FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 77-W-270 (fx77w270-il) Reynolds number: 200,000 Max Cl/Cd: 15.18 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w270-il-200000.txt Download as CSV file: xf-fx77w270-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-270
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 -0.8377 0.12931 0.12513 -0.0121 1.0001 0.0353
-18.500 -0.8880 0.11536 0.11079 -0.0214 1.0001 0.0350
-18.250 -0.9202 0.10575 0.10088 -0.0271 1.0001 0.0350
-18.000 -0.9438 0.09818 0.09304 -0.0312 1.0001 0.0351
-17.750 -0.9629 0.09169 0.08632 -0.0343 1.0001 0.0352
-17.500 -0.9785 0.08605 0.08044 -0.0367 1.0001 0.0354
-17.250 -0.9965 0.08208 0.07590 -0.0369 0.7971 0.0356
-17.000 -1.0099 0.07791 0.07117 -0.0374 0.7179 0.0358
-16.750 -1.0218 0.07403 0.06683 -0.0379 0.6769 0.0360
-16.500 -1.0076 0.07262 0.06524 -0.0378 0.6420 0.0364
-16.250 -0.9986 0.07078 0.06324 -0.0378 0.6232 0.0369
-16.000 -0.9917 0.06871 0.06104 -0.0379 0.6092 0.0373
-15.750 -0.9855 0.06661 0.05878 -0.0379 0.5994 0.0377
-15.500 -0.9813 0.06434 0.05634 -0.0379 0.5914 0.0382
-15.250 -0.9777 0.06209 0.05386 -0.0378 0.5850 0.0387
-15.000 -0.9743 0.05984 0.05137 -0.0375 0.5797 0.0391
-14.750 -0.9705 0.05763 0.04896 -0.0372 0.5746 0.0395
-14.500 -0.9659 0.05557 0.04666 -0.0368 0.5700 0.0398
-14.250 -0.9447 0.05455 0.04561 -0.0365 0.5648 0.0402
-14.000 -0.9259 0.05351 0.04452 -0.0362 0.5604 0.0407
-13.750 -0.9099 0.05226 0.04325 -0.0360 0.5565 0.0411
-13.500 -0.8950 0.05097 0.04191 -0.0356 0.5528 0.0417
-13.250 -0.8800 0.04971 0.04055 -0.0352 0.5492 0.0423
-13.000 -0.8646 0.04849 0.03922 -0.0348 0.5461 0.0428
-12.750 -0.8484 0.04735 0.03794 -0.0344 0.5432 0.0433
-12.500 -0.8313 0.04632 0.03676 -0.0339 0.5405 0.0437
-12.250 -0.8103 0.04545 0.03594 -0.0335 0.5380 0.0441
-12.000 -0.7912 0.04454 0.03507 -0.0331 0.5354 0.0446
-11.750 -0.7733 0.04358 0.03412 -0.0326 0.5330 0.0451
-11.500 -0.7560 0.04262 0.03314 -0.0321 0.5306 0.0457
-11.250 -0.7390 0.04166 0.03214 -0.0316 0.5284 0.0463
-11.000 -0.7221 0.04071 0.03114 -0.0310 0.5264 0.0469
-10.750 -0.7053 0.03977 0.03012 -0.0304 0.5245 0.0476
-10.500 -0.6896 0.03881 0.02915 -0.0298 0.5226 0.0483
-10.250 -0.6740 0.03793 0.02825 -0.0293 0.5208 0.0490
-10.000 -0.6581 0.03698 0.02732 -0.0287 0.5194 0.0499
-9.750 -0.6424 0.03601 0.02635 -0.0281 0.5181 0.0510
-9.500 -0.6271 0.03507 0.02538 -0.0273 0.5167 0.0521
-9.250 -0.6144 0.03414 0.02449 -0.0263 0.5153 0.0532
-9.000 -0.6047 0.03329 0.02364 -0.0248 0.5138 0.0545
-8.750 -0.5928 0.03249 0.02279 -0.0235 0.5121 0.0562
-8.500 -0.5763 0.03169 0.02199 -0.0231 0.5103 0.0582
-8.250 -0.5563 0.03099 0.02123 -0.0232 0.5086 0.0610
-8.000 -0.5358 0.03021 0.02045 -0.0235 0.5071 0.0641
-7.750 -0.5135 0.02949 0.01968 -0.0240 0.5058 0.0680
-7.500 -0.4902 0.02879 0.01898 -0.0246 0.5045 0.0729
-7.250 -0.4654 0.02817 0.01841 -0.0255 0.5032 0.0788
-7.000 -0.4387 0.02776 0.01807 -0.0264 0.5018 0.0875
-6.750 -0.4109 0.02758 0.01790 -0.0275 0.5000 0.1018
-6.500 -0.3825 0.02690 0.01742 -0.0290 0.4987 0.1196
-6.250 -0.3527 0.02627 0.01700 -0.0307 0.4972 0.1548
-6.000 -0.3219 0.02549 0.01657 -0.0329 0.4955 0.2071
-5.750 -0.2892 0.02449 0.01607 -0.0360 0.4937 0.2894
-5.500 -0.2547 0.02336 0.01572 -0.0395 0.4920 0.4259
-5.250 -0.2275 0.02393 0.01702 -0.0387 0.4906 0.5255
-5.000 -0.1975 0.02483 0.01801 -0.0384 0.4892 0.5693
-4.750 -0.1662 0.02565 0.01879 -0.0387 0.4879 0.5898
-4.500 -0.1336 0.02636 0.01941 -0.0395 0.4866 0.6064
-4.250 -0.0991 0.02684 0.01973 -0.0412 0.4852 0.6204
-4.000 -0.0711 0.02772 0.02061 -0.0405 0.4840 0.6258
-3.750 -0.0397 0.02838 0.02117 -0.0411 0.4828 0.6348
-3.500 -0.0092 0.02904 0.02176 -0.0415 0.4817 0.6417
-3.250 0.0170 0.03011 0.02282 -0.0404 0.4805 0.6462
-3.000 0.0452 0.03117 0.02388 -0.0403 0.4792 0.6525
-2.750 0.0782 0.03160 0.02428 -0.0419 0.4781 0.6612
-2.500 0.1038 0.03234 0.02513 -0.0408 0.4768 0.6646
-2.250 0.1298 0.03313 0.02599 -0.0400 0.4749 0.6692
-2.000 0.1623 0.03378 0.02662 -0.0416 0.4728 0.6794
-1.750 0.1865 0.03445 0.02735 -0.0404 0.4709 0.6844
-1.500 0.2090 0.03526 0.02821 -0.0385 0.4693 0.6889
-1.250 0.2367 0.03585 0.02880 -0.0385 0.4678 0.6957
-1.000 0.2715 0.03613 0.02898 -0.0411 0.4663 0.7036
-0.750 0.2933 0.03653 0.02940 -0.0392 0.4650 0.7069
-0.500 0.3160 0.03705 0.02992 -0.0375 0.4638 0.7121
-0.250 0.3489 0.03760 0.03039 -0.0392 0.4625 0.7222
0.000 0.3709 0.03796 0.03073 -0.0376 0.4614 0.7279
0.250 0.3909 0.03871 0.03147 -0.0355 0.4601 0.7332
0.500 0.4156 0.03984 0.03267 -0.0360 0.4584 0.7390
0.750 0.4446 0.04118 0.03418 -0.0393 0.4557 0.7437
1.000 0.4708 0.04293 0.03607 -0.0424 0.4525 0.7471
1.250 0.4857 0.04442 0.03770 -0.0420 0.4497 0.7488
1.500 0.5035 0.04577 0.03913 -0.0422 0.4475 0.7504
1.750 0.5256 0.04666 0.04003 -0.0427 0.4457 0.7520
2.000 0.5550 0.04661 0.03994 -0.0434 0.4444 0.7537
2.250 0.5878 0.04623 0.03947 -0.0443 0.4433 0.7559
2.500 0.6227 0.04574 0.03887 -0.0455 0.4423 0.7584
2.750 0.6575 0.04548 0.03850 -0.0470 0.4412 0.7613
3.000 0.6922 0.04560 0.03851 -0.0489 0.4400 0.7636
5.000 0.4368 0.10230 0.09636 -0.0497 0.4021 0.7693
5.250 0.4375 0.10640 0.10049 -0.0508 0.4021 0.7700
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