FX 77-W-270S (fx77w270s-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 77-W-270S (fx77w270s-il) Reynolds number: 200,000 Max Cl/Cd: 10.3 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w270s-il-200000.txt Download as CSV file: xf-fx77w270s-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-270S
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
------ -------- --------- --------- -------- -------- --------
-19.500 -0.8214 0.11615 0.11130 -0.0408 1.0001 0.0361
-19.250 -0.8596 0.10598 0.10079 -0.0470 1.0001 0.0362
-19.000 -0.8399 0.10555 0.10053 -0.0469 1.0001 0.0368
-18.750 -0.8403 0.10183 0.09679 -0.0490 1.0001 0.0372
-18.500 -0.8458 0.09737 0.09225 -0.0514 1.0001 0.0377
-18.250 -0.8553 0.09244 0.08720 -0.0538 1.0001 0.0381
-18.000 -0.8656 0.08757 0.08219 -0.0560 1.0001 0.0385
-17.750 -0.8762 0.08286 0.07731 -0.0579 1.0001 0.0388
-17.500 -0.8850 0.07853 0.07281 -0.0593 1.0001 0.0391
-17.250 -0.8918 0.07459 0.06872 -0.0605 1.0001 0.0394
-17.000 -0.9011 0.07195 0.06531 -0.0598 0.7377 0.0396
-16.750 -0.9065 0.06901 0.06181 -0.0598 0.6714 0.0399
-16.500 -0.9097 0.06610 0.05852 -0.0600 0.6434 0.0402
-16.250 -0.9054 0.06391 0.05607 -0.0600 0.6243 0.0406
-16.000 -0.8912 0.06262 0.05470 -0.0599 0.6093 0.0410
-15.750 -0.8804 0.06109 0.05307 -0.0598 0.5992 0.0415
-15.500 -0.8712 0.05942 0.05129 -0.0597 0.5909 0.0419
-15.250 -0.8623 0.05778 0.04949 -0.0596 0.5841 0.0424
-15.000 -0.8527 0.05620 0.04774 -0.0594 0.5784 0.0428
-14.750 -0.8432 0.05457 0.04601 -0.0591 0.5734 0.0434
-14.500 -0.8329 0.05304 0.04433 -0.0588 0.5687 0.0439
-14.250 -0.8218 0.05159 0.04271 -0.0585 0.5645 0.0444
-14.000 -0.8109 0.05018 0.04109 -0.0580 0.5607 0.0448
-13.750 -0.7931 0.04926 0.04012 -0.0577 0.5566 0.0454
-13.500 -0.7767 0.04824 0.03914 -0.0575 0.5533 0.0461
-13.250 -0.7621 0.04715 0.03804 -0.0572 0.5499 0.0469
-13.000 -0.7478 0.04606 0.03687 -0.0568 0.5467 0.0478
-12.750 -0.7324 0.04501 0.03572 -0.0564 0.5437 0.0486
-12.500 -0.7164 0.04402 0.03460 -0.0560 0.5411 0.0493
-12.250 -0.6988 0.04313 0.03360 -0.0555 0.5386 0.0499
-12.000 -0.6788 0.04246 0.03293 -0.0552 0.5361 0.0506
-11.750 -0.6605 0.04173 0.03220 -0.0548 0.5339 0.0514
-11.500 -0.6425 0.04089 0.03138 -0.0544 0.5322 0.0522
-11.250 -0.6245 0.04008 0.03055 -0.0539 0.5304 0.0531
-11.000 -0.6066 0.03929 0.02971 -0.0535 0.5285 0.0541
-10.750 -0.5887 0.03852 0.02888 -0.0530 0.5266 0.0553
-10.500 -0.5717 0.03772 0.02814 -0.0525 0.5248 0.0564
-10.250 -0.5545 0.03696 0.02738 -0.0520 0.5230 0.0578
-10.000 -0.5371 0.03622 0.02661 -0.0514 0.5212 0.0594
-9.750 -0.5200 0.03548 0.02581 -0.0508 0.5193 0.0611
-9.500 -0.5044 0.03467 0.02503 -0.0502 0.5174 0.0628
-9.250 -0.4878 0.03396 0.02428 -0.0495 0.5157 0.0649
-9.000 -0.4714 0.03329 0.02356 -0.0489 0.5141 0.0673
-8.750 -0.4566 0.03260 0.02292 -0.0482 0.5125 0.0699
-8.500 -0.4400 0.03193 0.02223 -0.0475 0.5113 0.0736
-8.250 -0.4270 0.03099 0.02137 -0.0466 0.5104 0.0775
-8.000 -0.4138 0.03007 0.02051 -0.0457 0.5093 0.0828
-7.750 -0.4016 0.02911 0.01961 -0.0447 0.5082 0.0902
-7.500 -0.3918 0.02803 0.01864 -0.0435 0.5070 0.1002
-7.250 -0.3838 0.02696 0.01768 -0.0420 0.5059 0.1143
-7.000 -0.3806 0.02604 0.01687 -0.0394 0.5049 0.1309
-6.750 -0.3833 0.02528 0.01623 -0.0355 0.5038 0.1493
-6.500 -0.3833 0.02460 0.01570 -0.0318 0.5025 0.1747
-6.250 -0.3797 0.02382 0.01514 -0.0286 0.5011 0.2128
-6.000 -0.3765 0.02288 0.01453 -0.0255 0.4997 0.2690
-5.750 -0.3733 0.02178 0.01391 -0.0223 0.4985 0.3549
-5.500 -0.3664 0.02094 0.01383 -0.0191 0.4974 0.4748
-5.250 -0.3385 0.02214 0.01554 -0.0177 0.4960 0.5595
-5.000 -0.3106 0.02279 0.01608 -0.0176 0.4947 0.5931
-4.750 -0.2822 0.02365 0.01681 -0.0174 0.4934 0.6125
-4.500 -0.2514 0.02489 0.01801 -0.0171 0.4921 0.6255
-4.250 -0.2206 0.02648 0.01958 -0.0166 0.4906 0.6368
-4.000 -0.1937 0.02764 0.02071 -0.0161 0.4892 0.6514
-3.750 -0.1589 0.02910 0.02231 -0.0155 0.4877 0.6575
-3.500 -0.1294 0.02993 0.02316 -0.0151 0.4861 0.6647
-3.250 -0.1061 0.03016 0.02333 -0.0149 0.4848 0.6732
-3.000 -0.0758 0.03104 0.02427 -0.0145 0.4833 0.6769
-2.750 -0.0465 0.03220 0.02547 -0.0137 0.4817 0.6856
-2.500 -0.0192 0.03325 0.02655 -0.0126 0.4802 0.6962
-2.250 0.0126 0.03442 0.02776 -0.0117 0.4786 0.7034
-2.000 0.0297 0.03418 0.02741 -0.0113 0.4771 0.7138
-1.750 0.0586 0.03439 0.02759 -0.0110 0.4755 0.7162
-1.500 0.0866 0.03465 0.02780 -0.0107 0.4740 0.7196
-1.250 0.1120 0.03491 0.02801 -0.0104 0.4728 0.7251
-1.000 0.1301 0.03470 0.02767 -0.0108 0.4717 0.7338
-0.750 0.1556 0.03494 0.02788 -0.0103 0.4705 0.7359
-0.500 0.1790 0.03567 0.02858 -0.0098 0.4691 0.7384
-0.250 0.1982 0.03632 0.02931 -0.0091 0.4678 0.7416
0.000 0.2134 0.03685 0.02995 -0.0083 0.4659 0.7452
0.250 0.2254 0.03757 0.03078 -0.0077 0.4631 0.7486
0.500 0.2380 0.03848 0.03173 -0.0074 0.4605 0.7524
0.750 0.2506 0.03942 0.03270 -0.0071 0.4583 0.7548
1.000 0.2634 0.04015 0.03347 -0.0060 0.4563 0.7564
1.250 0.2809 0.04072 0.03404 -0.0054 0.4547 0.7579
1.500 0.3028 0.04106 0.03435 -0.0052 0.4534 0.7597
1.750 0.3301 0.04109 0.03433 -0.0055 0.4523 0.7617
2.000 0.3622 0.04088 0.03403 -0.0064 0.4514 0.7636
2.250 0.3939 0.04079 0.03384 -0.0074 0.4504 0.7652
2.500 0.4232 0.04107 0.03403 -0.0083 0.4492 0.7672
3.500 0.1581 0.07459 0.06833 0.0042 0.4296 0.7742
3.750 0.1779 0.07660 0.07030 0.0033 0.4292 0.7748
4.000 0.1993 0.07870 0.07237 0.0024 0.4289 0.7754
4.750 0.0843 0.09424 0.08814 0.0026 0.4183 0.7783
5.000 0.1057 0.09535 0.08922 0.0021 0.4157 0.7792
5.250 0.1312 0.09645 0.09028 0.0014 0.4141 0.7799
5.500 0.1597 0.09756 0.09135 0.0005 0.4128 0.7806
5.750 0.1911 0.09870 0.09246 -0.0004 0.4119 0.7813
6.000 0.2252 0.09991 0.09363 -0.0013 0.4112 0.7821
6.250 0.2619 0.10125 0.09493 -0.0022 0.4106 0.7828
6.500 0.2946 0.10356 0.09721 -0.0031 0.4100 0.7837
6.750 0.2069 0.10733 0.10110 -0.0019 0.3963 0.7842
7.000 0.2348 0.10854 0.10229 -0.0026 0.3951 0.7855
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