GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 744 AIRFOIL (goe744-il) Reynolds number: 200,000 Max Cl/Cd: 56.84 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe744-il-200000.txt Download as CSV file: xf-goe744-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1666 0.09689 0.09235 -0.0011 0.5690 0.0511
-7.500 -0.1721 0.09458 0.09008 -0.0047 0.5670 0.0522
-7.250 -0.1973 0.09289 0.08841 -0.0112 0.5657 0.0526
-7.000 -0.1803 0.08915 0.08467 -0.0095 0.5631 0.0529
-6.750 -0.1611 0.08613 0.08161 -0.0080 0.5606 0.0535
-6.500 -0.1520 0.08384 0.07927 -0.0081 0.5584 0.0542
-6.250 -0.1426 0.08136 0.07684 -0.0094 0.5557 0.0551
-6.000 -0.1334 0.07880 0.07431 -0.0113 0.5528 0.0561
-5.750 -0.1239 0.07612 0.07163 -0.0137 0.5500 0.0576
-5.500 -0.1158 0.07238 0.06771 -0.0215 0.5480 0.0595
-5.250 -0.1016 0.06965 0.06501 -0.0204 0.5454 0.0600
-5.000 -0.0866 0.06731 0.06264 -0.0200 0.5429 0.0607
-4.750 -0.0709 0.06509 0.06035 -0.0202 0.5406 0.0618
-4.500 -0.0539 0.06286 0.05803 -0.0211 0.5383 0.0636
-4.250 -0.0305 0.05906 0.05401 -0.0261 0.5355 0.0674
-4.000 -0.0134 0.05693 0.05196 -0.0256 0.5321 0.0681
-3.750 0.0054 0.05506 0.05009 -0.0255 0.5290 0.0694
-3.500 0.0324 0.05219 0.04684 -0.0282 0.5265 0.0760
-3.250 0.0494 0.05011 0.04480 -0.0274 0.5239 0.0769
-3.000 0.0686 0.04853 0.04316 -0.0266 0.5215 0.0786
-2.750 0.0952 0.04629 0.04048 -0.0277 0.5192 0.0862
-2.500 0.1156 0.04450 0.03885 -0.0276 0.5156 0.0873
-2.250 0.1454 0.04452 0.03841 -0.0278 0.5122 0.0968
-2.000 0.1633 0.04122 0.03528 -0.0276 0.5090 0.0982
-1.750 0.1845 0.03972 0.03379 -0.0270 0.5061 0.1001
-1.500 0.2096 0.03869 0.03259 -0.0265 0.5036 0.1071
-1.250 0.2317 0.03685 0.03054 -0.0258 0.5014 0.1131
-1.000 0.2578 0.03627 0.02973 -0.0256 0.4982 0.1256
-0.750 0.2802 0.03484 0.02845 -0.0254 0.4941 0.1284
-0.500 0.3052 0.03406 0.02751 -0.0250 0.4906 0.1425
-0.250 0.3367 0.02705 0.01920 -0.0222 0.4885 0.0777
0.000 0.3649 0.02557 0.01736 -0.0213 0.4859 0.0721
0.250 0.3937 0.02434 0.01575 -0.0206 0.4837 0.0695
0.500 0.4221 0.02376 0.01494 -0.0202 0.4811 0.0692
0.750 0.4494 0.02357 0.01484 -0.0205 0.4763 0.0711
1.000 0.4776 0.02320 0.01442 -0.0204 0.4725 0.0729
1.250 0.5062 0.02270 0.01383 -0.0201 0.4694 0.0740
1.500 0.5348 0.02223 0.01325 -0.0197 0.4669 0.0753
1.750 0.5625 0.02168 0.01267 -0.0192 0.4647 0.0778
2.000 0.5880 0.02176 0.01289 -0.0190 0.4606 0.0820
2.250 0.6131 0.02173 0.01296 -0.0187 0.4561 0.0874
2.500 0.6391 0.02153 0.01279 -0.0182 0.4527 0.0944
2.750 0.6654 0.02118 0.01244 -0.0175 0.4500 0.1081
3.000 0.6893 0.02057 0.01222 -0.0163 0.4478 0.2339
3.250 0.8613 0.01939 0.01263 -0.0452 0.4399 1.0000
3.500 0.8865 0.01952 0.01268 -0.0447 0.4361 1.0000
3.750 0.9121 0.01950 0.01254 -0.0441 0.4332 1.0000
4.000 0.9379 0.01943 0.01231 -0.0434 0.4308 1.0000
4.250 0.9629 0.01967 0.01245 -0.0428 0.4279 1.0000
4.500 0.9860 0.02023 0.01312 -0.0428 0.4228 1.0000
4.750 1.0105 0.02038 0.01324 -0.0423 0.4190 1.0000
5.000 1.0360 0.02033 0.01309 -0.0417 0.4161 1.0000
5.250 1.0621 0.02023 0.01285 -0.0410 0.4135 1.0000
5.500 1.0850 0.02068 0.01332 -0.0406 0.4097 1.0000
5.750 1.1069 0.02119 0.01391 -0.0403 0.4050 1.0000
6.000 1.1310 0.02134 0.01403 -0.0397 0.4016 1.0000
6.250 1.1564 0.02132 0.01391 -0.0391 0.3988 1.0000
6.500 1.1826 0.02130 0.01375 -0.0385 0.3963 1.0000
6.750 1.2009 0.02208 0.01470 -0.0380 0.3913 1.0000
7.000 1.2222 0.02244 0.01509 -0.0374 0.3870 1.0000
7.250 1.2466 0.02247 0.01506 -0.0368 0.3838 1.0000
7.500 1.2727 0.02243 0.01491 -0.0362 0.3810 1.0000
7.750 1.2917 0.02307 0.01561 -0.0355 0.3772 1.0000
8.000 1.3079 0.02381 0.01645 -0.0347 0.3727 1.0000
8.250 1.3293 0.02409 0.01672 -0.0339 0.3691 1.0000
8.500 1.3540 0.02415 0.01671 -0.0334 0.3663 1.0000
8.750 1.3801 0.02428 0.01672 -0.0329 0.3634 1.0000
9.000 1.3858 0.02552 0.01819 -0.0313 0.3586 1.0000
9.250 1.4011 0.02611 0.01882 -0.0302 0.3547 1.0000
9.500 1.4233 0.02627 0.01895 -0.0295 0.3515 1.0000
9.750 1.4504 0.02631 0.01888 -0.0291 0.3488 1.0000
10.000 1.4564 0.02750 0.02019 -0.0274 0.3452 1.0000
10.250 1.4537 0.02897 0.02180 -0.0250 0.3412 1.0000
10.500 1.4628 0.02981 0.02269 -0.0235 0.3379 1.0000
10.750 1.4855 0.02998 0.02281 -0.0228 0.3352 1.0000
11.000 1.5209 0.02975 0.02246 -0.0231 0.3327 1.0000
11.250 1.4817 0.03268 0.02559 -0.0183 0.3290 1.0000
11.500 1.4414 0.03679 0.02989 -0.0156 0.3242 1.0000
11.750 1.4544 0.03762 0.03072 -0.0148 0.3213 1.0000
12.000 1.4858 0.03717 0.03023 -0.0144 0.3192 1.0000
12.250 1.5279 0.03621 0.02919 -0.0143 0.3173 1.0000
12.500 1.3040 0.05898 0.05251 -0.0137 0.3037 1.0000
12.750 1.3527 0.05602 0.04951 -0.0127 0.3035 1.0000
13.000 1.4085 0.05250 0.04595 -0.0117 0.3033 1.0000
13.250 1.4578 0.04997 0.04336 -0.0109 0.3025 1.0000
13.500 1.5094 0.04756 0.04089 -0.0103 0.3015 1.0000
13.750 0.7859 0.15983 0.15412 -0.0424 0.2623 1.0000
14.000 0.8028 0.16092 0.15522 -0.0421 0.2594 1.0000
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Polar data table (+)
Polar graphs
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