GOE 770 AIRFOIL (goe770-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 770 AIRFOIL (goe770-il) Reynolds number: 200,000 Max Cl/Cd: 59.33 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe770-il-200000-n5.txt Download as CSV file: xf-goe770-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 770 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.8142 0.09585 0.09079 -0.0475 1.0000 0.0385
-17.500 -0.8547 0.08514 0.07975 -0.0545 1.0000 0.0387
-17.250 -0.8813 0.07747 0.07179 -0.0592 1.0000 0.0390
-17.000 -0.8912 0.07270 0.06688 -0.0618 1.0000 0.0393
-16.750 -0.8911 0.06952 0.06367 -0.0633 1.0000 0.0396
-16.500 -0.8916 0.06632 0.06041 -0.0647 1.0000 0.0399
-16.250 -0.8928 0.06312 0.05713 -0.0661 1.0000 0.0402
-16.000 -0.8943 0.05997 0.05390 -0.0674 1.0000 0.0405
-15.750 -0.8952 0.05695 0.05078 -0.0685 1.0000 0.0409
-15.500 -0.8952 0.05408 0.04781 -0.0695 1.0000 0.0413
-15.250 -0.8943 0.05137 0.04499 -0.0703 1.0000 0.0418
-15.000 -0.8927 0.04878 0.04227 -0.0710 1.0000 0.0423
-14.750 -0.8902 0.04632 0.03966 -0.0715 1.0000 0.0429
-14.500 -0.8870 0.04400 0.03717 -0.0718 1.0000 0.0435
-14.250 -0.8786 0.04222 0.03537 -0.0718 1.0000 0.0440
-14.000 -0.8689 0.04065 0.03381 -0.0718 1.0000 0.0445
-13.750 -0.8564 0.03911 0.03223 -0.0725 0.9422 0.0450
-13.500 -0.8435 0.03771 0.03059 -0.0725 0.8562 0.0456
-13.250 -0.8353 0.03646 0.02910 -0.0713 0.8110 0.0462
-13.000 -0.8256 0.03521 0.02764 -0.0704 0.7800 0.0469
-12.750 -0.8148 0.03401 0.02621 -0.0696 0.7552 0.0477
-12.500 -0.8028 0.03285 0.02481 -0.0687 0.7350 0.0486
-12.250 -0.7899 0.03181 0.02370 -0.0680 0.7182 0.0492
-12.000 -0.7764 0.03085 0.02264 -0.0672 0.7040 0.0500
-11.750 -0.7621 0.02992 0.02161 -0.0664 0.6925 0.0508
-11.500 -0.7472 0.02903 0.02059 -0.0655 0.6824 0.0518
-11.250 -0.7314 0.02816 0.01960 -0.0646 0.6739 0.0528
-11.000 -0.7150 0.02734 0.01863 -0.0637 0.6656 0.0539
-10.500 -0.6835 0.02586 0.01706 -0.0615 0.6515 0.0559
-10.250 -0.6677 0.02526 0.01638 -0.0601 0.6448 0.0573
-10.000 -0.6516 0.02471 0.01571 -0.0587 0.6390 0.0588
-9.750 -0.6343 0.02413 0.01505 -0.0574 0.6341 0.0602
-9.500 -0.6158 0.02355 0.01447 -0.0563 0.6291 0.0616
-9.250 -0.5963 0.02303 0.01390 -0.0553 0.6242 0.0633
-9.000 -0.5760 0.02255 0.01332 -0.0543 0.6195 0.0654
-8.750 -0.5561 0.02207 0.01278 -0.0533 0.6151 0.0673
-8.500 -0.5348 0.02163 0.01232 -0.0525 0.6108 0.0697
-8.250 -0.5127 0.02121 0.01184 -0.0517 0.6062 0.0725
-8.000 -0.4912 0.02076 0.01138 -0.0509 0.6020 0.0750
-7.750 -0.4688 0.02038 0.01096 -0.0501 0.5982 0.0780
-7.500 -0.4458 0.02005 0.01054 -0.0494 0.5946 0.0814
-7.250 -0.4233 0.01967 0.01014 -0.0486 0.5911 0.0849
-7.000 -0.3991 0.01936 0.00979 -0.0481 0.5871 0.0892
-6.750 -0.3761 0.01896 0.00941 -0.0474 0.5831 0.0934
-6.500 -0.3517 0.01867 0.00907 -0.0469 0.5795 0.0985
-6.250 -0.3282 0.01831 0.00870 -0.0462 0.5761 0.1038
-6.000 -0.3037 0.01804 0.00836 -0.0457 0.5727 0.1101
-5.750 -0.2798 0.01770 0.00802 -0.0451 0.5695 0.1179
-5.500 -0.2555 0.01733 0.00771 -0.0446 0.5658 0.1280
-5.250 -0.2317 0.01692 0.00738 -0.0441 0.5621 0.1444
-4.750 -0.1873 0.01588 0.00684 -0.0426 0.5549 0.2509
-4.500 -0.1619 0.01567 0.00664 -0.0422 0.5515 0.2811
-4.250 -0.1363 0.01545 0.00647 -0.0418 0.5479 0.3040
-4.000 -0.1112 0.01518 0.00630 -0.0413 0.5437 0.3276
-3.500 -0.0635 0.01458 0.00612 -0.0400 0.5359 0.4143
-3.250 -0.0375 0.01450 0.00612 -0.0395 0.5325 0.4593
-3.000 -0.0103 0.01451 0.00609 -0.0392 0.5294 0.4858
-2.750 0.0170 0.01450 0.00612 -0.0390 0.5257 0.5071
-2.500 0.0445 0.01450 0.00613 -0.0388 0.5216 0.5226
-2.250 0.0725 0.01452 0.00610 -0.0387 0.5178 0.5364
-2.000 0.1001 0.01451 0.00609 -0.0385 0.5145 0.5486
-1.750 0.1282 0.01455 0.00604 -0.0384 0.5113 0.5596
-1.500 0.1559 0.01456 0.00606 -0.0383 0.5079 0.5703
-1.250 0.1837 0.01459 0.00609 -0.0382 0.5037 0.5818
-1.000 0.2113 0.01458 0.00612 -0.0380 0.4996 0.5916
-0.750 0.2394 0.01460 0.00609 -0.0380 0.4958 0.6009
-0.500 0.2675 0.01461 0.00606 -0.0380 0.4925 0.6075
-0.250 0.2955 0.01464 0.00607 -0.0380 0.4892 0.6141
0.000 0.3236 0.01468 0.00613 -0.0380 0.4850 0.6204
0.250 0.3516 0.01471 0.00615 -0.0380 0.4806 0.6270
0.500 0.3791 0.01471 0.00616 -0.0379 0.4765 0.6347
0.750 0.4069 0.01474 0.00614 -0.0379 0.4729 0.6430
1.000 0.4347 0.01480 0.00621 -0.0379 0.4687 0.6499
1.250 0.4621 0.01483 0.00630 -0.0378 0.4642 0.6566
1.500 0.4896 0.01487 0.00635 -0.0378 0.4599 0.6642
1.750 0.5171 0.01492 0.00638 -0.0377 0.4561 0.6731
2.000 0.5441 0.01497 0.00645 -0.0376 0.4525 0.6834
2.500 0.5975 0.01509 0.00670 -0.0373 0.4429 0.7056
2.750 0.6240 0.01514 0.00676 -0.0370 0.4386 0.7196
3.000 0.6501 0.01521 0.00687 -0.0367 0.4345 0.7361
3.250 0.6757 0.01529 0.00707 -0.0363 0.4295 0.7539
3.500 0.7013 0.01537 0.00722 -0.0360 0.4250 0.7728
3.750 0.7270 0.01546 0.00734 -0.0356 0.4211 0.7924
4.000 0.7526 0.01557 0.00750 -0.0351 0.4173 0.8145
4.250 0.7784 0.01571 0.00776 -0.0348 0.4127 0.8389
4.500 0.8052 0.01586 0.00797 -0.0347 0.4083 0.8651
4.750 0.8339 0.01603 0.00816 -0.0349 0.4044 0.8917
5.000 0.8664 0.01625 0.00837 -0.0360 0.4006 0.9164
5.250 0.9016 0.01651 0.00870 -0.0378 0.3957 0.9396
5.500 0.9369 0.01677 0.00897 -0.0396 0.3912 0.9609
5.750 0.9719 0.01704 0.00920 -0.0415 0.3874 0.9788
6.000 1.0083 0.01734 0.00946 -0.0437 0.3841 0.9924
6.250 1.0400 0.01765 0.00981 -0.0451 0.3803 1.0000
6.500 1.0574 0.01791 0.01009 -0.0435 0.3771 1.0000
6.750 1.0754 0.01819 0.01035 -0.0421 0.3740 1.0000
7.000 1.0943 0.01847 0.01061 -0.0408 0.3712 1.0000
7.250 1.1143 0.01878 0.01086 -0.0398 0.3687 1.0000
7.500 1.1333 0.01912 0.01122 -0.0387 0.3659 1.0000
7.750 1.1515 0.01948 0.01164 -0.0374 0.3627 1.0000
8.000 1.1699 0.01985 0.01204 -0.0363 0.3597 1.0000
8.250 1.1887 0.02023 0.01244 -0.0352 0.3570 1.0000
8.500 1.2081 0.02061 0.01281 -0.0342 0.3546 1.0000
8.750 1.2278 0.02100 0.01317 -0.0333 0.3524 1.0000
9.000 1.2464 0.02142 0.01359 -0.0323 0.3501 1.0000
9.250 1.2588 0.02195 0.01422 -0.0304 0.3471 1.0000
9.500 1.2714 0.02251 0.01484 -0.0287 0.3436 1.0000
9.750 1.2851 0.02307 0.01543 -0.0273 0.3399 1.0000
10.000 1.3015 0.02359 0.01594 -0.0263 0.3367 1.0000
10.250 1.3199 0.02412 0.01642 -0.0255 0.3336 1.0000
10.500 1.3285 0.02502 0.01746 -0.0240 0.3302 1.0000
10.750 1.3392 0.02592 0.01846 -0.0228 0.3270 1.0000
11.000 1.3515 0.02681 0.01941 -0.0219 0.3241 1.0000
11.250 1.3655 0.02765 0.02027 -0.0212 0.3214 1.0000
11.500 1.3825 0.02833 0.02094 -0.0206 0.3187 1.0000
11.750 1.3959 0.02928 0.02193 -0.0200 0.3161 1.0000
12.000 1.4001 0.03083 0.02363 -0.0190 0.3129 1.0000
12.250 1.4054 0.03239 0.02530 -0.0183 0.3094 1.0000
12.500 1.4128 0.03383 0.02680 -0.0177 0.3058 1.0000
12.750 1.4266 0.03477 0.02772 -0.0173 0.3023 1.0000
13.000 1.4315 0.03649 0.02952 -0.0168 0.2987 1.0000
13.250 1.4270 0.03911 0.03230 -0.0163 0.2944 1.0000
13.500 1.4273 0.04133 0.03460 -0.0159 0.2900 1.0000
13.750 1.4377 0.04260 0.03586 -0.0156 0.2860 1.0000
14.000 1.4343 0.04530 0.03867 -0.0154 0.2818 1.0000
14.250 1.4239 0.04879 0.04232 -0.0152 0.2769 1.0000
14.500 1.4250 0.05114 0.04471 -0.0152 0.2723 1.0000
14.750 1.4296 0.05315 0.04673 -0.0151 0.2679 1.0000
15.000 1.4089 0.05812 0.05190 -0.0154 0.2620 1.0000
15.250 1.4083 0.06083 0.05466 -0.0156 0.2567 1.0000
15.500 1.4000 0.06455 0.05846 -0.0159 0.2512 1.0000
15.750 1.3824 0.06950 0.06352 -0.0165 0.2443 1.0000
16.000 1.3808 0.07252 0.06656 -0.0168 0.2383 1.0000
16.250 1.3558 0.07863 0.07281 -0.0178 0.2304 1.0000
16.500 1.3492 0.08242 0.07663 -0.0184 0.2235 1.0000
16.750 1.3323 0.08764 0.08191 -0.0193 0.2151 1.0000
17.000 1.3183 0.09255 0.08687 -0.0203 0.2070 1.0000
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