GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 431 AIRFOIL (goe431-il) Reynolds number: 50,000 Max Cl/Cd: 39.51 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe431-il-50000-n5.txt Download as CSV file: xf-goe431-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 431 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2554 0.10809 0.10174 -0.0545 0.9540 0.0578
-7.500 -0.2564 0.10513 0.09881 -0.0556 0.9512 0.0580
-7.250 -0.2649 0.10276 0.09650 -0.0546 0.9473 0.0581
-7.000 -0.2731 0.10026 0.09405 -0.0539 0.9431 0.0581
-6.750 -0.2761 0.09694 0.09077 -0.0550 0.9398 0.0582
-6.500 -0.2756 0.09305 0.08691 -0.0574 0.9371 0.0583
-6.250 -0.2777 0.08905 0.08296 -0.0595 0.9340 0.0588
-6.000 -0.2799 0.08455 0.07849 -0.0622 0.9300 0.0596
-5.750 -0.2742 0.07705 0.07098 -0.0702 0.9265 0.0610
-5.500 -0.2567 0.07080 0.06470 -0.0783 0.9243 0.0638
-5.250 -0.1653 0.04757 0.04046 -0.1213 0.9245 0.0752
-5.000 -0.1649 0.05293 0.04630 -0.1105 0.9219 0.0788
-4.500 -0.0858 0.04848 0.04130 -0.1231 0.9183 0.1101
-4.000 -0.0222 0.04707 0.03929 -0.1290 0.9142 0.1519
-3.500 0.0330 0.04697 0.03877 -0.1308 0.9091 0.1866
-3.250 0.0642 0.04672 0.03825 -0.1325 0.9071 0.2021
-3.000 0.0939 0.04676 0.03808 -0.1337 0.9047 0.2170
-2.750 0.1165 0.04654 0.03766 -0.1341 0.9003 0.2304
-2.500 0.1510 0.04623 0.03717 -0.1356 0.8931 0.2396
-2.250 0.1978 0.04470 0.03512 -0.1405 0.8829 0.2454
-2.000 0.2428 0.04388 0.03408 -0.1436 0.8726 0.2499
-1.750 0.2887 0.04268 0.03254 -0.1472 0.8618 0.2530
-1.500 0.3245 0.04177 0.03132 -0.1491 0.8512 0.2552
-1.250 0.3737 0.04080 0.02992 -0.1532 0.8452 0.2590
-1.000 0.3959 0.04058 0.02963 -0.1526 0.8361 0.2617
-0.750 0.4368 0.04004 0.02894 -0.1548 0.8304 0.2653
-0.500 0.4606 0.03983 0.02862 -0.1545 0.8212 0.2678
-0.250 0.5023 0.03923 0.02781 -0.1568 0.8152 0.2710
0.000 0.5277 0.03906 0.02747 -0.1566 0.8054 0.2740
0.250 0.5687 0.03849 0.02679 -0.1585 0.7993 0.2776
0.500 0.5913 0.03842 0.02668 -0.1576 0.7882 0.2813
0.750 0.6351 0.03773 0.02584 -0.1596 0.7824 0.2891
1.000 0.6561 0.03766 0.02578 -0.1584 0.7698 0.2946
1.250 0.6813 0.03745 0.02556 -0.1577 0.7580 0.3013
1.500 0.7225 0.03662 0.02470 -0.1591 0.7511 0.3103
1.750 0.7448 0.03641 0.02452 -0.1579 0.7370 0.3186
2.000 0.7683 0.03612 0.02430 -0.1568 0.7224 0.3285
2.250 0.7922 0.03581 0.02406 -0.1557 0.7072 0.3419
2.500 0.8160 0.03547 0.02386 -0.1546 0.6911 0.3605
3.000 0.8526 0.03538 0.02412 -0.1512 0.6483 0.4121
3.250 0.8779 0.03495 0.02389 -0.1502 0.6296 0.4552
3.500 0.9015 0.03473 0.02383 -0.1491 0.6081 0.5078
3.750 0.9336 0.03391 0.02313 -0.1487 0.5925 0.5799
4.000 0.9657 0.03250 0.02216 -0.1479 0.5793 0.7037
4.250 0.9988 0.03154 0.02104 -0.1475 0.5660 1.0000
4.750 1.0746 0.03070 0.01972 -0.1487 0.5410 1.0000
5.000 1.1078 0.03076 0.01959 -0.1491 0.5289 1.0000
5.250 1.1416 0.03091 0.01957 -0.1496 0.5185 1.0000
5.500 1.1739 0.03122 0.01976 -0.1500 0.5088 1.0000
5.750 1.2036 0.03172 0.02021 -0.1503 0.5003 1.0000
6.000 1.2366 0.03217 0.02063 -0.1510 0.4930 1.0000
6.250 1.2678 0.03274 0.02121 -0.1516 0.4865 1.0000
6.500 1.2963 0.03342 0.02194 -0.1519 0.4797 1.0000
7.000 1.3572 0.03479 0.02349 -0.1531 0.4677 1.0000
7.250 1.3876 0.03553 0.02434 -0.1537 0.4623 1.0000
7.500 1.4280 0.03614 0.02505 -0.1558 0.4580 1.0000
7.750 1.4446 0.03727 0.02640 -0.1545 0.4527 1.0000
8.000 1.4680 0.03820 0.02748 -0.1541 0.4464 1.0000
8.250 1.4972 0.03899 0.02836 -0.1544 0.4395 1.0000
8.500 1.5077 0.04018 0.02980 -0.1521 0.4321 1.0000
8.750 1.5372 0.04086 0.03054 -0.1523 0.4240 1.0000
9.000 1.5407 0.04217 0.03210 -0.1490 0.4161 1.0000
9.250 1.5724 0.04280 0.03281 -0.1495 0.4086 1.0000
9.500 1.5705 0.04443 0.03474 -0.1457 0.4023 1.0000
9.750 1.5937 0.04534 0.03587 -0.1451 0.3958 1.0000
10.000 1.6023 0.04675 0.03752 -0.1428 0.3895 1.0000
10.250 1.6063 0.04832 0.03935 -0.1399 0.3829 1.0000
10.500 1.6342 0.04902 0.04023 -0.1398 0.3761 1.0000
10.750 1.6179 0.05149 0.04302 -0.1349 0.3696 1.0000
11.000 1.6521 0.05156 0.04323 -0.1351 0.3608 1.0000
11.250 1.6224 0.05490 0.04691 -0.1293 0.3544 1.0000
11.500 1.6314 0.05542 0.04753 -0.1267 0.3422 1.0000
12.000 1.5981 0.06050 0.05305 -0.1188 0.3209 1.0000
12.250 1.5863 0.06253 0.05518 -0.1155 0.3076 1.0000
12.500 1.5727 0.06497 0.05773 -0.1125 0.2942 1.0000
12.750 1.5431 0.07042 0.06346 -0.1103 0.2858 1.0000
13.000 1.5189 0.07547 0.06871 -0.1089 0.2756 1.0000
13.250 1.4981 0.08039 0.07377 -0.1080 0.2638 1.0000
13.500 1.4547 0.09056 0.08420 -0.1093 0.2587 1.0000
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Polar data table (+)
Polar graphs
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