GOE 498 AIRFOIL (goe498-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 498 AIRFOIL (goe498-il) Reynolds number: 100,000 Max Cl/Cd: 49.67 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe498-il-100000.txt Download as CSV file: xf-goe498-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 498 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2738 0.11129 0.10648 -0.0412 0.9822 0.1720
-8.500 -0.2455 0.10805 0.10321 -0.0433 0.9764 0.1762
-8.250 -0.2688 0.10591 0.10110 -0.0527 0.9657 0.1849
-8.000 -0.2516 0.10110 0.09629 -0.0549 0.9588 0.1866
-7.750 -0.3620 0.07248 0.06751 -0.0806 0.9403 0.1272
-7.500 -0.3609 0.06660 0.06157 -0.0845 0.9303 0.1262
-7.250 -0.3727 0.05036 0.04456 -0.1015 0.9220 0.1235
-7.000 -0.3701 0.04424 0.03777 -0.1048 0.9111 0.1245
-6.750 -0.3383 0.03958 0.03229 -0.1101 0.9061 0.1282
-6.500 -0.3141 0.03905 0.03191 -0.1098 0.8985 0.1315
-6.250 -0.2851 0.03749 0.03010 -0.1112 0.8912 0.1356
-6.000 -0.2445 0.03525 0.02731 -0.1148 0.8870 0.1414
-5.750 -0.2259 0.03478 0.02692 -0.1137 0.8780 0.1453
-5.500 -0.1923 0.03374 0.02563 -0.1152 0.8717 0.1516
-5.250 -0.1499 0.03254 0.02434 -0.1179 0.8680 0.1588
-5.000 -0.1333 0.03222 0.02392 -0.1164 0.8580 0.1644
-4.750 -0.0978 0.03127 0.02284 -0.1179 0.8524 0.1726
-4.500 -0.0537 0.03047 0.02191 -0.1206 0.8490 0.1838
-4.000 -0.0028 0.02961 0.02107 -0.1200 0.8331 0.2045
-3.750 0.0426 0.02888 0.02042 -0.1226 0.8301 0.2232
-3.500 0.0529 0.02915 0.02064 -0.1199 0.8188 0.2378
-3.250 0.0918 0.02876 0.02041 -0.1214 0.8141 0.2606
-3.000 0.1394 0.02826 0.01997 -0.1240 0.8115 0.2865
-2.750 0.1460 0.02877 0.02047 -0.1208 0.7993 0.2992
-2.500 0.1883 0.02831 0.02003 -0.1226 0.7954 0.3201
-2.250 0.2383 0.02763 0.01938 -0.1256 0.7930 0.3422
-1.750 0.2903 0.02759 0.01929 -0.1245 0.7771 0.3777
-1.500 0.3404 0.02682 0.01864 -0.1272 0.7744 0.4025
-1.250 0.3505 0.02729 0.01911 -0.1243 0.7628 0.4177
-1.000 0.3954 0.02658 0.01841 -0.1262 0.7585 0.4408
-0.750 0.4442 0.02570 0.01755 -0.1287 0.7553 0.4633
-0.500 0.4550 0.02615 0.01811 -0.1258 0.7442 0.4757
-0.250 0.4958 0.02557 0.01753 -0.1272 0.7392 0.4956
0.000 0.5431 0.02482 0.01678 -0.1295 0.7357 0.5176
0.250 0.5525 0.02541 0.01742 -0.1265 0.7245 0.5318
0.500 0.5920 0.02492 0.01694 -0.1277 0.7191 0.5534
0.750 0.6394 0.02419 0.01620 -0.1301 0.7154 0.5781
1.000 0.6443 0.02490 0.01700 -0.1264 0.7033 0.5943
1.250 0.6852 0.02432 0.01643 -0.1278 0.6981 0.6237
1.500 0.7058 0.02447 0.01669 -0.1262 0.6898 0.6496
1.750 0.7290 0.02444 0.01676 -0.1250 0.6815 0.6800
2.000 0.7724 0.02373 0.01609 -0.1266 0.6767 0.7213
2.250 0.7791 0.02421 0.01679 -0.1230 0.6655 0.7584
2.500 0.8135 0.02337 0.01622 -0.1228 0.6592 0.8446
2.750 0.8544 0.02337 0.01621 -0.1256 0.6494 1.0000
3.000 0.8905 0.02330 0.01595 -0.1268 0.6407 1.0000
3.250 0.9218 0.02339 0.01590 -0.1272 0.6323 1.0000
3.500 0.9472 0.02357 0.01600 -0.1266 0.6224 1.0000
3.750 0.9846 0.02345 0.01573 -0.1278 0.6151 1.0000
4.000 1.0007 0.02394 0.01621 -0.1258 0.6044 1.0000
4.250 1.0454 0.02359 0.01568 -0.1280 0.5981 1.0000
4.500 1.0529 0.02435 0.01651 -0.1247 0.5866 1.0000
4.750 1.0949 0.02405 0.01604 -0.1265 0.5798 1.0000
5.000 1.1044 0.02477 0.01683 -0.1235 0.5689 1.0000
5.250 1.1431 0.02458 0.01650 -0.1248 0.5617 1.0000
5.500 1.1551 0.02524 0.01723 -0.1222 0.5514 1.0000
5.750 1.1901 0.02516 0.01704 -0.1230 0.5436 1.0000
6.000 1.2050 0.02575 0.01768 -0.1208 0.5340 1.0000
6.250 1.2357 0.02579 0.01764 -0.1209 0.5257 1.0000
6.500 1.2541 0.02631 0.01819 -0.1193 0.5167 1.0000
6.750 1.2781 0.02660 0.01847 -0.1185 0.5084 1.0000
7.000 1.3048 0.02694 0.01878 -0.1182 0.5006 1.0000
7.250 1.3189 0.02753 0.01944 -0.1160 0.4917 1.0000
7.500 1.3564 0.02755 0.01934 -0.1172 0.4843 1.0000
7.750 1.3597 0.02840 0.02035 -0.1134 0.4748 1.0000
8.000 1.4019 0.02823 0.02002 -0.1153 0.4668 1.0000
8.250 1.3992 0.02918 0.02117 -0.1106 0.4571 1.0000
8.500 1.4408 0.02901 0.02083 -0.1123 0.4484 1.0000
8.750 1.4359 0.02999 0.02201 -0.1073 0.4387 1.0000
9.000 1.4727 0.02993 0.02183 -0.1084 0.4293 1.0000
9.250 1.4696 0.03075 0.02280 -0.1036 0.4189 1.0000
9.500 1.4897 0.03096 0.02296 -0.1021 0.4081 1.0000
9.750 1.5059 0.03117 0.02311 -0.1000 0.3965 1.0000
10.000 1.5032 0.03197 0.02400 -0.0954 0.3854 1.0000
10.250 1.5210 0.03224 0.02417 -0.0936 0.3733 1.0000
10.500 1.5293 0.03275 0.02465 -0.0907 0.3611 1.0000
10.750 1.5264 0.03379 0.02575 -0.0866 0.3496 1.0000
11.000 1.5403 0.03437 0.02624 -0.0847 0.3380 1.0000
11.250 1.5436 0.03533 0.02720 -0.0816 0.3271 1.0000
11.500 1.5441 0.03654 0.02846 -0.0785 0.3168 1.0000
11.750 1.5631 0.03702 0.02876 -0.0774 0.3061 1.0000
12.000 1.5499 0.03890 0.03086 -0.0733 0.2975 1.0000
12.250 1.5667 0.03957 0.03140 -0.0721 0.2883 1.0000
12.500 1.5558 0.04161 0.03365 -0.0687 0.2804 1.0000
12.750 1.5714 0.04232 0.03422 -0.0676 0.2719 1.0000
13.000 1.5584 0.04472 0.03686 -0.0645 0.2646 1.0000
13.250 1.5705 0.04559 0.03763 -0.0633 0.2564 1.0000
13.500 1.5575 0.04830 0.04057 -0.0608 0.2493 1.0000
13.750 1.5634 0.04964 0.04185 -0.0594 0.2412 1.0000
14.000 1.5526 0.05249 0.04488 -0.0576 0.2338 1.0000
14.250 1.5575 0.05399 0.04629 -0.0564 0.2251 1.0000
14.500 1.5429 0.05747 0.04997 -0.0551 0.2172 1.0000
14.750 1.5450 0.05941 0.05181 -0.0541 0.2079 1.0000
15.000 1.5325 0.06300 0.05553 -0.0533 0.1988 1.0000
15.250 1.5268 0.06609 0.05861 -0.0526 0.1888 1.0000
15.500 1.5281 0.06850 0.06088 -0.0519 0.1776 1.0000
15.750 1.5285 0.07116 0.06342 -0.0513 0.1665 1.0000
16.000 1.5156 0.07554 0.06794 -0.0512 0.1575 1.0000
16.250 1.5187 0.07813 0.07044 -0.0508 0.1485 1.0000
16.500 1.5136 0.08171 0.07408 -0.0509 0.1412 1.0000
16.750 1.5120 0.08501 0.07744 -0.0510 0.1350 1.0000
17.000 1.5038 0.08916 0.08173 -0.0515 0.1297 1.0000
17.250 1.5137 0.09096 0.08343 -0.0513 0.1245 1.0000
17.500 1.4957 0.09665 0.08942 -0.0527 0.1209 1.0000
17.750 1.4959 0.09981 0.09263 -0.0533 0.1169 1.0000
18.000 1.5076 0.10142 0.09416 -0.0532 0.1133 1.0000
18.250 1.4876 0.10776 0.10082 -0.0553 0.1110 1.0000
18.500 1.4738 0.11332 0.10658 -0.0573 0.1086 1.0000
18.750 1.4797 0.11572 0.10900 -0.0578 0.1058 1.0000
19.000 1.4945 0.11680 0.11000 -0.0576 0.1031 1.0000
19.250 1.4616 0.12565 0.11920 -0.0618 0.1021 1.0000
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