03247 0.02387 -0.0460 0.1188 1.0000
10.500 1.3538 0.03358 0.02500 -0.0436 0.1096 1.0000
10.750 1.3562 0.03452 0.02615 -0.0403 0.1000 1.0000
11.000 1.3570 0.03586 0.02771 -0.0370 0.0898 1.0000
11.250 1.3536 0.03758 0.02956 -0.0336 0.0784 1.0000
11.500 1.3487 0.03973 0.03177 -0.0304 0.0684 1.0000
11.750 1.3444 0.04194 0.03398 -0.0279 0.0612 1.0000
12.000 1.3429 0.04445 0.03667 -0.0257 0.0551 1.0000
12.250 1.3407 0.04678 0.03908 -0.0241 0.0514 1.0000
12.500 1.3390 0.04959 0.04198 -0.0226 0.0483 1.0000
12.750 1.3388 0.05248 0.04511 -0.0215 0.0457 1.0000
13.000 1.3383 0.05548 0.04827 -0.0206 0.0439 1.0000
13.250 1.3369 0.05857 0.05148 -0.0200 0.0423 1.0000
13.500 1.3368 0.06176 0.05473 -0.0196 0.0411 1.0000
13.750 1.3355 0.06564 0.05872 -0.0192 0.0401 1.0000
14.000 1.3275 0.07013 0.06350 -0.0196 0.0396 1.0000
14.250 1.3163 0.07515 0.06881 -0.0207 0.0393 1.0000
14.500 1.3023 0.08075 0.07467 -0.0225 0.0392 1.0000
14.750 1.2857 0.08694 0.08111 -0.0250 0.0392 1.0000
15.000 1.2664 0.09383 0.08824 -0.0284 0.0393 1.0000
15.250 1.2453 0.10139 0.09602 -0.0325 0.0394 1.0000
15.500 1.2227 0.10965 0.10448 -0.0373 0.0397 1.0000
15.750 1.1992 0.11860 0.11360 -0.0428 0.0400 1.0000
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