GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 436 AIRFOIL (goe436-il) Reynolds number: 500,000 Max Cl/Cd: 92.5 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe436-il-500000-n5.txt Download as CSV file: xf-goe436-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 436 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.9437 0.03448 0.03145 -0.0762 1.0000 0.0216
-12.500 -0.9355 0.03339 0.03032 -0.0742 1.0000 0.0221
-12.250 -0.9232 0.03194 0.02878 -0.0732 0.9994 0.0227
-12.000 -0.9014 0.02957 0.02617 -0.0749 0.9967 0.0236
-11.750 -0.8799 0.02698 0.02325 -0.0765 0.9938 0.0246
-11.500 -0.8592 0.02476 0.02069 -0.0772 0.9902 0.0256
-11.250 -0.8283 0.02458 0.02054 -0.0782 0.9878 0.0263
-11.000 -0.7962 0.02432 0.02027 -0.0794 0.9857 0.0270
-10.750 -0.7641 0.02389 0.01977 -0.0808 0.9838 0.0277
-10.500 -0.7388 0.02301 0.01875 -0.0810 0.9793 0.0285
-10.250 -0.7109 0.02187 0.01738 -0.0819 0.9760 0.0296
-10.000 -0.6815 0.02064 0.01590 -0.0831 0.9736 0.0304
-9.750 -0.6528 0.02025 0.01550 -0.0836 0.9699 0.0311
-9.500 -0.6233 0.02006 0.01530 -0.0841 0.9659 0.0317
-9.250 -0.5909 0.01988 0.01510 -0.0852 0.9630 0.0324
-9.000 -0.5580 0.01944 0.01458 -0.0865 0.9603 0.0332
-8.750 -0.5317 0.01884 0.01384 -0.0865 0.9537 0.0341
-8.500 -0.5025 0.01807 0.01290 -0.0871 0.9488 0.0350
-8.250 -0.4717 0.01727 0.01191 -0.0880 0.9454 0.0356
-8.000 -0.4471 0.01652 0.01105 -0.0876 0.9382 0.0363
-7.750 -0.4175 0.01602 0.01049 -0.0882 0.9326 0.0370
-7.500 -0.3889 0.01560 0.01001 -0.0884 0.9251 0.0375
-7.250 -0.3595 0.01516 0.00948 -0.0887 0.9156 0.0380
-7.000 -0.3318 0.01474 0.00897 -0.0887 0.9041 0.0387
-6.750 -0.3038 0.01435 0.00847 -0.0887 0.8926 0.0395
-6.500 -0.2763 0.01394 0.00795 -0.0885 0.8813 0.0403
-6.250 -0.2497 0.01352 0.00740 -0.0882 0.8695 0.0410
-6.000 -0.2235 0.01313 0.00688 -0.0877 0.8578 0.0416
-5.750 -0.1972 0.01279 0.00642 -0.0873 0.8470 0.0422
-5.500 -0.1714 0.01240 0.00592 -0.0868 0.8368 0.0427
-5.250 -0.1462 0.01198 0.00544 -0.0862 0.8261 0.0436
-5.000 -0.1203 0.01173 0.00513 -0.0857 0.8157 0.0444
-4.500 -0.0683 0.01139 0.00467 -0.0846 0.7923 0.0463
-4.250 -0.0423 0.01119 0.00442 -0.0841 0.7816 0.0473
-4.000 -0.0164 0.01099 0.00414 -0.0836 0.7708 0.0482
-3.750 0.0094 0.01079 0.00388 -0.0830 0.7578 0.0492
-3.500 0.0351 0.01063 0.00364 -0.0824 0.7425 0.0500
-3.250 0.0607 0.01051 0.00343 -0.0817 0.7249 0.0506
-3.000 0.0851 0.01024 0.00309 -0.0809 0.7050 0.0522
-2.750 0.1099 0.01014 0.00291 -0.0802 0.6830 0.0536
-2.500 0.1346 0.01012 0.00279 -0.0793 0.6613 0.0552
-2.250 0.1595 0.01009 0.00266 -0.0786 0.6407 0.0567
-2.000 0.1846 0.01006 0.00253 -0.0779 0.6229 0.0582
-1.750 0.2100 0.01003 0.00243 -0.0773 0.6069 0.0595
-1.500 0.2356 0.01002 0.00233 -0.0767 0.5916 0.0605
-1.250 0.2608 0.00993 0.00220 -0.0760 0.5753 0.0632
-1.000 0.2860 0.00991 0.00213 -0.0754 0.5557 0.0659
-0.750 0.3109 0.00995 0.00208 -0.0747 0.5321 0.0686
-0.500 0.3355 0.01002 0.00203 -0.0739 0.5030 0.0709
-0.250 0.3599 0.01012 0.00200 -0.0732 0.4759 0.0731
0.500 0.4349 0.01027 0.00200 -0.0712 0.4271 0.0926
0.750 0.4603 0.01029 0.00203 -0.0707 0.4166 0.1081
1.000 0.4852 0.01028 0.00208 -0.0701 0.4069 0.1439
1.250 0.5098 0.01011 0.00213 -0.0695 0.3987 0.2284
1.500 0.5288 0.00942 0.00222 -0.0681 0.3918 0.5188
1.750 0.5408 0.00850 0.00240 -0.0645 0.3867 0.8679
2.000 0.6321 0.00867 0.00261 -0.0782 0.3763 0.9904
2.250 0.6730 0.00882 0.00270 -0.0810 0.3702 1.0000
2.500 0.6963 0.00893 0.00277 -0.0800 0.3644 1.0000
2.750 0.7188 0.00910 0.00286 -0.0789 0.3574 1.0000
3.000 0.7423 0.00921 0.00295 -0.0779 0.3496 1.0000
3.250 0.7651 0.00937 0.00304 -0.0769 0.3425 1.0000
3.500 0.7888 0.00949 0.00315 -0.0759 0.3380 1.0000
3.750 0.8125 0.00962 0.00326 -0.0750 0.3328 1.0000
4.000 0.8352 0.00980 0.00338 -0.0740 0.3251 1.0000
4.250 0.8589 0.00993 0.00350 -0.0731 0.3175 1.0000
4.500 0.8816 0.01012 0.00363 -0.0721 0.3103 1.0000
4.750 0.9053 0.01026 0.00376 -0.0712 0.3023 1.0000
5.000 0.9279 0.01046 0.00391 -0.0701 0.2946 1.0000
5.250 0.9517 0.01060 0.00406 -0.0693 0.2884 1.0000
5.500 0.9749 0.01078 0.00422 -0.0684 0.2822 1.0000
5.750 0.9981 0.01096 0.00439 -0.0675 0.2765 1.0000
6.000 1.0215 0.01113 0.00457 -0.0666 0.2696 1.0000
6.250 1.0442 0.01134 0.00476 -0.0656 0.2624 1.0000
6.500 1.0672 0.01154 0.00496 -0.0647 0.2539 1.0000
6.750 1.0896 0.01178 0.00518 -0.0637 0.2441 1.0000
7.000 1.1112 0.01206 0.00541 -0.0626 0.2305 1.0000
7.250 1.1319 0.01239 0.00568 -0.0614 0.2135 1.0000
7.500 1.1498 0.01291 0.00605 -0.0597 0.1860 1.0000
7.750 1.1668 0.01350 0.00650 -0.0580 0.1608 1.0000
8.000 1.1842 0.01404 0.00696 -0.0563 0.1416 1.0000
8.250 1.2017 0.01456 0.00741 -0.0546 0.1266 1.0000
8.500 1.2173 0.01518 0.00793 -0.0527 0.1090 1.0000
8.750 1.2285 0.01599 0.00858 -0.0500 0.0768 1.0000
9.000 1.2391 0.01672 0.00920 -0.0472 0.0631 1.0000
9.250 1.2536 0.01722 0.00971 -0.0451 0.0592 1.0000
9.500 1.2678 0.01774 0.01025 -0.0429 0.0564 1.0000
9.750 1.2822 0.01828 0.01081 -0.0408 0.0540 1.0000
10.000 1.2972 0.01878 0.01137 -0.0389 0.0525 1.0000
10.250 1.3129 0.01925 0.01191 -0.0372 0.0509 1.0000
10.500 1.3273 0.01980 0.01251 -0.0354 0.0490 1.0000
10.750 1.3405 0.02043 0.01318 -0.0335 0.0472 1.0000
11.000 1.3524 0.02115 0.01394 -0.0315 0.0456 1.0000
11.250 1.3625 0.02199 0.01484 -0.0294 0.0435 1.0000
11.500 1.3776 0.02256 0.01548 -0.0279 0.0419 1.0000
11.750 1.3904 0.02329 0.01626 -0.0263 0.0398 1.0000
12.000 1.4012 0.02416 0.01717 -0.0246 0.0375 1.0000
12.250 1.4114 0.02511 0.01816 -0.0229 0.0351 1.0000
12.500 1.4218 0.02608 0.01918 -0.0214 0.0312 1.0000
12.750 1.4287 0.02734 0.02044 -0.0198 0.0252 1.0000
13.000 1.4318 0.02895 0.02202 -0.0181 0.0202 1.0000
13.250 1.4338 0.03074 0.02384 -0.0165 0.0176 1.0000
13.500 1.4365 0.03257 0.02573 -0.0152 0.0163 1.0000
13.750 1.4387 0.03454 0.02779 -0.0140 0.0153 1.0000
14.000 1.4395 0.03674 0.03008 -0.0131 0.0144 1.0000
14.250 1.4385 0.03926 0.03268 -0.0124 0.0137 1.0000
14.500 1.4363 0.04205 0.03557 -0.0120 0.0132 1.0000
14.750 1.4359 0.04477 0.03840 -0.0118 0.0127 1.0000
15.000 1.4338 0.04782 0.04156 -0.0119 0.0124 1.0000
15.250 1.4300 0.05120 0.04506 -0.0122 0.0121 1.0000
15.500 1.4251 0.05482 0.04879 -0.0127 0.0118 1.0000
15.750 1.4193 0.05868 0.05275 -0.0134 0.0115 1.0000
16.000 1.4107 0.06307 0.05726 -0.0144 0.0112 1.0000
16.250 1.4026 0.06748 0.06178 -0.0156 0.0110 1.0000
16.500 1.3926 0.07229 0.06670 -0.0170 0.0108 1.0000
16.750 1.3814 0.07739 0.07191 -0.0186 0.0106 1.0000
17.000 1.3704 0.08248 0.07711 -0.0202 0.0105 1.0000
17.250 1.3587 0.08777 0.08251 -0.0220 0.0103 1.0000
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Polar data table (+)
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