GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 596 AIRFOIL (goe596-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.73 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe596-il-1000000.txt Download as CSV file: xf-goe596-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 596 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2822 0.09731 0.09570 -0.0359 1.0000 0.0201
-10.250 -0.2832 0.09323 0.09162 -0.0369 1.0000 0.0201
-10.000 -0.2842 0.08920 0.08761 -0.0377 1.0000 0.0201
-9.750 -0.2888 0.08445 0.08287 -0.0380 1.0000 0.0204
-9.500 -0.2848 0.08196 0.08040 -0.0375 1.0000 0.0205
-9.250 -0.2814 0.07957 0.07803 -0.0370 1.0000 0.0207
-9.000 -0.2805 0.07708 0.07556 -0.0365 1.0000 0.0209
-8.750 -0.2701 0.07363 0.07211 -0.0387 0.9986 0.0213
-8.500 -0.2603 0.06969 0.06817 -0.0417 0.9936 0.0218
-8.250 -0.2532 0.06535 0.06383 -0.0450 0.9874 0.0229
-7.250 -0.2806 0.04445 0.04248 -0.0849 0.9608 0.0247
-7.000 -0.2537 0.04244 0.04040 -0.0879 0.9518 0.0251
-6.750 -0.2282 0.04025 0.03811 -0.0903 0.9396 0.0254
-6.500 -0.2068 0.03825 0.03599 -0.0914 0.9248 0.0261
-6.250 -0.1884 0.03313 0.03042 -0.0918 0.9076 0.0291
-6.000 -0.1752 0.02959 0.02650 -0.0909 0.8927 0.0292
-5.750 -0.1708 0.02347 0.01992 -0.0897 0.8786 0.0301
-5.500 -0.1484 0.02258 0.01897 -0.0892 0.8671 0.0305
-5.250 -0.1255 0.02183 0.01814 -0.0888 0.8564 0.0310
-5.000 -0.1025 0.02100 0.01718 -0.0882 0.8458 0.0318
-4.750 -0.0871 0.01565 0.01099 -0.0856 0.8349 0.0286
-4.500 -0.0633 0.01443 0.00953 -0.0848 0.8239 0.0288
-4.250 -0.0379 0.01406 0.00894 -0.0842 0.8120 0.0294
-4.000 -0.0143 0.01251 0.00716 -0.0834 0.7997 0.0297
-3.750 0.0106 0.01162 0.00613 -0.0827 0.7849 0.0299
-3.500 0.0356 0.01093 0.00532 -0.0821 0.7669 0.0301
-3.250 0.0605 0.01043 0.00470 -0.0813 0.7419 0.0304
-3.000 0.0850 0.01008 0.00421 -0.0805 0.7111 0.0307
-2.750 0.1094 0.00982 0.00381 -0.0797 0.6794 0.0311
-2.500 0.1345 0.00961 0.00348 -0.0791 0.6559 0.0315
-2.250 0.1602 0.00946 0.00325 -0.0785 0.6382 0.0323
-2.000 0.1861 0.00928 0.00300 -0.0780 0.6240 0.0330
-1.750 0.2121 0.00909 0.00274 -0.0775 0.6118 0.0336
-1.500 0.2385 0.00892 0.00251 -0.0771 0.6016 0.0342
-1.250 0.2650 0.00877 0.00232 -0.0767 0.5931 0.0346
-1.000 0.2916 0.00866 0.00217 -0.0764 0.5846 0.0351
-0.750 0.3180 0.00848 0.00195 -0.0760 0.5773 0.0356
-0.500 0.3443 0.00826 0.00169 -0.0756 0.5697 0.0372
-0.250 0.3711 0.00818 0.00159 -0.0752 0.5631 0.0387
0.000 0.3983 0.00812 0.00153 -0.0750 0.5569 0.0406
0.250 0.4252 0.00809 0.00147 -0.0747 0.5507 0.0422
0.500 0.4524 0.00800 0.00137 -0.0745 0.5450 0.0456
0.750 0.4794 0.00795 0.00133 -0.0742 0.5387 0.0511
1.000 0.5043 0.00759 0.00132 -0.0737 0.5324 0.1984
1.250 0.5258 0.00680 0.00139 -0.0728 0.5262 0.5209
1.500 0.5854 0.00581 0.00156 -0.0797 0.5179 0.9901
1.750 0.6349 0.00587 0.00158 -0.0845 0.5096 1.0000
2.000 0.6591 0.00597 0.00161 -0.0836 0.5023 1.0000
2.250 0.6843 0.00602 0.00165 -0.0830 0.4959 1.0000
2.500 0.7089 0.00611 0.00169 -0.0822 0.4886 1.0000
2.750 0.7340 0.00618 0.00174 -0.0816 0.4806 1.0000
3.000 0.7584 0.00629 0.00179 -0.0808 0.4696 1.0000
3.250 0.7831 0.00639 0.00185 -0.0801 0.4576 1.0000
3.500 0.8073 0.00653 0.00192 -0.0793 0.4410 1.0000
3.750 0.8321 0.00665 0.00200 -0.0786 0.4278 1.0000
4.000 0.8562 0.00682 0.00210 -0.0778 0.4113 1.0000
4.250 0.8801 0.00700 0.00221 -0.0770 0.3938 1.0000
4.500 0.9041 0.00720 0.00234 -0.0762 0.3769 1.0000
4.750 0.9274 0.00743 0.00249 -0.0753 0.3570 1.0000
5.000 0.9506 0.00769 0.00266 -0.0744 0.3383 1.0000
5.250 0.9742 0.00792 0.00283 -0.0736 0.3228 1.0000
5.500 0.9976 0.00817 0.00301 -0.0728 0.3069 1.0000
5.750 1.0208 0.00845 0.00321 -0.0719 0.2890 1.0000
6.000 1.0431 0.00879 0.00344 -0.0710 0.2623 1.0000
6.250 1.0633 0.00930 0.00375 -0.0697 0.2213 1.0000
6.500 1.0798 0.01010 0.00424 -0.0678 0.1671 1.0000
6.750 1.0956 0.01095 0.00479 -0.0659 0.1157 1.0000
7.000 1.1062 0.01220 0.00564 -0.0631 0.0491 1.0000
7.250 1.1276 0.01259 0.00602 -0.0620 0.0441 1.0000
7.500 1.1485 0.01302 0.00644 -0.0608 0.0399 1.0000
7.750 1.1707 0.01333 0.00677 -0.0599 0.0383 1.0000
8.000 1.1919 0.01369 0.00716 -0.0588 0.0364 1.0000
8.250 1.2117 0.01415 0.00762 -0.0575 0.0343 1.0000
8.500 1.2307 0.01464 0.00815 -0.0561 0.0325 1.0000
8.750 1.2516 0.01497 0.00851 -0.0550 0.0316 1.0000
9.000 1.2716 0.01535 0.00892 -0.0537 0.0304 1.0000
9.250 1.2905 0.01576 0.00935 -0.0524 0.0291 1.0000
9.500 1.3067 0.01631 0.00992 -0.0506 0.0277 1.0000
9.750 1.3183 0.01699 0.01065 -0.0479 0.0264 1.0000
10.000 1.3344 0.01735 0.01106 -0.0460 0.0258 1.0000
10.250 1.3499 0.01775 0.01149 -0.0441 0.0249 1.0000
10.500 1.3650 0.01818 0.01194 -0.0422 0.0239 1.0000
10.750 1.3779 0.01874 0.01252 -0.0400 0.0230 1.0000
11.000 1.3855 0.01960 0.01343 -0.0372 0.0219 1.0000
11.250 1.3954 0.02037 0.01426 -0.0349 0.0212 1.0000
11.500 1.4093 0.02097 0.01491 -0.0333 0.0207 1.0000
11.750 1.4220 0.02166 0.01564 -0.0315 0.0199 1.0000
12.000 1.4342 0.02240 0.01643 -0.0299 0.0193 1.0000
12.250 1.4458 0.02322 0.01728 -0.0283 0.0185 1.0000
12.500 1.4504 0.02455 0.01865 -0.0262 0.0177 1.0000
12.750 1.4555 0.02594 0.02011 -0.0243 0.0172 1.0000
13.000 1.4659 0.02700 0.02125 -0.0231 0.0167 1.0000
13.250 1.4758 0.02816 0.02246 -0.0220 0.0162 1.0000
13.500 1.4844 0.02947 0.02383 -0.0209 0.0157 1.0000
13.750 1.4912 0.03100 0.02543 -0.0198 0.0153 1.0000
14.000 1.4964 0.03274 0.02722 -0.0189 0.0149 1.0000
14.250 1.4978 0.03493 0.02947 -0.0181 0.0144 1.0000
14.500 1.4893 0.03825 0.03289 -0.0173 0.0139 1.0000
14.750 1.4933 0.04044 0.03517 -0.0170 0.0137 1.0000
15.000 1.4966 0.04278 0.03760 -0.0168 0.0135 1.0000
15.250 1.4993 0.04523 0.04014 -0.0167 0.0132 1.0000
15.500 1.4996 0.04803 0.04302 -0.0168 0.0129 1.0000
15.750 1.5010 0.05076 0.04584 -0.0170 0.0126 1.0000
16.000 1.5009 0.05373 0.04888 -0.0173 0.0123 1.0000
16.250 1.5016 0.05663 0.05185 -0.0177 0.0120 1.0000
16.500 1.4972 0.06026 0.05555 -0.0183 0.0118 1.0000
16.750 1.4911 0.06416 0.05955 -0.0191 0.0116 1.0000
17.000 1.4833 0.06837 0.06384 -0.0200 0.0114 1.0000
17.250 1.4712 0.07326 0.06883 -0.0212 0.0112 1.0000
17.500 1.4562 0.07870 0.07437 -0.0226 0.0110 1.0000
17.750 1.4497 0.08306 0.07883 -0.0239 0.0109 1.0000
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