GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 647 AIRFOIL (goe647-il) Reynolds number: 500,000 Max Cl/Cd: 81.34 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe647-il-500000-n5.txt Download as CSV file: xf-goe647-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 647 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6804 0.06236 0.05903 -0.0819 1.0000 0.0254
-14.250 -0.7181 0.05456 0.05109 -0.0865 1.0000 0.0254
-14.000 -0.7503 0.04810 0.04450 -0.0900 1.0000 0.0254
-13.750 -0.7524 0.04193 0.03816 -0.0980 0.9969 0.0256
-13.500 -0.7464 0.03639 0.03243 -0.1068 0.9882 0.0258
-13.250 -0.7389 0.03247 0.02830 -0.1131 0.9779 0.0260
-13.000 -0.7261 0.03020 0.02587 -0.1156 0.9686 0.0263
-12.750 -0.7107 0.02849 0.02399 -0.1168 0.9583 0.0266
-12.500 -0.6870 0.02685 0.02218 -0.1188 0.9507 0.0269
-12.250 -0.6589 0.02549 0.02064 -0.1210 0.9428 0.0273
-12.000 -0.6311 0.02431 0.01928 -0.1226 0.9337 0.0276
-11.750 -0.6029 0.02303 0.01787 -0.1243 0.9240 0.0279
-11.500 -0.5787 0.02203 0.01678 -0.1248 0.9114 0.0282
-11.250 -0.5549 0.02121 0.01587 -0.1248 0.8990 0.0285
-11.000 -0.5318 0.02055 0.01511 -0.1246 0.8868 0.0287
-10.750 -0.5111 0.01995 0.01441 -0.1237 0.8737 0.0291
-10.500 -0.4902 0.01941 0.01379 -0.1228 0.8619 0.0294
-10.250 -0.4691 0.01889 0.01315 -0.1218 0.8504 0.0298
-10.000 -0.4484 0.01839 0.01255 -0.1207 0.8388 0.0302
-9.750 -0.4273 0.01788 0.01192 -0.1196 0.8281 0.0305
-9.500 -0.4061 0.01739 0.01132 -0.1184 0.8170 0.0308
-9.250 -0.3844 0.01693 0.01075 -0.1173 0.8064 0.0311
-8.750 -0.3398 0.01611 0.00970 -0.1153 0.7847 0.0317
-8.500 -0.3181 0.01564 0.00916 -0.1141 0.7739 0.0321
-8.250 -0.2962 0.01520 0.00865 -0.1130 0.7622 0.0325
-8.000 -0.2734 0.01484 0.00823 -0.1120 0.7499 0.0329
-7.750 -0.2505 0.01455 0.00785 -0.1110 0.7350 0.0334
-7.500 -0.2278 0.01428 0.00748 -0.1099 0.7169 0.0339
-7.250 -0.2052 0.01402 0.00711 -0.1087 0.6978 0.0344
-7.000 -0.1821 0.01378 0.00675 -0.1076 0.6812 0.0349
-6.500 -0.1340 0.01331 0.00609 -0.1059 0.6572 0.0359
-6.250 -0.1097 0.01311 0.00580 -0.1050 0.6459 0.0364
-6.000 -0.0859 0.01283 0.00546 -0.1041 0.6346 0.0370
-5.750 -0.0612 0.01261 0.00519 -0.1033 0.6250 0.0378
-5.500 -0.0365 0.01244 0.00495 -0.1025 0.6152 0.0386
-5.250 -0.0111 0.01227 0.00473 -0.1019 0.6056 0.0396
-4.750 0.0394 0.01198 0.00431 -0.1004 0.5864 0.0419
-4.500 0.0644 0.01183 0.00412 -0.0997 0.5776 0.0434
-4.250 0.0903 0.01169 0.00394 -0.0991 0.5686 0.0452
-3.750 0.1411 0.01146 0.00362 -0.0977 0.5483 0.0505
-3.500 0.1662 0.01136 0.00349 -0.0970 0.5387 0.0551
-3.250 0.1918 0.01124 0.00336 -0.0964 0.5287 0.0624
-3.000 0.2168 0.01114 0.00327 -0.0957 0.5187 0.0746
-2.750 0.2417 0.01106 0.00318 -0.0949 0.5067 0.0884
-2.500 0.2669 0.01100 0.00310 -0.0942 0.4946 0.1004
-2.250 0.2916 0.01095 0.00302 -0.0935 0.4830 0.1124
-2.000 0.3160 0.01086 0.00294 -0.0927 0.4711 0.1310
-1.750 0.3400 0.01072 0.00293 -0.0919 0.4589 0.1776
-1.500 0.3645 0.01074 0.00293 -0.0911 0.4458 0.2012
-1.250 0.3888 0.01078 0.00294 -0.0902 0.4327 0.2174
-1.000 0.4132 0.01082 0.00296 -0.0894 0.4194 0.2324
-0.750 0.4377 0.01085 0.00299 -0.0887 0.4084 0.2511
-0.500 0.4617 0.01089 0.00303 -0.0878 0.3974 0.2708
-0.250 0.4861 0.01094 0.00308 -0.0870 0.3867 0.2864
0.000 0.5103 0.01102 0.00313 -0.0862 0.3766 0.2999
0.250 0.5341 0.01111 0.00318 -0.0853 0.3667 0.3139
0.500 0.5584 0.01117 0.00325 -0.0845 0.3584 0.3287
0.750 0.5822 0.01125 0.00332 -0.0836 0.3506 0.3459
1.000 0.6059 0.01131 0.00341 -0.0827 0.3445 0.3695
1.250 0.6298 0.01136 0.00350 -0.0819 0.3384 0.3981
1.500 0.6529 0.01144 0.00361 -0.0809 0.3326 0.4240
1.750 0.6764 0.01152 0.00372 -0.0800 0.3279 0.4477
2.000 0.7000 0.01158 0.00382 -0.0790 0.3230 0.4714
2.250 0.7225 0.01166 0.00393 -0.0780 0.3178 0.4953
2.500 0.7441 0.01177 0.00406 -0.0767 0.3131 0.5180
2.750 0.7668 0.01179 0.00417 -0.0757 0.3095 0.5493
3.000 0.7868 0.01173 0.00431 -0.0741 0.3059 0.6162
3.250 0.7984 0.01141 0.00447 -0.0707 0.3027 0.7766
3.750 0.9339 0.01185 0.00512 -0.0879 0.2930 1.0000
4.000 0.9552 0.01201 0.00527 -0.0866 0.2900 1.0000
4.250 0.9760 0.01220 0.00542 -0.0852 0.2871 1.0000
4.500 0.9959 0.01240 0.00559 -0.0837 0.2840 1.0000
4.750 1.0137 0.01263 0.00578 -0.0817 0.2810 1.0000
5.000 1.0319 0.01283 0.00595 -0.0799 0.2784 1.0000
5.250 1.0516 0.01299 0.00612 -0.0783 0.2759 1.0000
5.500 1.0708 0.01318 0.00631 -0.0767 0.2734 1.0000
5.750 1.0900 0.01340 0.00651 -0.0752 0.2710 1.0000
6.000 1.1088 0.01364 0.00674 -0.0736 0.2684 1.0000
6.250 1.1273 0.01390 0.00698 -0.0720 0.2661 1.0000
6.500 1.1453 0.01420 0.00726 -0.0703 0.2636 1.0000
6.750 1.1650 0.01445 0.00752 -0.0690 0.2618 1.0000
7.000 1.1853 0.01469 0.00778 -0.0678 0.2600 1.0000
7.250 1.2052 0.01496 0.00806 -0.0666 0.2580 1.0000
7.500 1.2246 0.01525 0.00836 -0.0653 0.2561 1.0000
7.750 1.2436 0.01556 0.00869 -0.0640 0.2539 1.0000
8.000 1.2619 0.01592 0.00904 -0.0627 0.2518 1.0000
8.250 1.2797 0.01631 0.00943 -0.0614 0.2495 1.0000
8.500 1.2965 0.01675 0.00986 -0.0599 0.2472 1.0000
8.750 1.3159 0.01711 0.01025 -0.0589 0.2457 1.0000
9.000 1.3352 0.01747 0.01066 -0.0579 0.2442 1.0000
9.250 1.3540 0.01787 0.01109 -0.0568 0.2426 1.0000
9.500 1.3723 0.01830 0.01155 -0.0558 0.2409 1.0000
9.750 1.3901 0.01877 0.01205 -0.0547 0.2392 1.0000
10.000 1.4075 0.01927 0.01258 -0.0536 0.2375 1.0000
10.250 1.4242 0.01982 0.01315 -0.0525 0.2359 1.0000
10.500 1.4401 0.02042 0.01378 -0.0514 0.2342 1.0000
10.750 1.4554 0.02109 0.01446 -0.0502 0.2325 1.0000
11.000 1.4714 0.02173 0.01514 -0.0492 0.2308 1.0000
11.250 1.4888 0.02230 0.01577 -0.0483 0.2296 1.0000
11.500 1.5058 0.02291 0.01644 -0.0475 0.2281 1.0000
11.750 1.5220 0.02358 0.01716 -0.0467 0.2264 1.0000
12.000 1.5374 0.02430 0.01794 -0.0458 0.2244 1.0000
12.250 1.5512 0.02514 0.01880 -0.0448 0.2216 1.0000
12.500 1.5632 0.02611 0.01979 -0.0438 0.2189 1.0000
12.750 1.5743 0.02718 0.02087 -0.0428 0.2163 1.0000
13.000 1.5896 0.02798 0.02176 -0.0421 0.2143 1.0000
13.250 1.6037 0.02888 0.02273 -0.0415 0.2115 1.0000
13.500 1.6152 0.02998 0.02388 -0.0407 0.2083 1.0000
13.750 1.6241 0.03131 0.02522 -0.0398 0.2049 1.0000
14.000 1.6318 0.03277 0.02670 -0.0389 0.2020 1.0000
14.250 1.6446 0.03385 0.02789 -0.0384 0.1994 1.0000
14.500 1.6556 0.03510 0.02921 -0.0378 0.1970 1.0000
14.750 1.6638 0.03662 0.03078 -0.0372 0.1934 1.0000
15.000 1.6686 0.03848 0.03267 -0.0366 0.1899 1.0000
15.250 1.6751 0.04023 0.03447 -0.0361 0.1873 1.0000
15.500 1.6834 0.04186 0.03618 -0.0357 0.1831 1.0000
15.750 1.6883 0.04381 0.03820 -0.0353 0.1796 1.0000
16.000 1.6865 0.04649 0.04090 -0.0349 0.1750 1.0000
16.250 1.6919 0.04849 0.04298 -0.0346 0.1709 1.0000
16.500 1.6913 0.05116 0.04570 -0.0344 0.1656 1.0000
16.750 1.6871 0.05425 0.04884 -0.0343 0.1605 1.0000
17.000 1.6829 0.05739 0.05203 -0.0342 0.1539 1.0000
17.250 1.6702 0.06160 0.05627 -0.0344 0.1458 1.0000
17.500 1.6585 0.06576 0.06048 -0.0346 0.1397 1.0000
17.750 1.6389 0.07096 0.06571 -0.0351 0.1311 1.0000
18.000 1.6193 0.07631 0.07111 -0.0358 0.1251 1.0000
18.250 1.5978 0.08202 0.07688 -0.0367 0.1186 1.0000
18.500 1.5763 0.08782 0.08276 -0.0378 0.1138 1.0000
18.750 1.5472 0.09482 0.08982 -0.0393 0.1067 1.0000
19.000 1.5274 0.10062 0.09571 -0.0406 0.1035 1.0000
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Polar data table (+)
Polar graphs
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