GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 494 AIRFOIL (goe494-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.28 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe494-il-1000000-n5.txt Download as CSV file: xf-goe494-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 494 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2947 0.08724 0.08562 -0.0479 0.9857 0.0032
-8.000 -0.2842 0.08314 0.08153 -0.0514 0.9798 0.0033
-7.750 -0.2737 0.07795 0.07634 -0.0563 0.9724 0.0035
-7.500 -0.2531 0.07311 0.07150 -0.0634 0.9673 0.0037
-7.250 -0.2278 0.06798 0.06635 -0.0719 0.9613 0.0039
-7.000 -0.1967 0.06230 0.06063 -0.0823 0.9551 0.0042
-6.750 -0.1653 0.05492 0.05320 -0.0950 0.9438 0.0049
-6.500 -0.1294 0.04303 0.04116 -0.1145 0.9277 0.0055
-6.250 -0.0751 0.01140 0.00737 -0.1477 0.9126 0.0059
-5.750 -0.0204 0.00964 0.00524 -0.1482 0.9014 0.0081
-5.500 0.0072 0.00929 0.00480 -0.1482 0.8961 0.0100
-5.250 0.0349 0.01020 0.00588 -0.1479 0.8901 0.0117
-5.000 0.0623 0.00992 0.00551 -0.1479 0.8843 0.0144
-4.750 0.0898 0.01016 0.00573 -0.1477 0.8775 0.0171
-4.500 0.1171 0.01018 0.00567 -0.1475 0.8706 0.0195
-4.250 0.1444 0.01033 0.00577 -0.1474 0.8629 0.0214
-4.000 0.1716 0.01049 0.00588 -0.1472 0.8553 0.0224
-3.500 0.2258 0.01010 0.00525 -0.1470 0.8340 0.0244
-3.250 0.2525 0.00942 0.00446 -0.1471 0.8206 0.0260
-3.000 0.2793 0.00916 0.00410 -0.1469 0.8061 0.0270
-2.750 0.3062 0.00882 0.00364 -0.1467 0.7927 0.0273
-2.500 0.3331 0.00849 0.00318 -0.1465 0.7804 0.0274
-2.250 0.3601 0.00825 0.00286 -0.1464 0.7695 0.0279
-2.000 0.3871 0.00796 0.00247 -0.1462 0.7597 0.0276
-1.750 0.4146 0.00767 0.00210 -0.1461 0.7519 0.0270
-1.500 0.4419 0.00745 0.00180 -0.1460 0.7458 0.0265
-1.250 0.4696 0.00727 0.00158 -0.1459 0.7405 0.0261
-1.000 0.4972 0.00713 0.00140 -0.1459 0.7354 0.0257
-0.750 0.5247 0.00702 0.00126 -0.1458 0.7312 0.0254
-0.500 0.5524 0.00692 0.00114 -0.1457 0.7269 0.0252
-0.250 0.5799 0.00685 0.00104 -0.1456 0.7210 0.0250
0.000 0.6072 0.00679 0.00097 -0.1455 0.7144 0.0248
0.250 0.6346 0.00674 0.00090 -0.1454 0.7075 0.0247
0.500 0.6618 0.00671 0.00084 -0.1452 0.7005 0.0247
0.750 0.6889 0.00669 0.00080 -0.1450 0.6906 0.0249
1.000 0.7154 0.00672 0.00076 -0.1447 0.6739 0.0255
1.250 0.7419 0.00675 0.00074 -0.1443 0.6513 0.0286
1.500 0.7680 0.00684 0.00078 -0.1439 0.6249 0.0331
1.750 0.7920 0.00712 0.00087 -0.1431 0.5696 0.0423
2.000 0.8156 0.00729 0.00108 -0.1425 0.5136 0.1823
2.250 0.8393 0.00762 0.00131 -0.1419 0.4565 0.2424
2.500 0.8589 0.00844 0.00172 -0.1406 0.3298 0.3085
2.750 0.8798 0.00916 0.00216 -0.1397 0.2286 0.3766
3.000 0.9022 0.00960 0.00255 -0.1390 0.1552 0.4979
3.500 0.9450 0.00996 0.00334 -0.1369 0.0366 1.0000
3.750 0.9703 0.01023 0.00360 -0.1364 0.0271 1.0000
4.000 0.9953 0.01055 0.00387 -0.1359 0.0170 1.0000
4.250 1.0204 0.01085 0.00416 -0.1354 0.0115 1.0000
4.500 1.0454 0.01115 0.00446 -0.1349 0.0095 1.0000
4.750 1.0696 0.01156 0.00487 -0.1342 0.0071 1.0000
5.000 1.0944 0.01188 0.00524 -0.1336 0.0064 1.0000
5.250 1.1187 0.01225 0.00564 -0.1330 0.0057 1.0000
5.500 1.1426 0.01268 0.00608 -0.1323 0.0050 1.0000
5.750 1.1648 0.01334 0.00682 -0.1313 0.0044 1.0000
6.000 1.1884 0.01378 0.00730 -0.1305 0.0041 1.0000
6.250 1.2117 0.01424 0.00783 -0.1297 0.0037 1.0000
6.500 1.2347 0.01473 0.00836 -0.1289 0.0034 1.0000
6.750 1.2571 0.01528 0.00895 -0.1280 0.0031 1.0000
7.000 1.2788 0.01592 0.00964 -0.1270 0.0029 1.0000
7.250 1.2971 0.01704 0.01088 -0.1254 0.0026 1.0000
7.500 1.3177 0.01785 0.01178 -0.1242 0.0026 1.0000
7.750 1.3380 0.01868 0.01271 -0.1230 0.0024 1.0000
8.000 1.3574 0.01968 0.01384 -0.1216 0.0023 1.0000
8.250 1.3761 0.02086 0.01519 -0.1201 0.0022 1.0000
8.500 1.3942 0.02221 0.01670 -0.1185 0.0020 1.0000
8.750 1.4119 0.02374 0.01842 -0.1169 0.0019 1.0000
9.000 1.4286 0.02555 0.02044 -0.1152 0.0018 1.0000
9.250 1.4438 0.02780 0.02296 -0.1133 0.0018 1.0000
9.500 1.4579 0.03005 0.02547 -0.1114 0.0017 1.0000
9.750 1.4717 0.03190 0.02753 -0.1095 0.0016 1.0000
10.000 1.4841 0.03367 0.02949 -0.1075 0.0016 1.0000
10.250 1.4929 0.03595 0.03200 -0.1050 0.0015 1.0000
10.500 1.4854 0.04151 0.03806 -0.1006 0.0015 1.0000
10.750 1.4117 0.05654 0.05395 -0.0887 0.0014 1.0000
11.000 1.3854 0.06128 0.05892 -0.0841 0.0014 1.0000
11.250 1.3583 0.06653 0.06438 -0.0811 0.0014 1.0000
11.500 1.3335 0.07200 0.07004 -0.0797 0.0014 1.0000
11.750 1.3084 0.07818 0.07638 -0.0799 0.0014 1.0000
12.000 1.2825 0.08527 0.08362 -0.0818 0.0015 1.0000
12.250 1.2515 0.09449 0.09301 -0.0859 0.0015 1.0000
12.500 1.2088 0.10944 0.10815 -0.0954 0.0015 1.0000
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Polar data table (+)
Polar graphs
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