GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 693 AIRFOIL (goe693-il) Reynolds number: 200,000 Max Cl/Cd: 72.51 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe693-il-200000-n5.txt Download as CSV file: xf-goe693-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 693 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6725 0.05235 0.04856 -0.0727 1.0000 0.0332
-10.500 -0.7258 0.04566 0.04158 -0.0708 1.0000 0.0331
-10.250 -0.7421 0.03851 0.03369 -0.0729 0.9953 0.0337
-10.000 -0.7238 0.03528 0.03013 -0.0750 0.9905 0.0345
-9.750 -0.6957 0.03413 0.02894 -0.0766 0.9867 0.0354
-9.500 -0.6669 0.03271 0.02736 -0.0786 0.9836 0.0365
-9.250 -0.6431 0.03079 0.02516 -0.0797 0.9781 0.0376
-9.000 -0.6159 0.02866 0.02265 -0.0814 0.9742 0.0388
-8.750 -0.5883 0.02689 0.02051 -0.0827 0.9701 0.0401
-8.500 -0.5613 0.02542 0.01869 -0.0835 0.9646 0.0410
-8.250 -0.5316 0.02395 0.01711 -0.0848 0.9608 0.0421
-8.000 -0.5038 0.02299 0.01605 -0.0854 0.9550 0.0430
-7.750 -0.4750 0.02211 0.01505 -0.0861 0.9492 0.0441
-7.500 -0.4435 0.02127 0.01405 -0.0872 0.9452 0.0456
-7.250 -0.4181 0.02047 0.01310 -0.0870 0.9369 0.0470
-7.000 -0.3883 0.01961 0.01206 -0.0876 0.9312 0.0483
-6.750 -0.3615 0.01888 0.01116 -0.0875 0.9231 0.0493
-6.500 -0.3338 0.01805 0.01030 -0.0877 0.9161 0.0508
-6.250 -0.3068 0.01748 0.00968 -0.0876 0.9079 0.0524
-6.000 -0.2785 0.01697 0.00909 -0.0878 0.9002 0.0546
-5.750 -0.2514 0.01649 0.00851 -0.0876 0.8911 0.0572
-5.500 -0.2232 0.01594 0.00789 -0.0876 0.8836 0.0598
-5.250 -0.1965 0.01552 0.00745 -0.0874 0.8741 0.0628
-5.000 -0.1684 0.01513 0.00698 -0.0874 0.8662 0.0668
-4.750 -0.1412 0.01476 0.00658 -0.0872 0.8568 0.0712
-4.500 -0.1135 0.01449 0.00628 -0.0871 0.8482 0.0771
-4.250 -0.0858 0.01423 0.00598 -0.0870 0.8397 0.0841
-4.000 -0.0580 0.01406 0.00573 -0.0869 0.8314 0.0920
-3.750 -0.0303 0.01383 0.00547 -0.0868 0.8234 0.0991
-3.500 -0.0027 0.01367 0.00524 -0.0867 0.8150 0.1065
-3.250 0.0250 0.01347 0.00500 -0.0866 0.8076 0.1137
-3.000 0.0526 0.01333 0.00482 -0.0865 0.8001 0.1217
-2.750 0.0802 0.01316 0.00462 -0.0865 0.7930 0.1294
-2.500 0.1079 0.01302 0.00446 -0.0864 0.7860 0.1378
-2.250 0.1354 0.01286 0.00430 -0.0863 0.7787 0.1458
-2.000 0.1631 0.01274 0.00414 -0.0862 0.7716 0.1552
-1.750 0.1903 0.01259 0.00401 -0.0861 0.7631 0.1661
-1.500 0.2177 0.01246 0.00388 -0.0859 0.7552 0.1789
-1.250 0.2450 0.01231 0.00378 -0.0858 0.7469 0.1972
-1.000 0.2723 0.01216 0.00368 -0.0857 0.7395 0.2243
-0.750 0.2993 0.01198 0.00362 -0.0855 0.7314 0.2635
-0.500 0.3260 0.01177 0.00356 -0.0854 0.7237 0.3204
-0.250 0.3515 0.01141 0.00353 -0.0850 0.7144 0.4191
0.000 0.3746 0.01088 0.00354 -0.0841 0.7058 0.5838
0.250 0.3953 0.01035 0.00362 -0.0820 0.6978 0.7688
0.500 0.4380 0.01018 0.00370 -0.0843 0.6892 0.9294
0.750 0.4800 0.01023 0.00367 -0.0872 0.6799 0.9794
1.000 0.5211 0.01029 0.00367 -0.0901 0.6709 1.0000
1.250 0.5465 0.01037 0.00367 -0.0895 0.6635 1.0000
1.500 0.5719 0.01045 0.00370 -0.0890 0.6555 1.0000
1.750 0.5974 0.01055 0.00373 -0.0885 0.6480 1.0000
2.000 0.6229 0.01064 0.00379 -0.0880 0.6400 1.0000
2.250 0.6485 0.01074 0.00383 -0.0875 0.6316 1.0000
2.500 0.6740 0.01084 0.00391 -0.0870 0.6221 1.0000
2.750 0.6994 0.01095 0.00397 -0.0864 0.6114 1.0000
3.000 0.7246 0.01106 0.00403 -0.0858 0.5987 1.0000
3.250 0.7497 0.01118 0.00412 -0.0853 0.5851 1.0000
3.500 0.7750 0.01132 0.00423 -0.0847 0.5719 1.0000
3.750 0.8002 0.01146 0.00434 -0.0842 0.5582 1.0000
4.000 0.8251 0.01162 0.00447 -0.0836 0.5429 1.0000
4.250 0.8496 0.01181 0.00460 -0.0829 0.5250 1.0000
4.500 0.8730 0.01204 0.00474 -0.0820 0.5010 1.0000
4.750 0.8949 0.01236 0.00491 -0.0809 0.4700 1.0000
5.000 0.9163 0.01273 0.00514 -0.0797 0.4411 1.0000
5.250 0.9380 0.01311 0.00540 -0.0787 0.4175 1.0000
5.500 0.9595 0.01352 0.00570 -0.0776 0.3969 1.0000
5.750 0.9812 0.01391 0.00602 -0.0766 0.3787 1.0000
6.000 1.0033 0.01429 0.00636 -0.0756 0.3647 1.0000
6.250 1.0253 0.01468 0.00671 -0.0747 0.3510 1.0000
6.500 1.0473 0.01506 0.00708 -0.0737 0.3378 1.0000
6.750 1.0692 0.01544 0.00747 -0.0728 0.3257 1.0000
7.000 1.0905 0.01584 0.00787 -0.0717 0.3139 1.0000
7.250 1.1111 0.01628 0.00829 -0.0706 0.3001 1.0000
7.500 1.1314 0.01671 0.00872 -0.0694 0.2853 1.0000
7.750 1.1516 0.01714 0.00917 -0.0682 0.2697 1.0000
8.000 1.1706 0.01761 0.00964 -0.0669 0.2503 1.0000
8.250 1.1869 0.01821 0.01017 -0.0651 0.2271 1.0000
8.500 1.2009 0.01891 0.01076 -0.0631 0.2048 1.0000
8.750 1.2114 0.01971 0.01146 -0.0605 0.1882 1.0000
9.000 1.2218 0.02053 0.01222 -0.0579 0.1751 1.0000
9.250 1.2337 0.02133 0.01300 -0.0557 0.1642 1.0000
9.500 1.2442 0.02224 0.01388 -0.0534 0.1552 1.0000
9.750 1.2603 0.02287 0.01460 -0.0519 0.1462 1.0000
10.000 1.2739 0.02366 0.01542 -0.0502 0.1366 1.0000
10.250 1.2882 0.02442 0.01623 -0.0486 0.1230 1.0000
10.500 1.3004 0.02534 0.01712 -0.0469 0.1047 1.0000
10.750 1.3081 0.02660 0.01825 -0.0449 0.0901 1.0000
11.000 1.3152 0.02796 0.01957 -0.0429 0.0802 1.0000
11.250 1.3242 0.02923 0.02089 -0.0412 0.0704 1.0000
11.500 1.3316 0.03068 0.02236 -0.0394 0.0567 1.0000
11.750 1.3342 0.03257 0.02414 -0.0375 0.0412 1.0000
12.000 1.3367 0.03454 0.02608 -0.0357 0.0342 1.0000
12.250 1.3403 0.03648 0.02808 -0.0342 0.0303 1.0000
12.500 1.3431 0.03856 0.03023 -0.0328 0.0278 1.0000
12.750 1.3453 0.04075 0.03251 -0.0315 0.0261 1.0000
13.000 1.3487 0.04290 0.03478 -0.0305 0.0246 1.0000
13.250 1.3504 0.04526 0.03726 -0.0295 0.0234 1.0000
13.500 1.3497 0.04793 0.04004 -0.0287 0.0224 1.0000
13.750 1.3464 0.05095 0.04316 -0.0280 0.0215 1.0000
14.000 1.3470 0.05365 0.04600 -0.0275 0.0207 1.0000
14.250 1.3460 0.05661 0.04910 -0.0272 0.0200 1.0000
14.500 1.3438 0.05981 0.05243 -0.0270 0.0194 1.0000
14.750 1.3406 0.06324 0.05598 -0.0270 0.0189 1.0000
15.000 1.3364 0.06690 0.05976 -0.0272 0.0185 1.0000
15.250 1.3309 0.07082 0.06380 -0.0276 0.0181 1.0000
15.500 1.3242 0.07503 0.06813 -0.0283 0.0177 1.0000
15.750 1.3163 0.07953 0.07273 -0.0291 0.0174 1.0000
16.000 1.3079 0.08418 0.07748 -0.0301 0.0171 1.0000
16.250 1.3034 0.08838 0.08183 -0.0311 0.0169 1.0000
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