GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 500 AIRFOIL (goe500-il) Reynolds number: 500,000 Max Cl/Cd: 131.78 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe500-il-500000.txt Download as CSV file: xf-goe500-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 500 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2086 0.10477 0.10238 -0.0677 0.9851 0.0286
-10.000 -0.1941 0.10109 0.09869 -0.0715 0.9839 0.0297
-9.000 -0.2688 0.02704 0.02365 -0.1595 0.9491 0.0269
-8.750 -0.2419 0.02621 0.02283 -0.1608 0.9457 0.0279
-8.500 -0.2130 0.02521 0.02175 -0.1625 0.9429 0.0289
-8.250 -0.1885 0.02293 0.01914 -0.1648 0.9390 0.0300
-8.000 -0.1671 0.02122 0.01711 -0.1654 0.9334 0.0311
-7.750 -0.1395 0.02050 0.01612 -0.1660 0.9297 0.0321
-7.500 -0.1151 0.01788 0.01323 -0.1674 0.9263 0.0337
-7.250 -0.0899 0.01719 0.01246 -0.1673 0.9222 0.0348
-7.000 -0.0647 0.01647 0.01161 -0.1672 0.9175 0.0359
-6.750 -0.0374 0.01577 0.01076 -0.1673 0.9137 0.0373
-6.500 -0.0090 0.01525 0.01007 -0.1675 0.9105 0.0385
-6.250 0.0164 0.01428 0.00891 -0.1674 0.9060 0.0395
-6.000 0.0419 0.01327 0.00781 -0.1672 0.9012 0.0410
-5.750 0.0697 0.01281 0.00730 -0.1673 0.8973 0.0427
-5.250 0.1238 0.01193 0.00624 -0.1668 0.8876 0.0456
-5.000 0.1516 0.01153 0.00575 -0.1667 0.8824 0.0468
-4.750 0.1794 0.01088 0.00501 -0.1666 0.8777 0.0492
-4.500 0.2057 0.01049 0.00461 -0.1663 0.8708 0.0516
-4.250 0.2338 0.01016 0.00420 -0.1661 0.8652 0.0544
-4.000 0.2613 0.00990 0.00388 -0.1659 0.8590 0.0570
-3.750 0.2888 0.00952 0.00351 -0.1657 0.8527 0.0638
-3.500 0.3175 0.00928 0.00326 -0.1657 0.8479 0.0746
-3.250 0.3447 0.00916 0.00319 -0.1655 0.8408 0.0903
-3.000 0.3728 0.00905 0.00306 -0.1654 0.8348 0.1025
-2.750 0.4006 0.00895 0.00292 -0.1652 0.8285 0.1108
-2.500 0.4282 0.00883 0.00279 -0.1651 0.8214 0.1187
-2.250 0.4562 0.00872 0.00264 -0.1649 0.8147 0.1253
-2.000 0.4837 0.00858 0.00250 -0.1648 0.8067 0.1325
-1.750 0.5116 0.00851 0.00237 -0.1646 0.7994 0.1379
-1.500 0.5391 0.00837 0.00226 -0.1645 0.7913 0.1469
-1.250 0.5668 0.00828 0.00217 -0.1644 0.7837 0.1589
-1.000 0.5944 0.00817 0.00210 -0.1642 0.7754 0.1771
-0.750 0.6219 0.00803 0.00207 -0.1641 0.7671 0.2187
-0.500 0.6493 0.00793 0.00207 -0.1640 0.7587 0.2768
-0.250 0.6765 0.00790 0.00209 -0.1637 0.7496 0.3120
0.000 0.7039 0.00789 0.00210 -0.1635 0.7415 0.3403
0.250 0.7309 0.00787 0.00214 -0.1633 0.7325 0.3674
0.500 0.7581 0.00788 0.00218 -0.1631 0.7244 0.3969
0.750 0.7850 0.00788 0.00224 -0.1628 0.7155 0.4317
1.000 0.8118 0.00788 0.00232 -0.1625 0.7068 0.4733
1.250 0.8383 0.00788 0.00240 -0.1622 0.6977 0.5209
1.500 0.8646 0.00786 0.00250 -0.1618 0.6882 0.5739
1.750 0.8906 0.00784 0.00260 -0.1614 0.6794 0.6384
2.000 0.9137 0.00757 0.00271 -0.1603 0.6697 0.7652
2.250 0.9430 0.00737 0.00274 -0.1604 0.6603 1.0000
2.500 0.9693 0.00753 0.00282 -0.1600 0.6503 1.0000
2.750 0.9954 0.00765 0.00291 -0.1596 0.6386 1.0000
3.000 1.0212 0.00779 0.00301 -0.1591 0.6262 1.0000
3.250 1.0466 0.00795 0.00312 -0.1585 0.6132 1.0000
3.500 1.0714 0.00813 0.00324 -0.1578 0.5976 1.0000
3.750 1.0958 0.00833 0.00337 -0.1571 0.5809 1.0000
4.000 1.1199 0.00854 0.00351 -0.1563 0.5638 1.0000
4.250 1.1432 0.00879 0.00368 -0.1554 0.5449 1.0000
4.500 1.1666 0.00905 0.00387 -0.1545 0.5276 1.0000
4.750 1.1899 0.00931 0.00406 -0.1536 0.5109 1.0000
5.000 1.2130 0.00958 0.00429 -0.1527 0.4934 1.0000
5.250 1.2356 0.00988 0.00452 -0.1517 0.4760 1.0000
5.500 1.2577 0.01019 0.00477 -0.1506 0.4582 1.0000
5.750 1.2797 0.01051 0.00504 -0.1495 0.4417 1.0000
6.000 1.3017 0.01083 0.00533 -0.1485 0.4260 1.0000
6.250 1.3219 0.01123 0.00564 -0.1471 0.4057 1.0000
6.500 1.3421 0.01161 0.00596 -0.1457 0.3822 1.0000
6.750 1.3595 0.01212 0.00634 -0.1439 0.3475 1.0000
7.000 1.3676 0.01313 0.00696 -0.1405 0.2765 1.0000
7.250 1.3668 0.01458 0.00792 -0.1358 0.2012 1.0000
7.500 1.3631 0.01624 0.00906 -0.1307 0.1210 1.0000
7.750 1.3616 0.01781 0.01025 -0.1262 0.0649 1.0000
8.000 1.3706 0.01879 0.01114 -0.1233 0.0514 1.0000
8.250 1.3841 0.01951 0.01190 -0.1211 0.0470 1.0000
8.500 1.3937 0.02050 0.01289 -0.1185 0.0425 1.0000
8.750 1.4071 0.02126 0.01372 -0.1164 0.0403 1.0000
9.000 1.4195 0.02209 0.01460 -0.1143 0.0380 1.0000
9.250 1.4286 0.02316 0.01571 -0.1119 0.0357 1.0000
9.500 1.4329 0.02460 0.01721 -0.1090 0.0335 1.0000
9.750 1.4459 0.02546 0.01815 -0.1072 0.0321 1.0000
10.000 1.4560 0.02656 0.01931 -0.1052 0.0305 1.0000
10.250 1.4642 0.02783 0.02062 -0.1031 0.0291 1.0000
10.500 1.4655 0.02968 0.02253 -0.1004 0.0276 1.0000
10.750 1.4682 0.03152 0.02445 -0.0980 0.0266 1.0000
11.000 1.4793 0.03270 0.02572 -0.0965 0.0255 1.0000
11.250 1.4883 0.03410 0.02719 -0.0949 0.0244 1.0000
11.500 1.4962 0.03563 0.02877 -0.0934 0.0233 1.0000
11.750 1.5008 0.03751 0.03070 -0.0918 0.0225 1.0000
12.000 1.4954 0.04046 0.03372 -0.0895 0.0216 1.0000
12.250 1.5020 0.04232 0.03568 -0.0882 0.0211 1.0000
12.500 1.5092 0.04416 0.03761 -0.0871 0.0204 1.0000
12.750 1.5155 0.04614 0.03969 -0.0860 0.0197 1.0000
13.000 1.5220 0.04816 0.04179 -0.0851 0.0191 1.0000
13.250 1.5279 0.05027 0.04396 -0.0843 0.0184 1.0000
13.500 1.5325 0.05259 0.04632 -0.0836 0.0179 1.0000
13.750 1.5320 0.05558 0.04937 -0.0826 0.0173 1.0000
14.000 1.5344 0.05833 0.05223 -0.0817 0.0168 1.0000
14.250 1.5397 0.06078 0.05479 -0.0813 0.0165 1.0000
14.500 1.5441 0.06337 0.05750 -0.0808 0.0160 1.0000
14.750 1.5479 0.06609 0.06034 -0.0804 0.0156 1.0000
15.000 1.5512 0.06892 0.06328 -0.0802 0.0152 1.0000
15.250 1.5542 0.07185 0.06630 -0.0801 0.0149 1.0000
15.500 1.5568 0.07487 0.06941 -0.0802 0.0145 1.0000
15.750 1.5587 0.07802 0.07263 -0.0804 0.0142 1.0000
16.000 1.5600 0.08130 0.07598 -0.0806 0.0139 1.0000
16.250 1.5595 0.08486 0.07964 -0.0802 0.0135 1.0000
16.500 1.5580 0.08876 0.08371 -0.0808 0.0133 1.0000
16.750 1.5562 0.09275 0.08787 -0.0817 0.0131 1.0000
17.000 1.5538 0.09692 0.09221 -0.0827 0.0128 1.0000
17.250 1.5506 0.10128 0.09673 -0.0839 0.0126 1.0000
17.500 1.5467 0.10585 0.10145 -0.0853 0.0123 1.0000
17.750 1.5420 0.11060 0.10637 -0.0869 0.0122 1.0000
18.000 1.5365 0.11555 0.11147 -0.0888 0.0120 1.0000
18.250 1.5308 0.12062 0.11669 -0.0909 0.0118 1.0000
18.500 1.5237 0.12603 0.12225 -0.0934 0.0117 1.0000
18.750 1.5161 0.13164 0.12802 -0.0962 0.0115 1.0000
19.000 1.5077 0.13750 0.13404 -0.0993 0.0114 1.0000
19.250 1.4985 0.14365 0.14033 -0.1027 0.0113 1.0000
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