WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il) Reynolds number: 100,000 Max Cl/Cd: 10.51 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w258-il-100000-n5.txt Download as CSV file: xf-fx77w258-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.5747 0.13649 0.12962 -0.0145 0.5725 0.0384
-17.000 -0.6573 0.11427 0.10702 -0.0281 0.5800 0.0373
-16.750 -0.6920 0.10372 0.09616 -0.0344 0.5798 0.0371
-16.500 -0.7129 0.09625 0.08839 -0.0387 0.5775 0.0372
-16.250 -0.7277 0.09017 0.08202 -0.0418 0.5746 0.0375
-16.000 -0.7392 0.08487 0.07645 -0.0444 0.5712 0.0379
-15.750 -0.7482 0.08012 0.07143 -0.0464 0.5675 0.0383
-15.500 -0.7452 0.07728 0.06853 -0.0475 0.5628 0.0388
-15.250 -0.7420 0.07455 0.06571 -0.0484 0.5586 0.0394
-15.000 -0.7397 0.07176 0.06278 -0.0493 0.5550 0.0400
-14.750 -0.7374 0.06900 0.05985 -0.0500 0.5518 0.0407
-14.500 -0.7349 0.06629 0.05697 -0.0505 0.5483 0.0414
-14.250 -0.7320 0.06368 0.05413 -0.0509 0.5450 0.0422
-14.000 -0.7228 0.06191 0.05236 -0.0511 0.5415 0.0428
-13.750 -0.7140 0.06015 0.05053 -0.0511 0.5384 0.0434
-13.500 -0.7052 0.05841 0.04869 -0.0511 0.5356 0.0441
-13.250 -0.6954 0.05677 0.04691 -0.0510 0.5332 0.0449
-13.000 -0.6843 0.05517 0.04518 -0.0509 0.5307 0.0457
-12.750 -0.6720 0.05369 0.04361 -0.0507 0.5281 0.0464
-12.500 -0.6598 0.05234 0.04225 -0.0505 0.5256 0.0471
-12.250 -0.6468 0.05106 0.04092 -0.0503 0.5231 0.0477
-12.000 -0.6331 0.04982 0.03961 -0.0500 0.5208 0.0485
-11.750 -0.6187 0.04864 0.03835 -0.0497 0.5186 0.0493
-11.500 -0.6038 0.04752 0.03712 -0.0493 0.5164 0.0502
-11.250 -0.5897 0.04642 0.03595 -0.0489 0.5143 0.0511
-11.000 -0.5753 0.04539 0.03484 -0.0486 0.5124 0.0522
-10.750 -0.5599 0.04439 0.03379 -0.0483 0.5102 0.0537
-10.500 -0.5439 0.04343 0.03278 -0.0479 0.5080 0.0554
-10.250 -0.5286 0.04246 0.03180 -0.0476 0.5059 0.0574
-10.000 -0.5115 0.04162 0.03087 -0.0472 0.5039 0.0599
-9.750 -0.4961 0.04070 0.02994 -0.0468 0.5021 0.0622
-9.500 -0.4792 0.03989 0.02905 -0.0463 0.5004 0.0652
-9.250 -0.4644 0.03897 0.02812 -0.0458 0.4987 0.0679
-9.000 -0.4487 0.03812 0.02723 -0.0452 0.4972 0.0710
-8.750 -0.4338 0.03725 0.02635 -0.0446 0.4958 0.0740
-8.500 -0.4185 0.03643 0.02553 -0.0440 0.4944 0.0774
-8.250 -0.4025 0.03568 0.02477 -0.0434 0.4932 0.0816
-8.000 -0.3860 0.03500 0.02409 -0.0428 0.4919 0.0873
-7.500 -0.3521 0.03376 0.02287 -0.0416 0.4894 0.1029
-7.250 -0.3379 0.03312 0.02231 -0.0407 0.4881 0.1110
-7.000 -0.3255 0.03248 0.02183 -0.0396 0.4868 0.1214
-6.750 -0.3127 0.03197 0.02141 -0.0383 0.4854 0.1401
-6.500 -0.3024 0.03141 0.02099 -0.0368 0.4842 0.1589
-6.250 -0.2911 0.03074 0.02051 -0.0358 0.4829 0.1886
-6.000 -0.2804 0.02992 0.01993 -0.0349 0.4814 0.2207
-5.750 -0.2688 0.02906 0.01932 -0.0342 0.4798 0.2669
-5.500 -0.2564 0.02820 0.01878 -0.0335 0.4783 0.3243
-5.250 -0.2403 0.02771 0.01875 -0.0325 0.4768 0.3949
-5.000 -0.2135 0.02896 0.02051 -0.0297 0.4753 0.4672
-4.750 -0.1813 0.03067 0.02234 -0.0275 0.4738 0.5097
-4.500 -0.1528 0.03149 0.02309 -0.0269 0.4724 0.5361
-4.250 -0.1291 0.03147 0.02290 -0.0275 0.4711 0.5620
-3.750 -0.0790 0.03216 0.02349 -0.0286 0.4676 0.5972
-3.500 -0.0515 0.03323 0.02457 -0.0277 0.4657 0.6050
-3.250 -0.0267 0.03343 0.02468 -0.0285 0.4638 0.6190
-3.000 -0.0002 0.03438 0.02562 -0.0274 0.4618 0.6264
-2.750 0.0250 0.03477 0.02591 -0.0277 0.4600 0.6389
-2.500 0.0510 0.03572 0.02685 -0.0261 0.4583 0.6446
-2.250 0.0765 0.03578 0.02678 -0.0272 0.4568 0.6573
-2.000 0.1015 0.03657 0.02755 -0.0255 0.4555 0.6610
-1.750 0.1269 0.03718 0.02811 -0.0244 0.4543 0.6660
-1.500 0.1523 0.03737 0.02820 -0.0246 0.4532 0.6744
-1.250 0.1780 0.03747 0.02819 -0.0250 0.4521 0.6806
-1.000 0.2032 0.03784 0.02850 -0.0242 0.4511 0.6835
-0.750 0.2237 0.03853 0.02924 -0.0236 0.4495 0.6872
-0.500 0.2409 0.03938 0.03021 -0.0236 0.4472 0.6920
-0.250 0.2601 0.04008 0.03095 -0.0249 0.4448 0.6979
0.000 0.2779 0.04085 0.03176 -0.0252 0.4424 0.7011
0.250 0.2943 0.04166 0.03261 -0.0246 0.4402 0.7030
0.500 0.3122 0.04236 0.03332 -0.0241 0.4383 0.7050
0.750 0.3311 0.04299 0.03394 -0.0238 0.4366 0.7075
1.000 0.3515 0.04352 0.03445 -0.0237 0.4351 0.7105
1.250 0.3756 0.04382 0.03469 -0.0240 0.4338 0.7139
1.500 0.4035 0.04395 0.03472 -0.0250 0.4327 0.7177
1.750 0.4357 0.04398 0.03462 -0.0270 0.4316 0.7216
2.000 0.4633 0.04407 0.03463 -0.0274 0.4307 0.7232
2.500 0.2375 0.06797 0.05954 -0.0226 0.4005 0.7278
4.500 0.3336 0.08285 0.07426 -0.0293 0.3784 0.7414
4.750 0.3574 0.08381 0.07516 -0.0305 0.3770 0.7436
5.000 0.3802 0.08459 0.07591 -0.0310 0.3758 0.7450
5.250 0.4037 0.08521 0.07650 -0.0314 0.3749 0.7460
5.500 0.4282 0.08577 0.07703 -0.0317 0.3741 0.7470
6.000 0.3918 0.09592 0.08737 -0.0336 0.3617 0.7492
6.250 0.4093 0.09729 0.08872 -0.0341 0.3601 0.7505
6.500 0.4301 0.09835 0.08976 -0.0347 0.3587 0.7516
6.750 0.4541 0.09906 0.09045 -0.0352 0.3576 0.7526
7.000 0.4794 0.09962 0.09098 -0.0358 0.3566 0.7537
7.500 0.4678 0.10693 0.09838 -0.0378 0.3441 0.7554
7.750 0.4891 0.10789 0.09933 -0.0385 0.3424 0.7564
8.000 0.5123 0.10867 0.10009 -0.0392 0.3410 0.7575
8.250 0.5361 0.10939 0.10078 -0.0398 0.3400 0.7586
8.500 0.5606 0.11009 0.10147 -0.0404 0.3392 0.7597
9.000 0.5388 0.11927 0.11079 -0.0431 0.3275 0.7612
9.250 0.5584 0.12055 0.11207 -0.0440 0.3258 0.7623
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