GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 447 AIRFOIL (goe447-il) Reynolds number: 200,000 Max Cl/Cd: 84.2 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe447-il-200000-n5.txt Download as CSV file: xf-goe447-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 447 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
------ -------- --------- --------- -------- -------- --------
-9.250 0.0691 0.09463 0.08995 -0.1120 0.8120 0.0435
-9.000 0.0774 0.09219 0.08751 -0.1133 0.8068 0.0446
-8.750 0.0831 0.08969 0.08499 -0.1155 0.8019 0.0458
-8.500 0.0868 0.08719 0.08245 -0.1183 0.7976 0.0462
-8.000 0.0961 0.08188 0.07715 -0.1238 0.7880 0.0464
-7.750 0.1135 0.07924 0.07449 -0.1221 0.7847 0.0469
-7.500 0.1271 0.07720 0.07241 -0.1221 0.7812 0.0478
-7.250 0.1375 0.07515 0.07035 -0.1230 0.7774 0.0488
-7.000 0.1452 0.07308 0.06830 -0.1244 0.7727 0.0498
-6.750 0.1566 0.07054 0.06576 -0.1271 0.7683 0.0506
-6.250 0.1821 0.06109 0.05614 -0.1396 0.7613 0.0403
-6.000 0.1986 0.05877 0.05382 -0.1414 0.7573 0.0398
-5.750 0.2177 0.05564 0.05065 -0.1454 0.7534 0.0397
-5.500 0.2402 0.05181 0.04673 -0.1507 0.7500 0.0399
-5.250 0.2635 0.04860 0.04341 -0.1546 0.7469 0.0396
-5.000 0.2884 0.04518 0.03987 -0.1588 0.7438 0.0392
-4.750 0.3142 0.04132 0.03590 -0.1631 0.7398 0.0388
-4.500 0.3428 0.03668 0.03104 -0.1680 0.7362 0.0387
-4.250 0.3754 0.02373 0.01682 -0.1771 0.7333 0.0401
-4.000 0.4025 0.02060 0.01298 -0.1783 0.7303 0.0409
-3.750 0.4299 0.01988 0.01209 -0.1785 0.7269 0.0415
-3.500 0.4556 0.01925 0.01135 -0.1784 0.7222 0.0422
-3.250 0.4825 0.01859 0.01052 -0.1784 0.7177 0.0430
-3.000 0.5105 0.01790 0.00961 -0.1786 0.7140 0.0442
-2.750 0.5387 0.01723 0.00872 -0.1787 0.7107 0.0456
-2.500 0.5645 0.01693 0.00838 -0.1784 0.7059 0.0472
-2.250 0.5913 0.01683 0.00825 -0.1783 0.7013 0.0491
-2.000 0.6194 0.01647 0.00777 -0.1783 0.6974 0.0517
-1.750 0.6472 0.01624 0.00748 -0.1784 0.6938 0.0540
-1.500 0.6732 0.01613 0.00737 -0.1781 0.6895 0.0571
-1.250 0.7001 0.01597 0.00717 -0.1779 0.6855 0.0614
-1.000 0.7278 0.01587 0.00697 -0.1779 0.6821 0.0677
-0.750 0.7563 0.01583 0.00690 -0.1781 0.6793 0.0734
-0.500 0.7823 0.01577 0.00682 -0.1778 0.6754 0.0789
-0.250 0.8081 0.01571 0.00679 -0.1775 0.6711 0.0836
0.000 0.8349 0.01565 0.00668 -0.1774 0.6671 0.0890
0.250 0.8627 0.01555 0.00660 -0.1775 0.6636 0.0965
0.500 0.8889 0.01552 0.00656 -0.1773 0.6595 0.1020
0.750 0.9140 0.01543 0.00653 -0.1769 0.6548 0.1056
1.000 0.9404 0.01537 0.00648 -0.1767 0.6507 0.1082
1.250 0.9681 0.01532 0.00639 -0.1768 0.6471 0.1110
1.500 0.9937 0.01535 0.00643 -0.1764 0.6428 0.1143
1.750 1.0185 0.01537 0.00650 -0.1759 0.6377 0.1183
2.000 1.0446 0.01536 0.00650 -0.1757 0.6331 0.1234
2.250 1.0721 0.01535 0.00646 -0.1757 0.6289 0.1307
2.750 1.1199 0.01530 0.00683 -0.1746 0.6173 0.2539
3.000 1.1456 0.01520 0.00691 -0.1743 0.6121 0.3527
3.500 1.1894 0.01445 0.00718 -0.1720 0.5984 1.0000
3.750 1.2117 0.01463 0.00734 -0.1710 0.5910 1.0000
4.000 1.2345 0.01480 0.00746 -0.1702 0.5835 1.0000
4.250 1.2564 0.01500 0.00762 -0.1691 0.5757 1.0000
4.500 1.2775 0.01520 0.00777 -0.1679 0.5667 1.0000
4.750 1.2978 0.01543 0.00799 -0.1666 0.5578 1.0000
5.000 1.3185 0.01566 0.00817 -0.1654 0.5496 1.0000
5.250 1.3380 0.01593 0.00844 -0.1640 0.5412 1.0000
5.500 1.3564 0.01619 0.00866 -0.1624 0.5325 1.0000
5.750 1.3725 0.01651 0.00898 -0.1604 0.5228 1.0000
6.000 1.3894 0.01685 0.00927 -0.1585 0.5136 1.0000
6.250 1.4056 0.01724 0.00964 -0.1566 0.5040 1.0000
6.500 1.4218 0.01766 0.01004 -0.1548 0.4950 1.0000
6.750 1.4375 0.01811 0.01046 -0.1529 0.4862 1.0000
7.000 1.4531 0.01860 0.01094 -0.1511 0.4776 1.0000
7.250 1.4680 0.01914 0.01143 -0.1491 0.4691 1.0000
7.500 1.4824 0.01971 0.01202 -0.1472 0.4603 1.0000
8.000 1.5109 0.02097 0.01325 -0.1435 0.4444 1.0000
8.250 1.5256 0.02162 0.01389 -0.1418 0.4378 1.0000
8.500 1.5404 0.02228 0.01459 -0.1402 0.4314 1.0000
8.750 1.5540 0.02302 0.01535 -0.1385 0.4242 1.0000
9.000 1.5674 0.02378 0.01611 -0.1367 0.4175 1.0000
9.250 1.5803 0.02459 0.01699 -0.1350 0.4104 1.0000
9.500 1.5927 0.02545 0.01786 -0.1333 0.4036 1.0000
9.750 1.6048 0.02633 0.01882 -0.1316 0.3967 1.0000
10.000 1.6148 0.02736 0.01988 -0.1297 0.3885 1.0000
10.250 1.6235 0.02849 0.02106 -0.1277 0.3792 1.0000
10.500 1.6289 0.02984 0.02241 -0.1255 0.3683 1.0000
10.750 1.6340 0.03128 0.02393 -0.1233 0.3552 1.0000
11.000 1.6368 0.03293 0.02560 -0.1211 0.3401 1.0000
11.250 1.6376 0.03479 0.02745 -0.1187 0.3229 1.0000
11.500 1.6354 0.03696 0.02958 -0.1163 0.3028 1.0000
11.750 1.6306 0.03945 0.03199 -0.1138 0.2807 1.0000
12.000 1.6235 0.04225 0.03471 -0.1113 0.2607 1.0000
12.250 1.6168 0.04512 0.03752 -0.1090 0.2434 1.0000
12.500 1.6113 0.04799 0.04034 -0.1069 0.2288 1.0000
12.750 1.6077 0.05077 0.04310 -0.1051 0.2166 1.0000
13.000 1.6073 0.05331 0.04565 -0.1036 0.2071 1.0000
13.250 1.6055 0.05602 0.04837 -0.1021 0.1989 1.0000
13.500 1.6059 0.05858 0.05097 -0.1008 0.1901 1.0000
13.750 1.6038 0.06146 0.05386 -0.0995 0.1816 1.0000
14.000 1.6019 0.06436 0.05680 -0.0984 0.1723 1.0000
14.250 1.6019 0.06710 0.05958 -0.0974 0.1642 1.0000
14.500 1.5991 0.07021 0.06272 -0.0964 0.1555 1.0000
14.750 1.5982 0.07315 0.06571 -0.0955 0.1432 1.0000
15.000 1.5911 0.07691 0.06943 -0.0947 0.1182 1.0000
15.250 1.5666 0.08282 0.07507 -0.0936 0.0849 1.0000
15.500 1.5515 0.08768 0.07985 -0.0929 0.0709 1.0000
15.750 1.5396 0.09223 0.08438 -0.0924 0.0504 1.0000
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