GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 596 AIRFOIL (goe596-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.48 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe596-il-1000000-n5.txt Download as CSV file: xf-goe596-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4143 0.09391 0.09217 -0.0345 1.0000 0.0132
-10.250 -0.4089 0.09153 0.08979 -0.0353 1.0000 0.0134
-10.000 -0.4048 0.08897 0.08726 -0.0361 1.0000 0.0135
-9.750 -0.4009 0.08656 0.08485 -0.0367 1.0000 0.0137
-9.500 -0.3971 0.08356 0.08188 -0.0382 0.9997 0.0139
-9.250 -0.3898 0.07980 0.07813 -0.0414 0.9889 0.0142
-8.750 -0.4816 0.02082 0.01723 -0.0926 0.9059 0.0198
-8.500 -0.4644 0.01891 0.01501 -0.0918 0.8926 0.0201
-8.250 -0.4417 0.01819 0.01415 -0.0912 0.8815 0.0204
-8.000 -0.4181 0.01765 0.01349 -0.0906 0.8704 0.0205
-7.750 -0.3944 0.01707 0.01278 -0.0900 0.8597 0.0207
-7.500 -0.3701 0.01661 0.01221 -0.0895 0.8496 0.0209
-7.250 -0.3460 0.01608 0.01155 -0.0889 0.8390 0.0211
-7.000 -0.3211 0.01562 0.01098 -0.0885 0.8299 0.0214
-6.750 -0.2966 0.01509 0.01031 -0.0879 0.8207 0.0216
-6.500 -0.2718 0.01450 0.00959 -0.0874 0.8112 0.0220
-6.250 -0.2474 0.01378 0.00872 -0.0869 0.8016 0.0222
-6.000 -0.2227 0.01319 0.00797 -0.0863 0.7903 0.0225
-5.750 -0.1975 0.01262 0.00727 -0.0858 0.7780 0.0228
-5.500 -0.1723 0.01210 0.00661 -0.0852 0.7645 0.0231
-5.250 -0.1469 0.01168 0.00607 -0.0847 0.7495 0.0233
-5.000 -0.1215 0.01133 0.00558 -0.0842 0.7311 0.0236
-4.750 -0.0961 0.01110 0.00523 -0.0836 0.7078 0.0239
-4.500 -0.0710 0.01094 0.00491 -0.0830 0.6803 0.0241
-4.250 -0.0456 0.01077 0.00460 -0.0824 0.6567 0.0242
-4.000 -0.0206 0.01034 0.00405 -0.0818 0.6388 0.0245
-3.750 0.0046 0.00998 0.00358 -0.0812 0.6229 0.0249
-3.500 0.0303 0.00975 0.00326 -0.0808 0.6080 0.0252
-3.250 0.0564 0.00959 0.00303 -0.0803 0.5938 0.0255
-3.000 0.0827 0.00944 0.00282 -0.0799 0.5812 0.0258
-2.750 0.1090 0.00932 0.00263 -0.0796 0.5697 0.0261
-2.500 0.1359 0.00917 0.00245 -0.0793 0.5613 0.0265
-2.000 0.1897 0.00891 0.00213 -0.0787 0.5481 0.0272
-1.750 0.2167 0.00880 0.00198 -0.0784 0.5414 0.0277
-1.500 0.2437 0.00871 0.00186 -0.0782 0.5362 0.0282
-1.250 0.2710 0.00863 0.00177 -0.0779 0.5310 0.0288
-1.000 0.2981 0.00856 0.00167 -0.0777 0.5251 0.0293
-0.750 0.3253 0.00850 0.00159 -0.0775 0.5198 0.0296
-0.500 0.3525 0.00841 0.00148 -0.0772 0.5142 0.0302
-0.250 0.3795 0.00834 0.00139 -0.0770 0.5090 0.0311
0.000 0.4067 0.00829 0.00134 -0.0767 0.5044 0.0322
0.250 0.4341 0.00825 0.00130 -0.0766 0.4995 0.0334
0.500 0.4613 0.00823 0.00128 -0.0763 0.4937 0.0347
0.750 0.4885 0.00823 0.00126 -0.0761 0.4878 0.0361
1.000 0.5156 0.00821 0.00125 -0.0759 0.4801 0.0403
1.250 0.5425 0.00821 0.00126 -0.0756 0.4727 0.0504
1.500 0.5690 0.00807 0.00128 -0.0754 0.4657 0.1134
1.750 0.5944 0.00786 0.00133 -0.0750 0.4576 0.2362
2.000 0.6183 0.00746 0.00141 -0.0744 0.4479 0.4396
2.500 0.7132 0.00645 0.00168 -0.0833 0.4198 1.0000
2.750 0.7367 0.00663 0.00175 -0.0824 0.3994 1.0000
3.000 0.7604 0.00681 0.00184 -0.0816 0.3807 1.0000
3.250 0.7836 0.00705 0.00195 -0.0806 0.3576 1.0000
3.500 0.8071 0.00726 0.00208 -0.0797 0.3402 1.0000
3.750 0.8313 0.00744 0.00220 -0.0790 0.3274 1.0000
4.000 0.8551 0.00765 0.00233 -0.0781 0.3124 1.0000
4.250 0.8792 0.00783 0.00247 -0.0774 0.3013 1.0000
4.500 0.9032 0.00803 0.00261 -0.0766 0.2887 1.0000
4.750 0.9267 0.00828 0.00277 -0.0758 0.2712 1.0000
5.000 0.9498 0.00855 0.00296 -0.0749 0.2511 1.0000
5.250 0.9723 0.00888 0.00317 -0.0740 0.2273 1.0000
5.500 0.9928 0.00937 0.00347 -0.0727 0.1910 1.0000
5.750 1.0137 0.00982 0.00379 -0.0715 0.1644 1.0000
6.000 1.0355 0.01022 0.00408 -0.0705 0.1453 1.0000
6.250 1.0560 0.01071 0.00442 -0.0693 0.1177 1.0000
6.500 1.0691 0.01177 0.00513 -0.0669 0.0531 1.0000
6.750 1.0909 0.01214 0.00546 -0.0659 0.0446 1.0000
7.000 1.1131 0.01247 0.00577 -0.0649 0.0402 1.0000
7.250 1.1359 0.01275 0.00606 -0.0641 0.0381 1.0000
7.500 1.1582 0.01305 0.00636 -0.0632 0.0361 1.0000
7.750 1.1800 0.01339 0.00670 -0.0622 0.0341 1.0000
8.000 1.2012 0.01375 0.00706 -0.0611 0.0321 1.0000
8.250 1.2229 0.01405 0.00739 -0.0602 0.0312 1.0000
8.500 1.2445 0.01436 0.00772 -0.0592 0.0303 1.0000
8.750 1.2653 0.01469 0.00807 -0.0581 0.0292 1.0000
9.000 1.2854 0.01505 0.00845 -0.0569 0.0280 1.0000
9.250 1.3046 0.01545 0.00886 -0.0556 0.0268 1.0000
9.500 1.3224 0.01591 0.00933 -0.0540 0.0254 1.0000
9.750 1.3412 0.01624 0.00971 -0.0526 0.0249 1.0000
10.000 1.3579 0.01660 0.01010 -0.0508 0.0241 1.0000
10.250 1.3735 0.01698 0.01051 -0.0489 0.0231 1.0000
10.500 1.3885 0.01741 0.01096 -0.0469 0.0220 1.0000
10.750 1.4022 0.01792 0.01148 -0.0448 0.0207 1.0000
11.000 1.4168 0.01840 0.01200 -0.0429 0.0198 1.0000
11.250 1.4311 0.01892 0.01255 -0.0411 0.0188 1.0000
11.500 1.4444 0.01950 0.01316 -0.0392 0.0177 1.0000
11.750 1.4568 0.02015 0.01383 -0.0373 0.0167 1.0000
12.000 1.4687 0.02086 0.01458 -0.0355 0.0157 1.0000
12.250 1.4802 0.02162 0.01538 -0.0337 0.0146 1.0000
12.500 1.4905 0.02249 0.01629 -0.0319 0.0137 1.0000
12.750 1.4998 0.02348 0.01731 -0.0301 0.0128 1.0000
13.000 1.5091 0.02450 0.01839 -0.0285 0.0122 1.0000
13.250 1.5179 0.02562 0.01957 -0.0270 0.0117 1.0000
13.500 1.5254 0.02690 0.02090 -0.0256 0.0110 1.0000
13.750 1.5321 0.02830 0.02236 -0.0242 0.0106 1.0000
14.000 1.5372 0.02991 0.02403 -0.0230 0.0100 1.0000
14.250 1.5425 0.03157 0.02576 -0.0219 0.0097 1.0000
14.500 1.5476 0.03334 0.02760 -0.0210 0.0094 1.0000
14.750 1.5519 0.03525 0.02959 -0.0202 0.0090 1.0000
15.000 1.5550 0.03737 0.03179 -0.0196 0.0088 1.0000
15.250 1.5570 0.03969 0.03418 -0.0192 0.0085 1.0000
15.500 1.5579 0.04223 0.03681 -0.0190 0.0082 1.0000
15.750 1.5571 0.04502 0.03968 -0.0189 0.0079 1.0000
16.000 1.5549 0.04809 0.04283 -0.0189 0.0076 1.0000
16.250 1.5525 0.05124 0.04607 -0.0192 0.0075 1.0000
16.500 1.5504 0.05443 0.04935 -0.0195 0.0073 1.0000
16.750 1.5476 0.05777 0.05278 -0.0199 0.0072 1.0000
17.000 1.5437 0.06133 0.05644 -0.0205 0.0071 1.0000
17.250 1.5395 0.06496 0.06016 -0.0212 0.0070 1.0000
17.500 1.5346 0.06877 0.06407 -0.0220 0.0069 1.0000
17.750 1.5274 0.07300 0.06840 -0.0230 0.0068 1.0000
18.000 1.5212 0.07718 0.07268 -0.0241 0.0066 1.0000
18.250 1.5140 0.08160 0.07719 -0.0255 0.0065 1.0000
18.500 1.5051 0.08640 0.08209 -0.0270 0.0065 1.0000
18.750 1.4973 0.09111 0.08690 -0.0287 0.0063 1.0000
19.000 1.4875 0.09627 0.09217 -0.0306 0.0063 1.0000
19.250 1.4789 0.10131 0.09730 -0.0326 0.0062 1.0000
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