GOE 702 AIRFOIL (goe702-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 702 AIRFOIL (goe702-il) Reynolds number: 500,000 Max Cl/Cd: 89.74 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe702-il-500000-n5.txt Download as CSV file: xf-goe702-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 702 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7360 0.07986 0.07620 -0.0656 0.9021 0.0362
-16.000 -0.7638 0.07120 0.06727 -0.0727 0.8805 0.0364
-15.750 -0.7903 0.06459 0.06047 -0.0772 0.8630 0.0366
-15.500 -0.8127 0.05911 0.05486 -0.0804 0.8472 0.0367
-15.000 -0.8696 0.04736 0.04284 -0.0870 0.8160 0.0369
-14.750 -0.9042 0.04064 0.03594 -0.0911 0.7998 0.0370
-14.500 -0.9403 0.03255 0.02755 -0.0982 0.7835 0.0370
-14.250 -0.9529 0.03014 0.02497 -0.0969 0.7705 0.0371
-14.000 -0.9577 0.02862 0.02333 -0.0944 0.7591 0.0373
-13.750 -0.9564 0.02754 0.02213 -0.0918 0.7498 0.0376
-13.500 -0.9473 0.02651 0.02099 -0.0902 0.7410 0.0379
-13.250 -0.9352 0.02560 0.01997 -0.0886 0.7330 0.0383
-13.000 -0.9203 0.02478 0.01905 -0.0874 0.7262 0.0387
-12.750 -0.9040 0.02400 0.01817 -0.0861 0.7197 0.0391
-12.500 -0.8867 0.02326 0.01731 -0.0849 0.7139 0.0395
-12.250 -0.8680 0.02257 0.01651 -0.0839 0.7089 0.0400
-12.000 -0.8482 0.02190 0.01574 -0.0829 0.7041 0.0404
-11.750 -0.8275 0.02129 0.01502 -0.0819 0.6991 0.0408
-11.500 -0.8072 0.02064 0.01429 -0.0809 0.6941 0.0413
-11.250 -0.7862 0.02004 0.01361 -0.0800 0.6891 0.0417
-11.000 -0.7638 0.01949 0.01302 -0.0792 0.6834 0.0423
-10.750 -0.7408 0.01900 0.01246 -0.0784 0.6775 0.0428
-10.500 -0.7174 0.01855 0.01192 -0.0777 0.6722 0.0434
-10.250 -0.6934 0.01811 0.01141 -0.0770 0.6679 0.0441
-10.000 -0.6688 0.01769 0.01092 -0.0764 0.6635 0.0449
-9.750 -0.6439 0.01731 0.01045 -0.0758 0.6585 0.0456
-9.500 -0.6197 0.01686 0.00994 -0.0751 0.6536 0.0463
-9.250 -0.5950 0.01646 0.00948 -0.0745 0.6489 0.0471
-9.000 -0.5694 0.01608 0.00907 -0.0739 0.6440 0.0479
-8.750 -0.5436 0.01573 0.00868 -0.0734 0.6392 0.0489
-8.500 -0.5176 0.01542 0.00829 -0.0729 0.6350 0.0498
-8.250 -0.4914 0.01514 0.00792 -0.0724 0.6313 0.0507
-8.000 -0.4654 0.01479 0.00754 -0.0719 0.6276 0.0517
-7.750 -0.4389 0.01446 0.00720 -0.0715 0.6235 0.0529
-7.500 -0.4122 0.01418 0.00689 -0.0711 0.6188 0.0543
-7.250 -0.3853 0.01394 0.00659 -0.0707 0.6145 0.0557
-7.000 -0.3584 0.01370 0.00628 -0.0702 0.6106 0.0570
-6.750 -0.3314 0.01341 0.00599 -0.0699 0.6067 0.0586
-6.500 -0.3041 0.01317 0.00573 -0.0695 0.6019 0.0603
-6.250 -0.2767 0.01296 0.00548 -0.0692 0.5965 0.0621
-6.000 -0.2495 0.01275 0.00523 -0.0688 0.5915 0.0640
-5.750 -0.2218 0.01254 0.00501 -0.0685 0.5870 0.0665
-5.500 -0.1940 0.01236 0.00481 -0.0682 0.5815 0.0693
-5.250 -0.1664 0.01218 0.00462 -0.0679 0.5754 0.0723
-5.000 -0.1387 0.01203 0.00445 -0.0676 0.5691 0.0758
-4.750 -0.1107 0.01188 0.00429 -0.0674 0.5618 0.0793
-4.500 -0.0828 0.01177 0.00415 -0.0671 0.5542 0.0836
-4.250 -0.0548 0.01165 0.00402 -0.0669 0.5467 0.0875
-4.000 -0.0268 0.01156 0.00390 -0.0666 0.5373 0.0917
-3.750 0.0011 0.01147 0.00377 -0.0663 0.5269 0.0952
-3.500 0.0287 0.01141 0.00366 -0.0660 0.5141 0.0992
-3.250 0.0564 0.01138 0.00356 -0.0657 0.4991 0.1027
-3.000 0.0838 0.01134 0.00345 -0.0654 0.4846 0.1059
-2.750 0.1111 0.01131 0.00338 -0.0651 0.4714 0.1097
-2.500 0.1385 0.01132 0.00332 -0.0648 0.4594 0.1131
-2.250 0.1659 0.01133 0.00326 -0.0645 0.4484 0.1160
-2.000 0.1931 0.01130 0.00321 -0.0641 0.4393 0.1200
-1.750 0.2204 0.01131 0.00318 -0.0639 0.4305 0.1240
-1.500 0.2478 0.01134 0.00315 -0.0636 0.4235 0.1274
-1.250 0.2754 0.01130 0.00312 -0.0633 0.4178 0.1323
-1.000 0.3028 0.01130 0.00311 -0.0630 0.4122 0.1378
-0.750 0.3299 0.01132 0.00311 -0.0627 0.4070 0.1445
-0.500 0.3574 0.01128 0.00310 -0.0625 0.4027 0.1550
-0.250 0.3847 0.01124 0.00311 -0.0622 0.3980 0.1683
0.000 0.4117 0.01123 0.00313 -0.0619 0.3932 0.1845
0.250 0.4383 0.01124 0.00318 -0.0615 0.3889 0.2064
0.500 0.4655 0.01122 0.00324 -0.0613 0.3857 0.2297
0.750 0.4930 0.01122 0.00329 -0.0610 0.3824 0.2481
1.000 0.5204 0.01126 0.00336 -0.0608 0.3789 0.2632
1.250 0.5474 0.01131 0.00343 -0.0605 0.3753 0.2771
1.500 0.5740 0.01139 0.00351 -0.0601 0.3715 0.2891
2.000 0.6282 0.01150 0.00367 -0.0596 0.3652 0.3129
2.250 0.6553 0.01157 0.00375 -0.0593 0.3622 0.3231
2.500 0.6820 0.01163 0.00385 -0.0590 0.3591 0.3344
2.750 0.7085 0.01172 0.00395 -0.0586 0.3561 0.3451
3.000 0.7345 0.01182 0.00406 -0.0582 0.3531 0.3580
3.250 0.7602 0.01191 0.00419 -0.0578 0.3503 0.3761
3.500 0.7866 0.01193 0.00431 -0.0574 0.3479 0.4025
3.750 0.8124 0.01196 0.00443 -0.0570 0.3451 0.4311
4.000 0.8375 0.01198 0.00457 -0.0565 0.3421 0.4683
4.250 0.8581 0.01171 0.00471 -0.0552 0.3395 0.6080
4.750 0.9731 0.01153 0.00528 -0.0674 0.3327 0.9948
5.000 1.0098 0.01169 0.00545 -0.0692 0.3305 1.0000
5.250 1.0331 0.01185 0.00560 -0.0684 0.3281 1.0000
5.500 1.0561 0.01202 0.00576 -0.0674 0.3254 1.0000
5.750 1.0787 0.01221 0.00594 -0.0665 0.3227 1.0000
6.000 1.1007 0.01242 0.00613 -0.0654 0.3202 1.0000
6.250 1.1223 0.01265 0.00633 -0.0643 0.3179 1.0000
6.500 1.1435 0.01290 0.00656 -0.0632 0.3156 1.0000
6.750 1.1662 0.01307 0.00676 -0.0623 0.3138 1.0000
7.000 1.1882 0.01327 0.00697 -0.0613 0.3115 1.0000
7.250 1.2096 0.01348 0.00720 -0.0602 0.3091 1.0000
7.500 1.2303 0.01371 0.00744 -0.0590 0.3066 1.0000
7.750 1.2501 0.01397 0.00769 -0.0577 0.3044 1.0000
8.000 1.2690 0.01425 0.00797 -0.0563 0.3022 1.0000
8.250 1.2864 0.01458 0.00828 -0.0547 0.2999 1.0000
8.500 1.3041 0.01485 0.00858 -0.0531 0.2979 1.0000
8.750 1.3205 0.01510 0.00887 -0.0512 0.2960 1.0000
9.000 1.3362 0.01540 0.00921 -0.0493 0.2939 1.0000
9.250 1.3516 0.01575 0.00958 -0.0476 0.2917 1.0000
9.500 1.3666 0.01616 0.01001 -0.0459 0.2893 1.0000
9.750 1.3811 0.01665 0.01051 -0.0443 0.2869 1.0000
10.000 1.3949 0.01722 0.01107 -0.0428 0.2844 1.0000
10.250 1.4106 0.01775 0.01164 -0.0416 0.2814 1.0000
10.500 1.4272 0.01826 0.01219 -0.0406 0.2779 1.0000
10.750 1.4419 0.01889 0.01285 -0.0395 0.2737 1.0000
11.000 1.4558 0.01960 0.01357 -0.0384 0.2707 1.0000
11.250 1.4682 0.02044 0.01441 -0.0372 0.2676 1.0000
11.500 1.4848 0.02107 0.01510 -0.0364 0.2652 1.0000
11.750 1.5003 0.02178 0.01587 -0.0356 0.2620 1.0000
12.000 1.5138 0.02265 0.01676 -0.0348 0.2584 1.0000
12.250 1.5256 0.02365 0.01777 -0.0339 0.2549 1.0000
12.500 1.5363 0.02475 0.01889 -0.0330 0.2520 1.0000
12.750 1.5510 0.02561 0.01982 -0.0324 0.2488 1.0000
13.000 1.5634 0.02665 0.02091 -0.0317 0.2447 1.0000
13.250 1.5723 0.02797 0.02224 -0.0309 0.2404 1.0000
13.500 1.5797 0.02941 0.02370 -0.0302 0.2363 1.0000
13.750 1.5912 0.03057 0.02493 -0.0296 0.2322 1.0000
14.000 1.5991 0.03204 0.02644 -0.0289 0.2279 1.0000
14.250 1.6038 0.03376 0.02818 -0.0282 0.2237 1.0000
14.500 1.6114 0.03529 0.02976 -0.0276 0.2201 1.0000
14.750 1.6175 0.03701 0.03153 -0.0271 0.2148 1.0000
15.000 1.6182 0.03925 0.03379 -0.0265 0.2096 1.0000
15.250 1.6220 0.04127 0.03586 -0.0261 0.2046 1.0000
15.500 1.6233 0.04356 0.03819 -0.0257 0.1987 1.0000
15.750 1.6203 0.04632 0.04098 -0.0254 0.1931 1.0000
16.000 1.6180 0.04910 0.04379 -0.0251 0.1864 1.0000
16.250 1.6094 0.05259 0.04732 -0.0250 0.1801 1.0000
16.500 1.5986 0.05642 0.05116 -0.0250 0.1711 1.0000
16.750 1.5872 0.06040 0.05518 -0.0251 0.1645 1.0000
17.000 1.5703 0.06513 0.05993 -0.0254 0.1564 1.0000
17.250 1.5537 0.06993 0.06477 -0.0258 0.1483 1.0000
17.500 1.5312 0.07556 0.07042 -0.0266 0.1396 1.0000
17.750 1.5067 0.08155 0.07644 -0.0275 0.1313 1.0000
18.000 1.4843 0.08741 0.08232 -0.0285 0.1225 1.0000
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