WORTMANN FX 77-W-343 AIRFOIL (fx77w343-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 77-W-343 AIRFOIL (fx77w343-il) Reynolds number: 200,000 Max Cl/Cd: 3.55 at α=-1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w343-il-200000.txt Download as CSV file: xf-fx77w343-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -0.9886 0.10125 0.09320 -0.0252 0.5905 0.0560
-19.500 -0.9914 0.09753 0.08916 -0.0265 0.5843 0.0567
-19.250 -0.9751 0.09633 0.08797 -0.0269 0.5763 0.0574
-19.000 -0.9617 0.09477 0.08634 -0.0274 0.5699 0.0581
-18.750 -0.9511 0.09283 0.08428 -0.0280 0.5646 0.0590
-18.500 -0.9442 0.09039 0.08174 -0.0287 0.5601 0.0601
-18.250 -0.9411 0.08750 0.07866 -0.0295 0.5561 0.0612
-18.000 -0.9285 0.08585 0.07694 -0.0298 0.5518 0.0622
-17.750 -0.9108 0.08486 0.07595 -0.0300 0.5478 0.0633
-17.500 -0.8993 0.08309 0.07407 -0.0304 0.5445 0.0646
-17.250 -0.8920 0.08074 0.07160 -0.0309 0.5416 0.0660
-17.000 -0.8783 0.07923 0.07004 -0.0311 0.5382 0.0673
-16.750 -0.8579 0.07860 0.06948 -0.0311 0.5346 0.0687
-16.500 -0.8440 0.07715 0.06798 -0.0312 0.5317 0.0702
-16.250 -0.8340 0.07520 0.06585 -0.0316 0.5291 0.0717
-16.000 -0.8126 0.07480 0.06550 -0.0314 0.5262 0.0732
-15.750 -0.7960 0.07368 0.06444 -0.0315 0.5241 0.0748
-15.500 -0.7815 0.07227 0.06301 -0.0317 0.5220 0.0764
-15.250 -0.7657 0.07108 0.06182 -0.0318 0.5198 0.0779
-15.000 -0.7500 0.06990 0.06070 -0.0319 0.5177 0.0794
-14.750 -0.7354 0.06855 0.05934 -0.0321 0.5157 0.0810
-14.500 -0.7202 0.06727 0.05800 -0.0322 0.5138 0.0827
-14.250 -0.7048 0.06608 0.05684 -0.0323 0.5120 0.0842
-14.000 -0.6898 0.06483 0.05558 -0.0324 0.5104 0.0858
-13.750 -0.6743 0.06364 0.05433 -0.0325 0.5088 0.0878
-13.500 -0.6589 0.06251 0.05316 -0.0326 0.5071 0.0897
-13.250 -0.6441 0.06135 0.05201 -0.0328 0.5055 0.0917
-13.000 -0.6288 0.06012 0.05076 -0.0329 0.5045 0.0945
-12.750 -0.6145 0.05887 0.04955 -0.0329 0.5034 0.0973
-12.500 -0.6000 0.05764 0.04833 -0.0329 0.5022 0.1010
-12.250 -0.5879 0.05630 0.04705 -0.0327 0.5010 0.1046
-12.000 -0.5759 0.05494 0.04571 -0.0325 0.4999 0.1089
-11.750 -0.5681 0.05328 0.04415 -0.0322 0.4988 0.1130
-11.500 -0.5586 0.05175 0.04270 -0.0319 0.4977 0.1182
-11.250 -0.5492 0.05023 0.04126 -0.0317 0.4967 0.1247
-11.000 -0.5390 0.04880 0.03989 -0.0314 0.4957 0.1343
-10.750 -0.5301 0.04734 0.03848 -0.0310 0.4948 0.1458
-10.500 -0.5253 0.04565 0.03689 -0.0303 0.4939 0.1574
-10.250 -0.5236 0.04379 0.03520 -0.0294 0.4931 0.1726
-10.000 -0.5179 0.04230 0.03378 -0.0286 0.4923 0.1959
-9.750 -0.5205 0.04042 0.03207 -0.0271 0.4917 0.2140
-9.500 -0.5228 0.03863 0.03043 -0.0255 0.4910 0.2418
-9.250 -0.5277 0.03675 0.02871 -0.0236 0.4902 0.2653
-9.000 -0.5367 0.03472 0.02687 -0.0211 0.4893 0.2970
-8.750 -0.5463 0.03296 0.02524 -0.0181 0.4883 0.3235
-8.500 -0.5738 0.03124 0.02370 -0.0124 0.4875 0.3485
-8.250 -0.5792 0.02990 0.02252 -0.0106 0.4864 0.3846
-8.000 -0.5645 0.02900 0.02189 -0.0114 0.4852 0.4318
-7.750 -0.5375 0.02902 0.02212 -0.0120 0.4841 0.4597
-7.500 -0.5083 0.02931 0.02254 -0.0128 0.4829 0.4842
-7.250 -0.4787 0.02952 0.02282 -0.0140 0.4818 0.5030
-7.000 -0.4467 0.03052 0.02391 -0.0141 0.4805 0.5150
-6.750 -0.4129 0.03204 0.02552 -0.0136 0.4790 0.5229
-6.500 -0.3833 0.03198 0.02543 -0.0158 0.4777 0.5369
-6.250 -0.3489 0.03373 0.02722 -0.0153 0.4764 0.5412
-6.000 -0.3210 0.03303 0.02640 -0.0187 0.4753 0.5566
-5.750 -0.2877 0.03473 0.02814 -0.0181 0.4741 0.5590
-5.500 -0.2538 0.03646 0.02987 -0.0177 0.4730 0.5612
-5.250 -0.2263 0.03562 0.02888 -0.0210 0.4719 0.5751
-5.000 -0.1943 0.03719 0.03046 -0.0205 0.4708 0.5763
-4.750 -0.1620 0.03880 0.03205 -0.0199 0.4698 0.5772
-4.500 -0.1301 0.04031 0.03353 -0.0194 0.4687 0.5783
-4.250 -0.0990 0.04179 0.03498 -0.0190 0.4677 0.5796
-4.000 -0.0701 0.04354 0.03670 -0.0188 0.4665 0.5814
-3.750 -0.0495 0.04276 0.03591 -0.0224 0.4654 0.5939
-3.500 -0.0264 0.04460 0.03794 -0.0220 0.4637 0.5949
-3.250 -0.0090 0.04694 0.04047 -0.0215 0.4607 0.5961
-3.000 0.0054 0.04933 0.04301 -0.0207 0.4576 0.5977
-2.750 0.0201 0.04945 0.04309 -0.0250 0.4551 0.6108
-2.500 0.0363 0.05114 0.04483 -0.0238 0.4533 0.6117
-2.250 0.0584 0.05225 0.04594 -0.0227 0.4520 0.6129
-2.000 0.0845 0.05307 0.04673 -0.0216 0.4510 0.6141
-1.750 0.1135 0.05373 0.04734 -0.0206 0.4501 0.6157
-1.500 0.1435 0.05434 0.04789 -0.0198 0.4494 0.6184
-1.250 0.1749 0.05359 0.04698 -0.0241 0.4484 0.6304
-1.000 0.1962 0.05519 0.04857 -0.0220 0.4474 0.6316
-0.250 -0.2575 0.10018 0.09474 -0.0122 0.4373 0.6335
0.000 -0.2424 0.10161 0.09616 -0.0109 0.4345 0.6353
0.750 -0.1610 0.10549 0.09986 -0.0140 0.4302 0.6503
1.000 -0.1393 0.10700 0.10139 -0.0120 0.4295 0.6521
1.250 -0.1168 0.10867 0.10306 -0.0098 0.4288 0.6544
1.500 -0.0917 0.11051 0.10490 -0.0081 0.4283 0.6577
1.750 -0.0591 0.11261 0.10696 -0.0086 0.4278 0.6632
2.000 -0.1387 0.11540 0.10987 -0.0083 0.4141 0.6633
2.250 -0.1036 0.11674 0.11110 -0.0125 0.4127 0.6708
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