GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 744 AIRFOIL (goe744-il) Reynolds number: 200,000 Max Cl/Cd: 64.81 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe744-il-200000-n5.txt Download as CSV file: xf-goe744-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 744 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1694 0.09467 0.08955 0.0007 0.5187 0.0414
-7.500 -0.1643 0.09201 0.08686 -0.0008 0.5170 0.0422
-7.250 -0.1634 0.08921 0.08406 -0.0030 0.5154 0.0431
-7.000 -0.1683 0.08637 0.08127 -0.0058 0.5139 0.0434
-6.750 -0.1727 0.08359 0.07851 -0.0085 0.5123 0.0436
-6.500 -0.1683 0.08028 0.07519 -0.0118 0.5104 0.0437
-6.250 -0.1587 0.07706 0.07197 -0.0135 0.5081 0.0438
-6.000 -0.1453 0.07450 0.06941 -0.0134 0.5055 0.0440
-5.750 -0.1318 0.07207 0.06696 -0.0137 0.5032 0.0444
-5.500 -0.1184 0.06955 0.06440 -0.0146 0.5011 0.0448
-5.250 -0.1042 0.06701 0.06181 -0.0158 0.4992 0.0454
-5.000 -0.0891 0.06437 0.05908 -0.0172 0.4974 0.0460
-4.750 -0.0725 0.06161 0.05623 -0.0188 0.4954 0.0469
-4.250 -0.0340 0.05440 0.04880 -0.0236 0.4909 0.0494
-3.750 0.0040 0.04516 0.03914 -0.0252 0.4866 0.0388
-3.500 0.0249 0.04335 0.03726 -0.0251 0.4843 0.0384
-3.250 0.0465 0.04090 0.03466 -0.0251 0.4820 0.0379
-3.000 0.0683 0.03792 0.03144 -0.0250 0.4800 0.0373
-2.750 0.0900 0.03430 0.02747 -0.0245 0.4781 0.0368
-2.500 0.1119 0.03067 0.02344 -0.0237 0.4760 0.0371
-2.250 0.1348 0.02780 0.02015 -0.0228 0.4736 0.0377
-2.000 0.1591 0.02572 0.01769 -0.0220 0.4710 0.0378
-1.750 0.1847 0.02412 0.01572 -0.0213 0.4683 0.0379
-1.500 0.2112 0.02289 0.01417 -0.0207 0.4655 0.0382
-1.250 0.2385 0.02190 0.01286 -0.0203 0.4630 0.0386
-1.000 0.2662 0.02111 0.01179 -0.0198 0.4607 0.0391
-0.750 0.2937 0.02056 0.01113 -0.0196 0.4586 0.0396
-0.500 0.3218 0.02019 0.01079 -0.0196 0.4554 0.0405
-0.250 0.3500 0.01982 0.01038 -0.0195 0.4521 0.0417
0.000 0.3785 0.01941 0.00986 -0.0194 0.4490 0.0429
0.250 0.4070 0.01901 0.00933 -0.0192 0.4462 0.0437
0.500 0.4350 0.01859 0.00891 -0.0191 0.4438 0.0445
0.750 0.4628 0.01828 0.00855 -0.0188 0.4414 0.0455
1.000 0.4905 0.01808 0.00839 -0.0188 0.4381 0.0467
1.250 0.5182 0.01792 0.00825 -0.0186 0.4346 0.0485
1.500 0.5453 0.01771 0.00810 -0.0185 0.4313 0.0506
1.750 0.5724 0.01754 0.00793 -0.0182 0.4283 0.0530
2.000 0.5993 0.01737 0.00772 -0.0179 0.4256 0.0551
2.250 0.6260 0.01726 0.00760 -0.0176 0.4228 0.0579
2.500 0.6525 0.01724 0.00766 -0.0174 0.4190 0.0624
2.750 0.6788 0.01719 0.00767 -0.0171 0.4153 0.0695
3.000 0.7049 0.01708 0.00765 -0.0168 0.4120 0.0843
3.250 0.7293 0.01685 0.00768 -0.0161 0.4091 0.1790
3.500 0.7545 0.01682 0.00774 -0.0157 0.4061 0.2362
3.750 0.7786 0.01682 0.00798 -0.0152 0.4020 0.3006
4.250 0.9712 0.01598 0.00832 -0.0427 0.3916 1.0000
4.500 0.9962 0.01622 0.00856 -0.0425 0.3878 1.0000
4.750 1.0211 0.01648 0.00881 -0.0422 0.3836 1.0000
5.000 1.0458 0.01669 0.00898 -0.0418 0.3799 1.0000
5.250 1.0702 0.01689 0.00909 -0.0414 0.3767 1.0000
5.500 1.0944 0.01714 0.00930 -0.0409 0.3735 1.0000
5.750 1.1180 0.01748 0.00968 -0.0406 0.3695 1.0000
6.000 1.1414 0.01779 0.00998 -0.0402 0.3656 1.0000
6.250 1.1646 0.01805 0.01020 -0.0396 0.3619 1.0000
6.500 1.1874 0.01832 0.01038 -0.0391 0.3587 1.0000
6.750 1.2091 0.01876 0.01089 -0.0386 0.3543 1.0000
7.000 1.2304 0.01915 0.01131 -0.0380 0.3503 1.0000
7.250 1.2514 0.01953 0.01165 -0.0373 0.3468 1.0000
7.500 1.2721 0.01988 0.01195 -0.0366 0.3437 1.0000
7.750 1.2910 0.02040 0.01252 -0.0358 0.3401 1.0000
8.000 1.3087 0.02096 0.01313 -0.0349 0.3363 1.0000
8.250 1.3256 0.02149 0.01367 -0.0339 0.3326 1.0000
8.500 1.3418 0.02201 0.01415 -0.0328 0.3293 1.0000
8.750 1.3559 0.02264 0.01478 -0.0316 0.3259 1.0000
9.000 1.3648 0.02359 0.01582 -0.0301 0.3219 1.0000
9.250 1.3666 0.02469 0.01696 -0.0280 0.3183 1.0000
9.500 1.3678 0.02574 0.01800 -0.0257 0.3152 1.0000
9.750 1.3752 0.02661 0.01884 -0.0240 0.3125 1.0000
10.000 1.3775 0.02797 0.02025 -0.0224 0.3092 1.0000
10.250 1.3778 0.02960 0.02197 -0.0211 0.3056 1.0000
10.500 1.3815 0.03108 0.02348 -0.0199 0.3023 1.0000
10.750 1.3889 0.03229 0.02468 -0.0189 0.2992 1.0000
11.000 1.4013 0.03311 0.02546 -0.0180 0.2966 1.0000
11.250 1.4004 0.03516 0.02759 -0.0172 0.2931 1.0000
11.500 1.3971 0.03749 0.03002 -0.0165 0.2891 1.0000
11.750 1.4002 0.03927 0.03184 -0.0158 0.2859 1.0000
12.000 1.4095 0.04049 0.03304 -0.0152 0.2832 1.0000
12.250 1.4247 0.04114 0.03367 -0.0145 0.2810 1.0000
12.500 1.4217 0.04364 0.03626 -0.0140 0.2780 1.0000
12.750 1.4140 0.04666 0.03941 -0.0138 0.2745 1.0000
13.000 1.4120 0.04919 0.04200 -0.0135 0.2712 1.0000
13.250 1.4205 0.05064 0.04346 -0.0131 0.2685 1.0000
13.500 1.4365 0.05126 0.04405 -0.0126 0.2663 1.0000
13.750 1.4435 0.05291 0.04574 -0.0123 0.2639 1.0000
14.000 1.4235 0.05775 0.05075 -0.0127 0.2603 1.0000
14.250 1.4150 0.06133 0.05444 -0.0130 0.2570 1.0000
14.500 1.4165 0.06376 0.05692 -0.0130 0.2542 1.0000
14.750 1.4304 0.06467 0.05783 -0.0127 0.2521 1.0000
15.000 1.4519 0.06466 0.05780 -0.0122 0.2504 1.0000
15.250 1.4230 0.07095 0.06427 -0.0132 0.2466 1.0000
15.500 1.3811 0.07920 0.07271 -0.0147 0.2414 1.0000
15.750 1.3814 0.08198 0.07555 -0.0150 0.2387 1.0000
16.000 1.3972 0.08267 0.07624 -0.0148 0.2370 1.0000
16.250 1.4202 0.08237 0.07594 -0.0144 0.2358 1.0000
16.500 1.4458 0.08173 0.07530 -0.0138 0.2347 1.0000
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Polar data table (+)
Polar graphs
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