GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 412 AIRFOIL (goe412-il) Reynolds number: 100,000 Max Cl/Cd: 54.66 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe412-il-100000.txt Download as CSV file: xf-goe412-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 412 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3052 0.10191 0.09746 -0.0465 0.9741 0.1227
-7.500 -0.3130 0.09955 0.09513 -0.0509 0.9650 0.1271
-7.250 -0.3268 0.09490 0.09048 -0.0636 0.9522 0.1299
-7.000 -0.3024 0.09167 0.08727 -0.0588 0.9498 0.1319
-6.750 -0.2799 0.08879 0.08435 -0.0593 0.9453 0.1367
-6.500 -0.2925 0.08421 0.07960 -0.0751 0.9310 0.1455
-6.250 -0.2668 0.08066 0.07615 -0.0711 0.9290 0.1476
-6.000 -0.2519 0.07830 0.07379 -0.0700 0.9234 0.1509
-5.500 -0.2156 0.07036 0.06566 -0.0802 0.9117 0.1650
-5.250 -0.2158 0.06884 0.06414 -0.0772 0.9024 0.1679
-5.000 -0.1882 0.06443 0.05952 -0.0844 0.8977 0.1805
-4.750 -0.1679 0.05074 0.04432 -0.0946 0.8895 0.1139
-4.500 -0.1387 0.04405 0.03689 -0.0973 0.8856 0.1003
-4.250 -0.1017 0.04086 0.03342 -0.1000 0.8826 0.0983
-4.000 -0.0815 0.03890 0.03113 -0.0996 0.8762 0.0974
-3.750 -0.0520 0.03689 0.02869 -0.1005 0.8711 0.0973
-3.500 -0.0122 0.03521 0.02644 -0.1027 0.8678 0.0995
-3.250 0.0156 0.03403 0.02516 -0.1032 0.8627 0.1029
-3.000 0.0393 0.03342 0.02444 -0.1029 0.8561 0.1062
-2.750 0.0788 0.03235 0.02309 -0.1047 0.8526 0.1117
-2.500 0.1229 0.03119 0.02190 -0.1075 0.8503 0.1212
-2.250 0.1315 0.03136 0.02197 -0.1046 0.8408 0.1309
-2.000 0.1699 0.03046 0.02110 -0.1064 0.8371 0.1611
-1.750 0.2127 0.02946 0.02035 -0.1091 0.8347 0.1986
-1.500 0.2197 0.03003 0.02102 -0.1062 0.8248 0.2179
-1.250 0.2571 0.02977 0.02084 -0.1079 0.8209 0.2598
-1.000 0.3006 0.02910 0.02042 -0.1104 0.8185 0.3134
-0.750 0.3048 0.02966 0.02122 -0.1072 0.8078 0.3559
-0.500 0.3532 0.02739 0.02092 -0.1094 0.8056 1.0000
-0.250 0.3994 0.02718 0.02033 -0.1122 0.8029 1.0000
0.000 0.4009 0.02830 0.02132 -0.1085 0.7916 1.0000
0.250 0.4433 0.02810 0.02089 -0.1106 0.7879 1.0000
0.500 0.4833 0.02796 0.02057 -0.1123 0.7841 1.0000
0.750 0.4909 0.02889 0.02141 -0.1094 0.7731 1.0000
1.000 0.5386 0.02831 0.02067 -0.1120 0.7705 1.0000
1.250 0.5425 0.02947 0.02177 -0.1087 0.7586 1.0000
1.500 0.5871 0.02891 0.02109 -0.1107 0.7553 1.0000
1.750 0.6343 0.02816 0.02023 -0.1130 0.7532 1.0000
2.000 0.6360 0.02951 0.02156 -0.1095 0.7404 1.0000
2.250 0.6808 0.02881 0.02078 -0.1114 0.7378 1.0000
2.500 0.6858 0.03007 0.02202 -0.1084 0.7258 1.0000
2.750 0.7288 0.02938 0.02128 -0.1100 0.7226 1.0000
3.000 0.7689 0.02876 0.02061 -0.1111 0.7184 1.0000
3.250 0.7845 0.02930 0.02114 -0.1091 0.7075 1.0000
3.500 0.8362 0.02789 0.01968 -0.1115 0.7048 1.0000
3.750 0.8459 0.02870 0.02050 -0.1088 0.6925 1.0000
4.000 0.8951 0.02739 0.01917 -0.1109 0.6892 1.0000
4.250 0.9077 0.02805 0.01985 -0.1085 0.6775 1.0000
4.500 0.9541 0.02690 0.01867 -0.1103 0.6734 1.0000
4.750 0.9692 0.02740 0.01922 -0.1082 0.6623 1.0000
5.000 1.0139 0.02635 0.01815 -0.1098 0.6574 1.0000
5.250 1.0312 0.02663 0.01848 -0.1079 0.6459 1.0000
5.500 1.0798 0.02531 0.01712 -0.1100 0.6403 1.0000
5.750 1.0960 0.02557 0.01744 -0.1079 0.6279 1.0000
6.000 1.1230 0.02539 0.01729 -0.1072 0.6180 1.0000
6.250 1.1594 0.02480 0.01670 -0.1079 0.6094 1.0000
6.500 1.1781 0.02501 0.01698 -0.1062 0.5973 1.0000
6.750 1.2057 0.02485 0.01685 -0.1057 0.5867 1.0000
7.000 1.2407 0.02439 0.01639 -0.1063 0.5766 1.0000
7.250 1.2592 0.02459 0.01665 -0.1045 0.5631 1.0000
7.500 1.2805 0.02464 0.01674 -0.1030 0.5493 1.0000
7.750 1.3028 0.02465 0.01679 -0.1017 0.5349 1.0000
8.000 1.3244 0.02468 0.01683 -0.1003 0.5196 1.0000
8.250 1.3446 0.02479 0.01694 -0.0987 0.5036 1.0000
8.500 1.3635 0.02498 0.01713 -0.0970 0.4870 1.0000
8.750 1.3812 0.02527 0.01742 -0.0951 0.4700 1.0000
9.000 1.3980 0.02564 0.01775 -0.0931 0.4526 1.0000
9.250 1.4141 0.02608 0.01814 -0.0911 0.4350 1.0000
9.500 1.4287 0.02663 0.01862 -0.0888 0.4170 1.0000
9.750 1.4370 0.02736 0.01934 -0.0857 0.3996 1.0000
10.000 1.4477 0.02816 0.02011 -0.0831 0.3831 1.0000
10.250 1.4607 0.02901 0.02091 -0.0809 0.3677 1.0000
10.500 1.4743 0.02988 0.02173 -0.0790 0.3532 1.0000
10.750 1.4852 0.03079 0.02262 -0.0766 0.3395 1.0000
11.000 1.4895 0.03186 0.02377 -0.0736 0.3267 1.0000
11.250 1.4943 0.03295 0.02490 -0.0707 0.3143 1.0000
11.500 1.4989 0.03404 0.02600 -0.0679 0.3022 1.0000
11.750 1.5056 0.03509 0.02701 -0.0655 0.2906 1.0000
12.000 1.5053 0.03645 0.02850 -0.0626 0.2799 1.0000
12.250 1.5062 0.03787 0.03003 -0.0600 0.2693 1.0000
12.500 1.5072 0.03930 0.03147 -0.0575 0.2586 1.0000
12.750 1.5045 0.04100 0.03325 -0.0550 0.2477 1.0000
13.000 1.5003 0.04297 0.03536 -0.0526 0.2369 1.0000
13.250 1.4981 0.04493 0.03739 -0.0506 0.2265 1.0000
13.500 1.4965 0.04692 0.03936 -0.0487 0.2160 1.0000
13.750 1.4894 0.04952 0.04216 -0.0469 0.2051 1.0000
14.000 1.4825 0.05225 0.04499 -0.0453 0.1935 1.0000
14.250 1.4736 0.05532 0.04811 -0.0439 0.1811 1.0000
14.500 1.4622 0.05884 0.05167 -0.0428 0.1676 1.0000
14.750 1.4475 0.06300 0.05591 -0.0420 0.1524 1.0000
15.000 1.4295 0.06793 0.06094 -0.0417 0.1342 1.0000
15.250 1.4094 0.07351 0.06653 -0.0419 0.1140 1.0000
15.500 1.3885 0.07937 0.07225 -0.0423 0.0988 1.0000
15.750 1.3691 0.08506 0.07778 -0.0426 0.0889 1.0000
16.000 1.3544 0.08992 0.08244 -0.0424 0.0811 1.0000
16.250 1.3475 0.09383 0.08634 -0.0421 0.0739 1.0000
16.500 1.3467 0.09668 0.08917 -0.0413 0.0681 1.0000
16.750 1.3469 0.09970 0.09222 -0.0411 0.0636 1.0000
17.000 1.3556 0.10111 0.09353 -0.0398 0.0598 1.0000
17.250 1.3582 0.10404 0.09667 -0.0397 0.0572 1.0000
17.500 1.3639 0.10637 0.09910 -0.0393 0.0548 1.0000
17.750 1.3792 0.10695 0.09954 -0.0379 0.0522 1.0000
18.000 1.3825 0.10981 0.10256 -0.0379 0.0507 1.0000
18.250 1.3789 0.11390 0.10690 -0.0388 0.0495 1.0000
18.500 1.3760 0.11792 0.11113 -0.0399 0.0483 1.0000
18.750 1.3727 0.12204 0.11544 -0.0412 0.0472 1.0000
19.000 1.3692 0.12625 0.11983 -0.0426 0.0465 1.0000
19.250 1.3647 0.13074 0.12450 -0.0443 0.0459 1.0000
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