FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 77-W-270 (fx77w270-il) Reynolds number: 100,000 Max Cl/Cd: 12.84 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w270-il-100000-n5.txt Download as CSV file: xf-fx77w270-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7544 0.12138 0.11449 -0.0174 0.6263 0.0377
-17.000 -0.7932 0.10976 0.10249 -0.0245 0.6263 0.0376
-16.750 -0.8121 0.10251 0.09494 -0.0284 0.6197 0.0376
-16.500 -0.8243 0.09672 0.08889 -0.0312 0.6113 0.0378
-16.000 -0.8376 0.08751 0.07918 -0.0348 0.5961 0.0382
-15.750 -0.8405 0.08368 0.07511 -0.0360 0.5894 0.0385
-15.500 -0.8412 0.08024 0.07143 -0.0368 0.5835 0.0387
-15.250 -0.8405 0.07706 0.06802 -0.0375 0.5781 0.0391
-15.000 -0.8378 0.07418 0.06492 -0.0379 0.5727 0.0394
-14.750 -0.8338 0.07151 0.06202 -0.0381 0.5679 0.0398
-14.500 -0.8256 0.06945 0.05985 -0.0382 0.5633 0.0401
-14.250 -0.8168 0.06749 0.05781 -0.0382 0.5589 0.0405
-14.000 -0.8077 0.06554 0.05580 -0.0382 0.5543 0.0409
-13.750 -0.7983 0.06368 0.05384 -0.0381 0.5499 0.0413
-13.500 -0.7886 0.06188 0.05192 -0.0379 0.5460 0.0418
-13.250 -0.7782 0.06017 0.05007 -0.0377 0.5425 0.0423
-13.000 -0.7669 0.05855 0.04831 -0.0374 0.5392 0.0429
-12.750 -0.7546 0.05699 0.04664 -0.0370 0.5357 0.0436
-12.500 -0.7432 0.05545 0.04507 -0.0367 0.5325 0.0442
-12.250 -0.7321 0.05394 0.04351 -0.0364 0.5296 0.0449
-12.000 -0.7202 0.05251 0.04201 -0.0361 0.5269 0.0458
-11.750 -0.7075 0.05116 0.04057 -0.0357 0.5246 0.0468
-11.500 -0.6943 0.04988 0.03918 -0.0353 0.5224 0.0480
-11.000 -0.6679 0.04742 0.03663 -0.0346 0.5183 0.0505
-10.750 -0.6528 0.04630 0.03545 -0.0342 0.5161 0.0522
-10.500 -0.6386 0.04517 0.03431 -0.0338 0.5140 0.0539
-10.250 -0.6228 0.04416 0.03321 -0.0334 0.5119 0.0561
-10.000 -0.6076 0.04312 0.03212 -0.0329 0.5099 0.0583
-9.750 -0.5915 0.04216 0.03106 -0.0324 0.5080 0.0612
-9.500 -0.5772 0.04111 0.02997 -0.0317 0.5063 0.0637
-9.250 -0.5619 0.04015 0.02891 -0.0310 0.5046 0.0669
-9.000 -0.5502 0.03907 0.02782 -0.0299 0.5031 0.0696
-8.750 -0.5396 0.03813 0.02682 -0.0286 0.5018 0.0726
-8.500 -0.5319 0.03719 0.02585 -0.0269 0.5005 0.0754
-8.250 -0.5186 0.03633 0.02499 -0.0261 0.4992 0.0790
-8.000 -0.5021 0.03552 0.02423 -0.0257 0.4978 0.0835
-7.750 -0.4834 0.03479 0.02353 -0.0256 0.4963 0.0894
-7.500 -0.4629 0.03415 0.02289 -0.0256 0.4947 0.0979
-7.250 -0.4423 0.03346 0.02225 -0.0256 0.4930 0.1079
-7.000 -0.4214 0.03276 0.02169 -0.0258 0.4912 0.1200
-6.750 -0.3981 0.03220 0.02121 -0.0261 0.4893 0.1410
-6.500 -0.3749 0.03157 0.02071 -0.0265 0.4875 0.1631
-6.250 -0.3503 0.03099 0.02026 -0.0271 0.4858 0.1987
-6.000 -0.3259 0.03019 0.01973 -0.0281 0.4844 0.2462
-5.750 -0.3004 0.02928 0.01918 -0.0296 0.4831 0.3145
-5.500 -0.2757 0.02866 0.01927 -0.0301 0.4819 0.4176
-5.250 -0.2528 0.03001 0.02113 -0.0266 0.4808 0.4945
-5.000 -0.2263 0.03172 0.02295 -0.0238 0.4797 0.5281
-4.750 -0.1931 0.03183 0.02295 -0.0261 0.4785 0.5638
-4.500 -0.1610 0.03234 0.02340 -0.0274 0.4770 0.5833
-4.000 -0.0981 0.03345 0.02436 -0.0294 0.4726 0.6127
-3.750 -0.0678 0.03406 0.02489 -0.0299 0.4704 0.6248
-3.500 -0.0346 0.03433 0.02500 -0.0320 0.4683 0.6392
-3.250 -0.0092 0.03515 0.02581 -0.0303 0.4666 0.6438
-3.000 0.0182 0.03581 0.02641 -0.0296 0.4651 0.6516
-2.750 0.0480 0.03623 0.02673 -0.0303 0.4637 0.6623
-2.500 0.0728 0.03695 0.02742 -0.0286 0.4626 0.6683
-2.250 0.1040 0.03724 0.02758 -0.0300 0.4615 0.6791
-2.000 0.1308 0.03758 0.02785 -0.0296 0.4604 0.6841
-1.750 0.1574 0.03794 0.02813 -0.0291 0.4594 0.6878
-1.500 0.1853 0.03833 0.02855 -0.0298 0.4580 0.6919
-1.250 0.2152 0.03872 0.02896 -0.0316 0.4563 0.6971
-1.000 0.2488 0.03904 0.02925 -0.0348 0.4545 0.7025
-0.750 0.2753 0.03945 0.02968 -0.0354 0.4527 0.7041
-0.500 0.3021 0.03986 0.03012 -0.0360 0.4509 0.7059
-0.250 0.3291 0.04024 0.03049 -0.0366 0.4490 0.7080
0.000 0.3567 0.04056 0.03079 -0.0374 0.4471 0.7103
0.250 0.3852 0.04082 0.03101 -0.0384 0.4454 0.7130
0.500 0.4147 0.04104 0.03117 -0.0397 0.4439 0.7160
0.750 0.4456 0.04125 0.03130 -0.0413 0.4426 0.7192
1.000 0.4781 0.04149 0.03145 -0.0434 0.4415 0.7223
1.250 0.5100 0.04175 0.03162 -0.0453 0.4404 0.7247
1.500 0.5376 0.04204 0.03186 -0.0458 0.4395 0.7262
1.750 0.5561 0.04355 0.03354 -0.0465 0.4371 0.7276
2.000 0.5612 0.04651 0.03682 -0.0467 0.4326 0.7290
2.250 0.5678 0.04901 0.03949 -0.0467 0.4290 0.7304
2.500 0.5796 0.05084 0.04139 -0.0468 0.4264 0.7318
2.750 0.5965 0.05213 0.04270 -0.0471 0.4245 0.7333
3.000 0.6161 0.05316 0.04372 -0.0476 0.4230 0.7348
3.250 0.6399 0.05378 0.04432 -0.0482 0.4217 0.7364
3.500 0.6672 0.05411 0.04460 -0.0490 0.4207 0.7387
3.750 0.6971 0.05431 0.04473 -0.0501 0.4199 0.7413
5.250 0.5386 0.08942 0.08049 -0.0486 0.3827 0.7484
5.500 0.5565 0.09081 0.08188 -0.0490 0.3813 0.7494
6.000 0.5148 0.10238 0.09365 -0.0503 0.3683 0.7513
6.250 0.5361 0.10330 0.09456 -0.0508 0.3667 0.7526
6.500 0.5594 0.10405 0.09528 -0.0513 0.3655 0.7539
6.750 0.5839 0.10472 0.09594 -0.0520 0.3645 0.7549
7.000 0.6087 0.10543 0.09663 -0.0526 0.3638 0.7559
7.500 0.4058 0.11911 0.11107 -0.0340 0.3414 0.7535
7.750 0.4052 0.12173 0.11374 -0.0341 0.3375 0.7543
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Polar data table (+)
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