GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 648 AIRFOIL (goe648-il) Reynolds number: 100,000 Max Cl/Cd: 44.15 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe648-il-100000-n5.txt Download as CSV file: xf-goe648-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 648 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6800 0.05337 0.04759 -0.0645 1.0000 0.0490
-10.250 -0.6911 0.05199 0.04620 -0.0611 1.0000 0.0494
-10.000 -0.6759 0.05017 0.04430 -0.0623 0.9955 0.0503
-9.750 -0.6600 0.04711 0.04099 -0.0648 0.9880 0.0516
-9.500 -0.6476 0.04316 0.03657 -0.0672 0.9805 0.0531
-9.250 -0.6386 0.03914 0.03184 -0.0682 0.9717 0.0551
-9.000 -0.6102 0.03821 0.03094 -0.0694 0.9664 0.0565
-8.750 -0.5867 0.03675 0.02931 -0.0699 0.9594 0.0582
-8.500 -0.5599 0.03467 0.02686 -0.0713 0.9546 0.0604
-8.250 -0.5411 0.03300 0.02484 -0.0707 0.9460 0.0624
-8.000 -0.5094 0.03204 0.02386 -0.0721 0.9414 0.0645
-7.750 -0.4860 0.03088 0.02253 -0.0718 0.9340 0.0666
-7.500 -0.4585 0.02951 0.02081 -0.0722 0.9279 0.0694
-7.250 -0.4241 0.02849 0.01979 -0.0739 0.9241 0.0720
-7.000 -0.4029 0.02771 0.01894 -0.0729 0.9153 0.0746
-6.750 -0.3708 0.02665 0.01763 -0.0737 0.9103 0.0780
-6.500 -0.3348 0.02569 0.01669 -0.0755 0.9069 0.0816
-6.250 -0.3146 0.02507 0.01604 -0.0741 0.8971 0.0851
-6.000 -0.2803 0.02419 0.01501 -0.0752 0.8926 0.0896
-5.750 -0.2493 0.02348 0.01436 -0.0759 0.8870 0.0941
-5.500 -0.2230 0.02290 0.01369 -0.0755 0.8788 0.0993
-5.250 -0.1871 0.02216 0.01300 -0.0770 0.8742 0.1053
-5.000 -0.1608 0.02167 0.01244 -0.0765 0.8653 0.1117
-4.750 -0.1278 0.02101 0.01184 -0.0773 0.8579 0.1190
-4.500 -0.0975 0.02046 0.01125 -0.0774 0.8488 0.1276
-4.250 -0.0654 0.01987 0.01068 -0.0779 0.8395 0.1377
-4.000 -0.0375 0.01935 0.01020 -0.0775 0.8285 0.1488
-3.750 -0.0037 0.01875 0.00963 -0.0783 0.8193 0.1641
-3.500 0.0209 0.01831 0.00925 -0.0774 0.8062 0.1825
-3.250 0.0506 0.01780 0.00881 -0.0773 0.7946 0.2099
-3.000 0.0795 0.01734 0.00844 -0.0772 0.7823 0.2463
-2.750 0.1031 0.01701 0.00822 -0.0761 0.7688 0.2837
-2.500 0.1299 0.01665 0.00797 -0.0756 0.7572 0.3260
-2.250 0.1572 0.01629 0.00775 -0.0752 0.7452 0.3736
-2.000 0.1800 0.01604 0.00766 -0.0739 0.7312 0.4241
-1.750 0.2048 0.01581 0.00758 -0.0729 0.7179 0.4799
-1.500 0.2311 0.01561 0.00747 -0.0720 0.7048 0.5342
-1.250 0.2567 0.01542 0.00738 -0.0710 0.6909 0.5912
-1.000 0.2807 0.01528 0.00737 -0.0696 0.6755 0.6460
-0.750 0.3053 0.01518 0.00735 -0.0682 0.6601 0.6964
-0.500 0.3305 0.01512 0.00731 -0.0669 0.6444 0.7411
-0.250 0.3566 0.01509 0.00726 -0.0659 0.6286 0.7824
0.000 0.3853 0.01508 0.00722 -0.0653 0.6120 0.8226
0.250 0.4202 0.01512 0.00720 -0.0661 0.5935 0.8625
0.500 0.4644 0.01524 0.00721 -0.0688 0.5724 0.8993
0.750 0.5128 0.01541 0.00721 -0.0726 0.5498 0.9317
1.000 0.5586 0.01562 0.00722 -0.0761 0.5276 0.9619
1.250 0.6029 0.01586 0.00728 -0.0795 0.5041 0.9919
1.500 0.6249 0.01610 0.00732 -0.0786 0.4845 1.0000
1.750 0.6406 0.01632 0.00736 -0.0764 0.4668 1.0000
2.000 0.6575 0.01657 0.00744 -0.0744 0.4505 1.0000
2.250 0.6750 0.01685 0.00754 -0.0724 0.4359 1.0000
2.500 0.6933 0.01713 0.00768 -0.0706 0.4223 1.0000
2.750 0.7123 0.01743 0.00784 -0.0690 0.4103 1.0000
3.000 0.7317 0.01776 0.00801 -0.0674 0.4001 1.0000
3.250 0.7517 0.01808 0.00823 -0.0659 0.3903 1.0000
3.500 0.7722 0.01843 0.00844 -0.0646 0.3823 1.0000
3.750 0.7930 0.01877 0.00871 -0.0633 0.3740 1.0000
4.000 0.8140 0.01916 0.00895 -0.0621 0.3672 1.0000
4.250 0.8354 0.01951 0.00927 -0.0609 0.3599 1.0000
4.500 0.8569 0.01990 0.00957 -0.0598 0.3535 1.0000
4.750 0.8791 0.02032 0.00987 -0.0589 0.3478 1.0000
5.000 0.9005 0.02070 0.01026 -0.0578 0.3416 1.0000
5.250 0.9223 0.02111 0.01062 -0.0568 0.3360 1.0000
5.750 0.9665 0.02199 0.01142 -0.0549 0.3257 1.0000
6.000 0.9879 0.02242 0.01186 -0.0539 0.3204 1.0000
6.250 1.0101 0.02289 0.01226 -0.0531 0.3157 1.0000
6.500 1.0327 0.02339 0.01271 -0.0523 0.3111 1.0000
6.750 1.0525 0.02385 0.01325 -0.0511 0.3062 1.0000
7.000 1.0732 0.02433 0.01374 -0.0500 0.3015 1.0000
7.250 1.0949 0.02483 0.01420 -0.0491 0.2972 1.0000
7.500 1.1166 0.02537 0.01473 -0.0483 0.2930 1.0000
7.750 1.1337 0.02589 0.01535 -0.0467 0.2882 1.0000
8.000 1.1524 0.02641 0.01591 -0.0454 0.2837 1.0000
8.250 1.1728 0.02694 0.01644 -0.0444 0.2798 1.0000
8.500 1.1941 0.02752 0.01699 -0.0436 0.2761 1.0000
8.750 1.2069 0.02810 0.01773 -0.0413 0.2717 1.0000
9.000 1.2216 0.02868 0.01839 -0.0395 0.2674 1.0000
9.250 1.2382 0.02924 0.01897 -0.0379 0.2636 1.0000
9.500 1.2585 0.02981 0.01949 -0.0370 0.2602 1.0000
9.750 1.2695 0.03055 0.02038 -0.0348 0.2564 1.0000
10.000 1.2811 0.03129 0.02127 -0.0327 0.2524 1.0000
10.250 1.2946 0.03198 0.02203 -0.0309 0.2488 1.0000
10.500 1.3103 0.03261 0.02266 -0.0295 0.2454 1.0000
10.750 1.3261 0.03332 0.02339 -0.0282 0.2423 1.0000
11.000 1.3311 0.03434 0.02462 -0.0256 0.2385 1.0000
11.250 1.3392 0.03528 0.02568 -0.0235 0.2347 1.0000
11.500 1.3502 0.03610 0.02656 -0.0218 0.2313 1.0000
11.750 1.3648 0.03681 0.02728 -0.0206 0.2284 1.0000
12.000 1.3693 0.03799 0.02860 -0.0185 0.2249 1.0000
12.250 1.3694 0.03939 0.03019 -0.0161 0.2209 1.0000
12.500 1.3737 0.04058 0.03146 -0.0143 0.2171 1.0000
12.750 1.3828 0.04146 0.03235 -0.0129 0.2135 1.0000
13.000 1.3850 0.04294 0.03394 -0.0113 0.2101 1.0000
13.250 1.3798 0.04505 0.03627 -0.0095 0.2063 1.0000
13.500 1.3794 0.04689 0.03822 -0.0082 0.2028 1.0000
13.750 1.3844 0.04829 0.03966 -0.0072 0.1994 1.0000
14.000 1.3875 0.04996 0.04137 -0.0062 0.1962 1.0000
14.250 1.3721 0.05344 0.04511 -0.0053 0.1925 1.0000
14.500 1.3629 0.05652 0.04834 -0.0048 0.1888 1.0000
14.750 1.3625 0.05881 0.05070 -0.0045 0.1855 1.0000
15.000 1.3699 0.06036 0.05224 -0.0042 0.1825 1.0000
15.250 1.3370 0.06678 0.05897 -0.0051 0.1793 1.0000
15.500 1.3043 0.07379 0.06621 -0.0069 0.1759 1.0000
15.750 1.2880 0.07894 0.07148 -0.0083 0.1726 1.0000
16.000 1.3055 0.07932 0.07183 -0.0079 0.1697 1.0000
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