GOE 514 AIRFOIL (goe514-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 514 AIRFOIL (goe514-il) Reynolds number: 200,000 Max Cl/Cd: 51.55 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe514-il-200000-n5.txt Download as CSV file: xf-goe514-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3256 0.08712 0.08311 -0.0970 0.9655 0.0199
-13.000 -0.3710 0.07479 0.07057 -0.1055 0.9622 0.0196
-12.750 -0.3953 0.06625 0.06188 -0.1129 0.9599 0.0197
-12.500 -0.4324 0.05972 0.05527 -0.1154 0.9518 0.0195
-12.250 -0.4776 0.04898 0.04427 -0.1264 0.9462 0.0191
-12.000 -0.5166 0.04478 0.03989 -0.1237 0.9359 0.0190
-11.750 -0.5213 0.04122 0.03613 -0.1240 0.9318 0.0191
-11.500 -0.5361 0.03907 0.03384 -0.1196 0.9235 0.0193
-11.250 -0.5309 0.03676 0.03136 -0.1185 0.9186 0.0198
-11.000 -0.5174 0.03463 0.02902 -0.1182 0.9158 0.0205
-10.750 -0.5180 0.03330 0.02754 -0.1144 0.9092 0.0208
-10.500 -0.5116 0.03199 0.02602 -0.1116 0.9032 0.0214
-10.250 -0.4944 0.03051 0.02440 -0.1108 0.9002 0.0220
-10.000 -0.4731 0.02910 0.02289 -0.1106 0.8982 0.0228
-9.750 -0.4764 0.02850 0.02220 -0.1052 0.8888 0.0232
-9.500 -0.4577 0.02739 0.02096 -0.1040 0.8850 0.0241
-9.250 -0.4333 0.02627 0.01966 -0.1037 0.8826 0.0252
-9.000 -0.4068 0.02512 0.01841 -0.1039 0.8809 0.0267
-8.750 -0.4097 0.02473 0.01797 -0.0982 0.8703 0.0277
-8.500 -0.3847 0.02382 0.01692 -0.0978 0.8673 0.0298
-8.250 -0.3550 0.02280 0.01582 -0.0983 0.8650 0.0322
-8.000 -0.3495 0.02232 0.01526 -0.0939 0.8552 0.0343
-7.750 -0.3229 0.02146 0.01433 -0.0936 0.8509 0.0379
-7.500 -0.2890 0.02059 0.01341 -0.0948 0.8482 0.0444
-7.250 -0.2827 0.02026 0.01303 -0.0904 0.8373 0.0489
-7.000 -0.2510 0.01961 0.01231 -0.0910 0.8332 0.0565
-6.750 -0.2360 0.01928 0.01189 -0.0883 0.8240 0.0621
-6.500 -0.2090 0.01874 0.01128 -0.0880 0.8180 0.0685
-6.250 -0.1849 0.01835 0.01076 -0.0870 0.8106 0.0745
-6.000 -0.1611 0.01778 0.01017 -0.0861 0.8019 0.0803
-5.750 -0.1366 0.01735 0.00965 -0.0852 0.7933 0.0867
-5.500 -0.1055 0.01680 0.00911 -0.0858 0.7856 0.0963
-5.000 -0.0430 0.01615 0.00849 -0.0868 0.7697 0.1233
-4.750 -0.0110 0.01593 0.00815 -0.0873 0.7609 0.1356
-4.500 0.0260 0.01568 0.00782 -0.0890 0.7523 0.1467
-4.250 0.0562 0.01549 0.00754 -0.0893 0.7428 0.1551
-4.000 0.0954 0.01529 0.00720 -0.0914 0.7334 0.1639
-3.750 0.1229 0.01516 0.00695 -0.0911 0.7221 0.1702
-3.500 0.1528 0.01503 0.00677 -0.0915 0.7116 0.1764
-3.250 0.1838 0.01494 0.00655 -0.0920 0.7007 0.1819
-3.000 0.2069 0.01489 0.00637 -0.0908 0.6896 0.1866
-2.750 0.2322 0.01482 0.00627 -0.0902 0.6784 0.1913
-2.500 0.2542 0.01480 0.00617 -0.0889 0.6659 0.1965
-2.250 0.2737 0.01478 0.00606 -0.0870 0.6537 0.2010
-2.000 0.2936 0.01476 0.00596 -0.0853 0.6411 0.2043
-1.750 0.3131 0.01476 0.00590 -0.0834 0.6283 0.2083
-1.500 0.3293 0.01479 0.00587 -0.0810 0.6145 0.2132
-1.250 0.3459 0.01483 0.00581 -0.0786 0.5995 0.2182
-1.000 0.3615 0.01489 0.00583 -0.0760 0.5836 0.2223
-0.750 0.3760 0.01499 0.00584 -0.0732 0.5657 0.2274
-0.500 0.3905 0.01511 0.00584 -0.0704 0.5474 0.2334
-0.250 0.4042 0.01524 0.00591 -0.0676 0.5294 0.2382
0.000 0.4180 0.01542 0.00598 -0.0647 0.5119 0.2445
0.250 0.4321 0.01560 0.00604 -0.0620 0.4957 0.2512
0.500 0.4464 0.01579 0.00616 -0.0594 0.4813 0.2573
0.750 0.4615 0.01600 0.00626 -0.0569 0.4688 0.2649
1.000 0.4768 0.01620 0.00639 -0.0545 0.4581 0.2711
1.250 0.4940 0.01639 0.00652 -0.0525 0.4484 0.2786
1.500 0.5108 0.01660 0.00664 -0.0505 0.4405 0.2850
1.750 0.5295 0.01677 0.00679 -0.0488 0.4335 0.2918
2.000 0.5481 0.01697 0.00692 -0.0472 0.4268 0.2987
2.250 0.5664 0.01716 0.00707 -0.0455 0.4213 0.3047
2.500 0.5861 0.01732 0.00722 -0.0441 0.4156 0.3116
2.750 0.6052 0.01751 0.00737 -0.0425 0.4099 0.3177
3.000 0.6234 0.01772 0.00754 -0.0409 0.4049 0.3239
3.250 0.6432 0.01788 0.00771 -0.0395 0.4004 0.3305
3.500 0.6625 0.01805 0.00788 -0.0381 0.3958 0.3366
3.750 0.6813 0.01823 0.00806 -0.0366 0.3916 0.3434
4.000 0.7007 0.01846 0.00824 -0.0352 0.3879 0.3508
4.250 0.7202 0.01864 0.00844 -0.0339 0.3844 0.3580
4.500 0.7396 0.01882 0.00865 -0.0326 0.3804 0.3672
4.750 0.7585 0.01900 0.00887 -0.0312 0.3766 0.3780
5.000 0.7775 0.01921 0.00909 -0.0298 0.3729 0.3901
5.250 0.7973 0.01943 0.00931 -0.0287 0.3696 0.4068
5.500 0.8177 0.01958 0.00955 -0.0277 0.3663 0.4332
5.750 1.0428 0.02026 0.01155 -0.0705 0.3571 1.0000
6.000 1.0587 0.02056 0.01180 -0.0687 0.3543 1.0000
6.250 1.0757 0.02088 0.01206 -0.0670 0.3516 1.0000
6.500 1.0914 0.02118 0.01238 -0.0651 0.3487 1.0000
6.750 1.1072 0.02148 0.01272 -0.0633 0.3458 1.0000
7.000 1.1229 0.02180 0.01306 -0.0615 0.3428 1.0000
7.250 1.1393 0.02214 0.01340 -0.0598 0.3403 1.0000
7.500 1.1558 0.02250 0.01374 -0.0582 0.3378 1.0000
7.750 1.1735 0.02286 0.01407 -0.0568 0.3356 1.0000
8.000 1.1911 0.02324 0.01444 -0.0555 0.3333 1.0000
8.250 1.2052 0.02364 0.01492 -0.0536 0.3302 1.0000
8.500 1.2200 0.02405 0.01538 -0.0518 0.3273 1.0000
8.750 1.2333 0.02449 0.01585 -0.0499 0.3239 1.0000
9.000 1.2489 0.02493 0.01630 -0.0483 0.3213 1.0000
9.250 1.2649 0.02537 0.01672 -0.0469 0.3187 1.0000
9.500 1.2807 0.02584 0.01722 -0.0454 0.3162 1.0000
9.750 1.2925 0.02638 0.01786 -0.0435 0.3129 1.0000
10.000 1.3051 0.02694 0.01849 -0.0417 0.3097 1.0000
10.250 1.3172 0.02751 0.01910 -0.0398 0.3064 1.0000
10.500 1.3313 0.02806 0.01966 -0.0383 0.3038 1.0000
10.750 1.3465 0.02860 0.02017 -0.0370 0.3010 1.0000
11.000 1.3571 0.02931 0.02102 -0.0352 0.2981 1.0000
11.250 1.3662 0.03007 0.02188 -0.0332 0.2942 1.0000
11.500 1.3772 0.03081 0.02269 -0.0316 0.2911 1.0000
11.750 1.3885 0.03155 0.02346 -0.0300 0.2881 1.0000
12.000 1.4016 0.03224 0.02416 -0.0287 0.2857 1.0000
12.250 1.4098 0.03319 0.02523 -0.0270 0.2821 1.0000
12.500 1.4178 0.03420 0.02636 -0.0253 0.2783 1.0000
12.750 1.4239 0.03529 0.02751 -0.0235 0.2738 1.0000
13.000 1.4313 0.03635 0.02857 -0.0220 0.2700 1.0000
13.250 1.4357 0.03771 0.03007 -0.0203 0.2648 1.0000
13.500 1.4398 0.03914 0.03159 -0.0187 0.2595 1.0000
13.750 1.4442 0.04057 0.03303 -0.0173 0.2550 1.0000
14.000 1.4480 0.04218 0.03477 -0.0160 0.2498 1.0000
14.250 1.4501 0.04398 0.03666 -0.0147 0.2440 1.0000
14.500 1.4515 0.04585 0.03855 -0.0134 0.2391 1.0000
14.750 1.4532 0.04785 0.04070 -0.0124 0.2332 1.0000
15.000 1.4516 0.05018 0.04309 -0.0114 0.2266 1.0000
15.250 1.4517 0.05244 0.04542 -0.0105 0.2217 1.0000
15.500 1.4484 0.05512 0.04820 -0.0097 0.2143 1.0000
15.750 1.4434 0.05802 0.05115 -0.0089 0.2084 1.0000
16.000 1.4372 0.06117 0.05440 -0.0084 0.2009 1.0000
16.250 1.4255 0.06503 0.05831 -0.0079 0.1924 1.0000
16.500 1.4107 0.06938 0.06270 -0.0077 0.1832 1.0000
16.750 1.3977 0.07365 0.06705 -0.0077 0.1758 1.0000
17.000 1.3825 0.07830 0.07177 -0.0079 0.1698 1.0000
17.250 1.3656 0.08332 0.07687 -0.0083 0.1625 1.0000
17.500 1.3427 0.08924 0.08283 -0.0090 0.1549 1.0000
17.750 1.3292 0.09401 0.08769 -0.0097 0.1500 1.0000
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Polar data table (+)
Polar graphs
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