WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il) Reynolds number: 200,000 Max Cl/Cd: 9.54 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w258-il-200000.txt Download as CSV file: xf-fx77w258-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-W-258 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -0.7515 0.12544 0.12059 -0.0205 0.6956 0.0341
-18.500 -0.7975 0.11251 0.10739 -0.0289 0.7054 0.0339
-18.250 -0.8292 0.10318 0.09770 -0.0346 0.6914 0.0338
-18.000 -0.8529 0.09574 0.08989 -0.0388 0.6703 0.0339
-17.750 -0.8727 0.08927 0.08306 -0.0422 0.6524 0.0340
-17.500 -0.8899 0.08353 0.07694 -0.0450 0.6389 0.0342
-17.250 -0.9058 0.07828 0.07136 -0.0473 0.6274 0.0344
-17.000 -0.9035 0.07549 0.06838 -0.0481 0.6140 0.0347
-16.750 -0.8948 0.07347 0.06629 -0.0486 0.6024 0.0351
-16.250 -0.8872 0.06839 0.06090 -0.0498 0.5876 0.0357
-16.000 -0.8828 0.06598 0.05834 -0.0502 0.5817 0.0360
-15.750 -0.8781 0.06367 0.05585 -0.0505 0.5765 0.0363
-15.500 -0.8730 0.06145 0.05344 -0.0508 0.5719 0.0367
-15.250 -0.8671 0.05930 0.05116 -0.0509 0.5675 0.0370
-15.000 -0.8610 0.05725 0.04895 -0.0510 0.5634 0.0374
-14.750 -0.8538 0.05536 0.04688 -0.0509 0.5597 0.0377
-14.500 -0.8471 0.05353 0.04483 -0.0508 0.5563 0.0380
-14.250 -0.8387 0.05191 0.04300 -0.0506 0.5531 0.0384
-14.000 -0.8182 0.05096 0.04212 -0.0503 0.5498 0.0388
-13.750 -0.8016 0.04985 0.04102 -0.0500 0.5464 0.0393
-13.500 -0.7864 0.04868 0.03981 -0.0497 0.5430 0.0398
-13.250 -0.7714 0.04753 0.03859 -0.0494 0.5399 0.0403
-13.000 -0.7562 0.04641 0.03737 -0.0491 0.5370 0.0408
-12.750 -0.7408 0.04535 0.03619 -0.0487 0.5345 0.0414
-12.500 -0.7251 0.04435 0.03506 -0.0484 0.5322 0.0419
-12.250 -0.7081 0.04336 0.03403 -0.0480 0.5302 0.0424
-12.000 -0.6898 0.04249 0.03323 -0.0476 0.5281 0.0430
-11.750 -0.6730 0.04157 0.03234 -0.0472 0.5260 0.0436
-11.500 -0.6562 0.04067 0.03143 -0.0468 0.5239 0.0443
-11.250 -0.6395 0.03978 0.03051 -0.0464 0.5220 0.0451
-11.000 -0.6228 0.03891 0.02957 -0.0460 0.5201 0.0460
-10.750 -0.6069 0.03801 0.02869 -0.0455 0.5184 0.0469
-10.500 -0.5911 0.03716 0.02784 -0.0451 0.5168 0.0478
-10.250 -0.5746 0.03637 0.02702 -0.0447 0.5152 0.0489
-10.000 -0.5577 0.03565 0.02624 -0.0442 0.5136 0.0500
-9.500 -0.5241 0.03423 0.02485 -0.0435 0.5109 0.0522
-9.250 -0.5067 0.03349 0.02414 -0.0431 0.5098 0.0537
-9.000 -0.4892 0.03279 0.02343 -0.0427 0.5086 0.0555
-8.750 -0.4716 0.03211 0.02279 -0.0423 0.5073 0.0576
-8.500 -0.4534 0.03148 0.02214 -0.0419 0.5061 0.0605
-8.250 -0.4360 0.03082 0.02148 -0.0415 0.5049 0.0640
-8.000 -0.4210 0.03002 0.02072 -0.0409 0.5037 0.0676
-7.750 -0.4077 0.02922 0.01994 -0.0401 0.5024 0.0717
-7.500 -0.3967 0.02846 0.01921 -0.0389 0.5010 0.0763
-7.250 -0.3875 0.02777 0.01860 -0.0373 0.4995 0.0814
-7.000 -0.3764 0.02721 0.01809 -0.0360 0.4981 0.0884
-6.750 -0.3607 0.02662 0.01751 -0.0355 0.4967 0.0999
-6.500 -0.3458 0.02584 0.01679 -0.0352 0.4952 0.1132
-6.250 -0.3287 0.02518 0.01627 -0.0350 0.4936 0.1384
-6.000 -0.3112 0.02462 0.01590 -0.0351 0.4920 0.1714
-5.750 -0.2915 0.02389 0.01548 -0.0356 0.4907 0.2227
-5.500 -0.2695 0.02288 0.01491 -0.0366 0.4894 0.2994
-5.250 -0.2453 0.02186 0.01451 -0.0380 0.4880 0.3994
-5.000 -0.2197 0.02191 0.01521 -0.0378 0.4866 0.5026
-4.750 -0.1927 0.02306 0.01666 -0.0363 0.4852 0.5510
-4.500 -0.1620 0.02363 0.01720 -0.0369 0.4836 0.5767
-4.250 -0.1327 0.02457 0.01815 -0.0365 0.4822 0.5892
-4.000 -0.1022 0.02520 0.01870 -0.0370 0.4807 0.6021
-3.750 -0.0701 0.02561 0.01896 -0.0384 0.4792 0.6169
-3.500 -0.0425 0.02653 0.01987 -0.0375 0.4779 0.6213
-3.250 -0.0140 0.02726 0.02056 -0.0371 0.4766 0.6274
-3.000 0.0173 0.02757 0.02072 -0.0384 0.4753 0.6375
-2.750 0.0434 0.02848 0.02163 -0.0370 0.4741 0.6408
-2.500 0.0696 0.02946 0.02260 -0.0359 0.4729 0.6455
-2.250 0.0996 0.03030 0.02330 -0.0371 0.4715 0.6573
-2.000 0.1209 0.03161 0.02474 -0.0348 0.4702 0.6606
-1.750 0.1422 0.03285 0.02613 -0.0328 0.4686 0.6649
-1.500 0.1647 0.03400 0.02738 -0.0320 0.4666 0.6724
-1.250 0.1886 0.03484 0.02826 -0.0325 0.4645 0.6807
-1.000 0.2072 0.03598 0.02949 -0.0306 0.4624 0.6836
-0.750 0.2276 0.03691 0.03048 -0.0295 0.4605 0.6872
-0.500 0.2516 0.03757 0.03112 -0.0294 0.4587 0.6936
-0.250 0.2814 0.03767 0.03112 -0.0309 0.4570 0.7016
0.000 0.3022 0.03807 0.03152 -0.0283 0.4557 0.7049
0.250 0.3253 0.03848 0.03189 -0.0264 0.4545 0.7102
0.500 0.3562 0.03887 0.03217 -0.0279 0.4532 0.7200
0.750 0.3758 0.03941 0.03269 -0.0260 0.4521 0.7253
1.000 0.3868 0.04102 0.03437 -0.0233 0.4503 0.7297
1.250 0.2257 0.05690 0.05111 -0.0228 0.4338 0.7268
1.500 0.2488 0.05669 0.05089 -0.0198 0.4332 0.7328
1.750 0.2966 0.05533 0.04943 -0.0204 0.4329 0.7410
2.000 0.3459 0.05364 0.04763 -0.0210 0.4329 0.7464
2.250 0.3790 0.05278 0.04671 -0.0199 0.4326 0.7489
2.500 0.4169 0.05192 0.04576 -0.0202 0.4323 0.7507
2.750 0.4492 0.05177 0.04555 -0.0207 0.4316 0.7524
3.000 0.4786 0.05220 0.04591 -0.0211 0.4308 0.7550
5.000 0.2273 0.10401 0.09839 -0.0338 0.4013 0.7665
5.250 0.2479 0.10515 0.09951 -0.0346 0.3986 0.7673
5.500 0.3655 0.09789 0.09203 -0.0340 0.3933 0.7687
5.750 0.3651 0.10195 0.09612 -0.0349 0.3914 0.7694
6.000 0.3904 0.10384 0.09799 -0.0357 0.3918 0.7703
6.250 0.4139 0.10597 0.10012 -0.0365 0.3921 0.7714
6.500 0.4301 0.10883 0.10299 -0.0373 0.3922 0.7727
6.750 0.4335 0.11273 0.10692 -0.0384 0.3922 0.7738
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