WORTMANN FX 77-W-343 AIRFOIL (fx77w343-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: WORTMANN FX 77-W-343 AIRFOIL (fx77w343-il) Reynolds number: 200,000 Max Cl/Cd: 20.76 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w343-il-200000-n5.txt Download as CSV file: xf-fx77w343-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-W-343 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -0.8591 0.10767 0.09894 -0.0176 0.5010 0.0444
-18.500 -0.8537 0.10485 0.09609 -0.0188 0.4984 0.0449
-18.250 -0.8484 0.10204 0.09323 -0.0199 0.4958 0.0455
-18.000 -0.8417 0.09943 0.09055 -0.0209 0.4933 0.0462
-17.750 -0.8345 0.09690 0.08795 -0.0218 0.4910 0.0469
-17.500 -0.8271 0.09440 0.08536 -0.0226 0.4889 0.0476
-17.250 -0.8194 0.09197 0.08287 -0.0234 0.4869 0.0483
-17.000 -0.8115 0.08953 0.08038 -0.0243 0.4851 0.0490
-16.750 -0.8027 0.08725 0.07807 -0.0250 0.4834 0.0499
-16.500 -0.7928 0.08512 0.07590 -0.0256 0.4815 0.0508
-16.250 -0.7825 0.08304 0.07377 -0.0262 0.4796 0.0519
-16.000 -0.7721 0.08099 0.07168 -0.0267 0.4776 0.0529
-15.750 -0.7607 0.07908 0.06972 -0.0272 0.4756 0.0540
-15.500 -0.7488 0.07725 0.06782 -0.0277 0.4737 0.0552
-15.250 -0.7364 0.07548 0.06595 -0.0281 0.4719 0.0565
-15.000 -0.7246 0.07369 0.06410 -0.0285 0.4703 0.0576
-14.750 -0.7124 0.07195 0.06229 -0.0288 0.4687 0.0587
-14.500 -0.6998 0.07028 0.06052 -0.0291 0.4673 0.0600
-14.250 -0.6860 0.06872 0.05886 -0.0294 0.4660 0.0613
-14.000 -0.6740 0.06702 0.05713 -0.0297 0.4649 0.0624
-13.750 -0.6622 0.06531 0.05539 -0.0299 0.4637 0.0637
-13.500 -0.6494 0.06372 0.05375 -0.0301 0.4626 0.0652
-13.250 -0.6349 0.06232 0.05228 -0.0303 0.4613 0.0668
-13.000 -0.6249 0.06055 0.05051 -0.0303 0.4602 0.0680
-12.750 -0.6136 0.05891 0.04884 -0.0304 0.4591 0.0695
-12.500 -0.6010 0.05740 0.04728 -0.0305 0.4579 0.0710
-12.250 -0.5882 0.05593 0.04578 -0.0305 0.4568 0.0724
-12.000 -0.5766 0.05440 0.04423 -0.0305 0.4557 0.0739
-11.750 -0.5642 0.05295 0.04276 -0.0304 0.4547 0.0756
-11.500 -0.5510 0.05159 0.04139 -0.0304 0.4537 0.0775
-11.250 -0.5379 0.05026 0.04006 -0.0303 0.4527 0.0798
-11.000 -0.5247 0.04896 0.03877 -0.0302 0.4518 0.0826
-10.750 -0.5111 0.04772 0.03753 -0.0301 0.4509 0.0871
-10.500 -0.4957 0.04666 0.03642 -0.0300 0.4499 0.0929
-10.250 -0.4797 0.04567 0.03538 -0.0299 0.4490 0.0981
-10.000 -0.4636 0.04471 0.03436 -0.0298 0.4480 0.1028
-9.750 -0.4507 0.04357 0.03320 -0.0295 0.4471 0.1073
-9.500 -0.4383 0.04241 0.03207 -0.0292 0.4464 0.1123
-9.250 -0.4269 0.04121 0.03095 -0.0287 0.4458 0.1190
-9.000 -0.4164 0.04003 0.02985 -0.0280 0.4452 0.1320
-8.750 -0.4016 0.03913 0.02896 -0.0276 0.4445 0.1435
-8.500 -0.3906 0.03803 0.02789 -0.0270 0.4438 0.1528
-8.250 -0.3848 0.03665 0.02665 -0.0259 0.4431 0.1646
-8.000 -0.3785 0.03534 0.02545 -0.0247 0.4424 0.1875
-7.750 -0.3704 0.03415 0.02432 -0.0236 0.4415 0.2023
-7.500 -0.3704 0.03257 0.02289 -0.0218 0.4407 0.2194
-7.250 -0.3735 0.03113 0.02155 -0.0192 0.4399 0.2451
-7.000 -0.3852 0.02980 0.02029 -0.0153 0.4391 0.2611
-6.750 -0.3881 0.02799 0.01866 -0.0139 0.4383 0.2917
-6.500 -0.3738 0.02630 0.01715 -0.0156 0.4373 0.3290
-6.250 -0.3499 0.02485 0.01603 -0.0186 0.4362 0.3882
-6.000 -0.3203 0.02437 0.01577 -0.0204 0.4349 0.4415
-5.750 -0.2901 0.02447 0.01607 -0.0211 0.4338 0.4692
-5.500 -0.2580 0.02449 0.01611 -0.0225 0.4327 0.4929
-5.250 -0.2269 0.02488 0.01656 -0.0229 0.4319 0.5071
-5.000 -0.1956 0.02530 0.01701 -0.0235 0.4311 0.5184
-4.750 -0.1649 0.02602 0.01778 -0.0233 0.4303 0.5258
-4.500 -0.1327 0.02629 0.01800 -0.0245 0.4294 0.5348
-4.250 -0.1007 0.02668 0.01834 -0.0255 0.4285 0.5427
-4.000 -0.0646 0.02619 0.01767 -0.0291 0.4274 0.5559
-3.750 -0.0339 0.02674 0.01826 -0.0295 0.4268 0.5591
-3.500 -0.0025 0.02714 0.01868 -0.0303 0.4261 0.5629
-3.250 0.0301 0.02729 0.01882 -0.0319 0.4253 0.5682
-3.000 0.0650 0.02710 0.01857 -0.0347 0.4244 0.5754
-2.750 0.0951 0.02765 0.01915 -0.0351 0.4235 0.5774
-2.500 0.1255 0.02820 0.01973 -0.0357 0.4226 0.5801
-2.250 0.1564 0.02870 0.02025 -0.0365 0.4216 0.5838
-2.000 0.1899 0.02888 0.02039 -0.0386 0.4206 0.5909
-1.750 0.2210 0.02935 0.02085 -0.0397 0.4196 0.5952
-1.500 0.2501 0.03004 0.02158 -0.0399 0.4186 0.5981
-1.250 0.2800 0.03062 0.02216 -0.0405 0.4177 0.6023
-1.000 0.3165 0.03052 0.02195 -0.0439 0.4167 0.6114
-0.750 0.3447 0.03111 0.02256 -0.0440 0.4158 0.6131
-0.500 0.3735 0.03156 0.02302 -0.0444 0.4148 0.6149
-0.250 0.4029 0.03194 0.02338 -0.0450 0.4139 0.6170
0.000 0.4333 0.03219 0.02360 -0.0460 0.4130 0.6199
0.250 0.4665 0.03223 0.02355 -0.0480 0.4121 0.6243
0.500 0.5033 0.03203 0.02321 -0.0513 0.4113 0.6297
0.750 0.5323 0.03232 0.02348 -0.0519 0.4106 0.6308
1.000 0.5614 0.03266 0.02380 -0.0525 0.4098 0.6319
1.250 0.5903 0.03307 0.02417 -0.0533 0.4091 0.6332
1.500 0.6155 0.03360 0.02480 -0.0538 0.4082 0.6346
1.750 0.6393 0.03422 0.02551 -0.0543 0.4070 0.6361
2.000 0.6619 0.03489 0.02628 -0.0547 0.4057 0.6378
2.250 0.6836 0.03560 0.02708 -0.0552 0.4042 0.6399
2.500 0.7045 0.03632 0.02786 -0.0557 0.4028 0.6423
2.750 0.7255 0.03700 0.02858 -0.0565 0.4013 0.6450
3.000 0.7475 0.03762 0.02919 -0.0577 0.3999 0.6480
3.250 0.7645 0.03835 0.02996 -0.0576 0.3986 0.6495
3.500 0.7780 0.03912 0.03078 -0.0568 0.3974 0.6505
3.750 0.7905 0.03984 0.03154 -0.0558 0.3962 0.6515
4.000 0.7979 0.04059 0.03233 -0.0540 0.3951 0.6525
4.250 0.8046 0.04133 0.03309 -0.0523 0.3941 0.6536
4.500 0.8247 0.04177 0.03351 -0.0523 0.3933 0.6549
4.750 0.8503 0.04204 0.03374 -0.0528 0.3926 0.6565
5.000 0.8777 0.04228 0.03394 -0.0536 0.3919 0.6582
6.500 0.3991 0.11206 0.10503 -0.0452 0.3302 0.6634
6.750 0.4206 0.11304 0.10597 -0.0464 0.3293 0.6651
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