GOE 514 AIRFOIL (goe514-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 514 AIRFOIL (goe514-il) Reynolds number: 100,000 Max Cl/Cd: 41.89 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe514-il-100000-n5.txt Download as CSV file: xf-goe514-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 514 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2253 0.10213 0.09729 -0.0765 0.9621 0.0361
-10.750 -0.3563 0.07483 0.06997 -0.0898 0.9522 0.0352
-10.500 -0.4079 0.06401 0.05905 -0.0981 0.9430 0.0344
-10.250 -0.4560 0.05660 0.05140 -0.0989 0.9318 0.0338
-10.000 -0.4886 0.05080 0.04524 -0.0968 0.9200 0.0338
-9.750 -0.4925 0.04597 0.03991 -0.0969 0.9144 0.0347
-9.500 -0.5042 0.04356 0.03720 -0.0922 0.9037 0.0353
-9.250 -0.4859 0.04211 0.03571 -0.0919 0.8993 0.0364
-9.000 -0.4813 0.04066 0.03411 -0.0890 0.8915 0.0375
-8.750 -0.4708 0.03894 0.03215 -0.0870 0.8850 0.0389
-8.500 -0.4520 0.03691 0.02977 -0.0865 0.8813 0.0412
-8.250 -0.4477 0.03623 0.02907 -0.0827 0.8719 0.0425
-8.000 -0.4274 0.03502 0.02768 -0.0819 0.8670 0.0458
-7.750 -0.4020 0.03372 0.02622 -0.0819 0.8641 0.0493
-7.500 -0.3987 0.03315 0.02553 -0.0778 0.8540 0.0522
-7.250 -0.3747 0.03207 0.02427 -0.0773 0.8499 0.0574
-6.750 -0.3401 0.03044 0.02237 -0.0737 0.8360 0.0691
-6.500 -0.3095 0.02927 0.02103 -0.0741 0.8322 0.0780
-6.250 -0.2970 0.02869 0.02029 -0.0712 0.8219 0.0850
-6.000 -0.2660 0.02780 0.01944 -0.0716 0.8170 0.0945
-5.750 -0.2487 0.02749 0.01914 -0.0695 0.8072 0.1028
-5.500 -0.2176 0.02697 0.01856 -0.0697 0.8016 0.1134
-5.250 -0.1957 0.02661 0.01805 -0.0683 0.7936 0.1228
-5.000 -0.1703 0.02627 0.01765 -0.0675 0.7872 0.1318
-4.750 -0.1372 0.02567 0.01694 -0.0680 0.7838 0.1416
-4.500 -0.1208 0.02545 0.01649 -0.0656 0.7740 0.1513
-4.250 -0.0900 0.02494 0.01602 -0.0657 0.7693 0.1603
-4.000 -0.0664 0.02460 0.01552 -0.0647 0.7620 0.1704
-3.750 -0.0399 0.02429 0.01519 -0.0640 0.7548 0.1792
-3.500 -0.0026 0.02366 0.01442 -0.0653 0.7508 0.1891
-3.250 0.0143 0.02366 0.01439 -0.0630 0.7402 0.1956
-3.000 0.0518 0.02309 0.01365 -0.0643 0.7350 0.2047
-2.750 0.0726 0.02304 0.01357 -0.0627 0.7250 0.2105
-2.500 0.1105 0.02251 0.01284 -0.0641 0.7185 0.2190
-2.250 0.1335 0.02242 0.01273 -0.0630 0.7081 0.2242
-2.000 0.1721 0.02198 0.01211 -0.0645 0.7005 0.2335
-1.750 0.1933 0.02195 0.01207 -0.0631 0.6886 0.2391
-1.500 0.2283 0.02163 0.01161 -0.0641 0.6789 0.2466
-1.250 0.2549 0.02146 0.01136 -0.0636 0.6669 0.2529
-1.000 0.2786 0.02138 0.01122 -0.0626 0.6540 0.2582
-0.750 0.3082 0.02116 0.01085 -0.0627 0.6414 0.2649
-0.500 0.3389 0.02095 0.01055 -0.0630 0.6284 0.2703
-0.250 0.3588 0.02094 0.01048 -0.0614 0.6134 0.2763
0.000 0.3815 0.02092 0.01034 -0.0603 0.5985 0.2833
0.250 0.4046 0.02088 0.01027 -0.0593 0.5832 0.2892
0.500 0.4282 0.02089 0.01016 -0.0584 0.5679 0.2968
0.750 0.4520 0.02090 0.01010 -0.0576 0.5526 0.3038
1.000 0.4759 0.02096 0.01005 -0.0568 0.5380 0.3119
1.250 0.5005 0.02104 0.01000 -0.0562 0.5243 0.3201
1.500 0.5234 0.02116 0.01005 -0.0554 0.5115 0.3286
1.750 0.5469 0.02131 0.01010 -0.0547 0.5000 0.3377
2.000 0.5714 0.02144 0.01012 -0.0541 0.4899 0.3475
2.250 0.5932 0.02161 0.01023 -0.0532 0.4800 0.3568
2.500 0.6166 0.02178 0.01029 -0.0525 0.4717 0.3675
2.750 0.6379 0.02194 0.01043 -0.0515 0.4636 0.3768
3.250 0.6834 0.02229 0.01068 -0.0500 0.4503 0.3991
3.500 0.7052 0.02245 0.01082 -0.0491 0.4442 0.4134
3.750 0.7299 0.02256 0.01089 -0.0488 0.4387 0.4370
4.250 0.9576 0.02345 0.01293 -0.0851 0.4201 1.0000
4.500 0.9725 0.02378 0.01324 -0.0829 0.4157 1.0000
4.750 0.9896 0.02412 0.01353 -0.0812 0.4113 1.0000
5.000 1.0090 0.02446 0.01378 -0.0799 0.4073 1.0000
5.250 1.0328 0.02482 0.01402 -0.0794 0.4035 1.0000
5.500 1.0441 0.02520 0.01445 -0.0767 0.3993 1.0000
5.750 1.0595 0.02559 0.01484 -0.0747 0.3953 1.0000
6.000 1.0771 0.02598 0.01519 -0.0732 0.3916 1.0000
6.250 1.0990 0.02636 0.01551 -0.0724 0.3884 1.0000
6.500 1.1218 0.02678 0.01587 -0.0718 0.3855 1.0000
6.750 1.1323 0.02726 0.01643 -0.0691 0.3820 1.0000
7.000 1.1455 0.02774 0.01695 -0.0669 0.3784 1.0000
7.250 1.1616 0.02820 0.01743 -0.0652 0.3751 1.0000
7.500 1.1807 0.02863 0.01783 -0.0640 0.3719 1.0000
7.750 1.2052 0.02905 0.01819 -0.0638 0.3692 1.0000
8.000 1.2159 0.02965 0.01888 -0.0613 0.3663 1.0000
8.250 1.2250 0.03028 0.01962 -0.0587 0.3633 1.0000
8.500 1.2367 0.03090 0.02031 -0.0564 0.3602 1.0000
8.750 1.2513 0.03147 0.02092 -0.0547 0.3573 1.0000
9.000 1.2695 0.03197 0.02142 -0.0536 0.3544 1.0000
9.250 1.2935 0.03241 0.02183 -0.0533 0.3518 1.0000
9.500 1.2991 0.03323 0.02278 -0.0504 0.3491 1.0000
9.750 1.3022 0.03416 0.02386 -0.0472 0.3463 1.0000
10.000 1.3083 0.03505 0.02487 -0.0445 0.3433 1.0000
10.250 1.3183 0.03580 0.02569 -0.0424 0.3401 1.0000
10.500 1.3351 0.03631 0.02620 -0.0412 0.3370 1.0000
10.750 1.3608 0.03664 0.02649 -0.0413 0.3343 1.0000
11.000 1.3486 0.03816 0.02824 -0.0365 0.3309 1.0000
11.250 1.3416 0.03959 0.02984 -0.0327 0.3271 1.0000
11.500 1.3453 0.04057 0.03089 -0.0302 0.3230 1.0000
11.750 1.3639 0.04086 0.03115 -0.0293 0.3193 1.0000
12.000 1.3673 0.04198 0.03235 -0.0270 0.3157 1.0000
12.250 1.3477 0.04440 0.03500 -0.0228 0.3116 1.0000
12.500 1.3425 0.04621 0.03695 -0.0201 0.3079 1.0000
12.750 1.3501 0.04734 0.03816 -0.0187 0.3049 1.0000
13.000 1.3691 0.04778 0.03862 -0.0181 0.3024 1.0000
13.250 1.3621 0.04999 0.04096 -0.0158 0.2992 1.0000
13.500 1.3141 0.05555 0.04682 -0.0117 0.2946 1.0000
13.750 1.2946 0.05930 0.05072 -0.0098 0.2904 1.0000
14.000 1.3101 0.05996 0.05142 -0.0092 0.2875 1.0000
14.250 1.3444 0.05891 0.05036 -0.0092 0.2853 1.0000
14.750 1.1927 0.08029 0.07221 -0.0066 0.2704 1.0000
15.000 1.2345 0.07761 0.06955 -0.0059 0.2694 1.0000
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