WORTMANN FX 77-W-343 AIRFOIL (fx77w343-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: WORTMANN FX 77-W-343 AIRFOIL (fx77w343-il) Reynolds number: 50,000 Max Cl/Cd: -0.14 at α=-2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w343-il-50000.txt Download as CSV file: xf-fx77w343-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.1814 0.15600 0.14910 -0.0456 0.6639 0.2248
-14.000 -0.1703 0.15147 0.14456 -0.0493 0.6630 0.2231
-13.750 -0.5505 0.08912 0.08144 -0.0688 0.6759 0.2051
-13.500 -0.5956 0.08228 0.07423 -0.0693 0.6762 0.2071
-13.250 -0.6272 0.07733 0.06890 -0.0693 0.6760 0.2100
-13.000 -0.5679 0.07878 0.07063 -0.0709 0.6729 0.2196
-12.750 -0.5614 0.07680 0.06856 -0.0714 0.6719 0.2273
-12.500 -0.5497 0.07553 0.06726 -0.0719 0.6709 0.2374
-12.250 -0.5154 0.07609 0.06799 -0.0725 0.6694 0.2514
-12.000 -0.4800 0.07716 0.06927 -0.0730 0.6683 0.2678
-11.750 -0.4529 0.07793 0.07020 -0.0738 0.6678 0.2864
-11.500 -0.3835 0.08357 0.07631 -0.0762 0.6668 0.3105
-11.250 -0.8355 0.08859 0.08075 -0.0549 0.8782 0.2231
-11.000 -0.7497 0.08998 0.08247 -0.0612 0.8515 0.2445
-10.750 -0.6910 0.09029 0.08300 -0.0647 0.8279 0.2698
-10.500 -0.6334 0.09058 0.08367 -0.0663 0.7905 0.3045
-10.250 -0.0972 0.11956 0.11259 -0.0802 0.6665 0.3836
-10.000 -0.0983 0.12661 0.11986 -0.0836 0.6819 0.3892
-9.750 -0.1018 0.12859 0.12185 -0.0828 0.6922 0.4042
-9.500 -0.0592 0.13172 0.12483 -0.0823 0.6896 0.4241
-8.750 -0.6538 0.11456 0.10902 -0.0339 0.8885 0.4017
-8.500 -0.6180 0.11953 0.11391 -0.0322 0.8693 0.4200
-7.750 -0.4673 0.13957 0.13359 -0.0315 0.8264 0.4631
-7.500 -0.4860 0.13894 0.13291 -0.0261 0.8134 0.4797
-7.250 -0.4367 0.14431 0.13814 -0.0275 0.8048 0.4994
-7.000 -0.3925 0.14924 0.14300 -0.0265 0.7886 0.5089
-6.750 -0.3429 0.15363 0.14725 -0.0289 0.7818 0.5315
-6.500 -0.3429 0.15442 0.14799 -0.0248 0.7680 0.5438
-6.250 -0.2966 0.15805 0.15150 -0.0267 0.7606 0.5662
-6.000 -0.2584 0.16229 0.15560 -0.0287 0.7575 0.5949
-5.750 -0.2719 0.16127 0.15459 -0.0228 0.7424 0.6054
-5.500 -0.1734 0.17147 0.16472 -0.0268 0.7364 0.6889
-5.250 -0.1703 0.16965 0.16288 -0.0247 0.7256 0.6996
-5.000 -0.1546 0.16951 0.16265 -0.0248 0.7186 0.7203
-4.750 -0.1309 0.17012 0.16312 -0.0264 0.7146 0.7410
-4.250 -0.1290 0.16883 0.16170 -0.0229 0.6983 0.7702
-4.000 -0.1097 0.16897 0.16173 -0.0239 0.6935 0.7873
-3.750 -0.0845 0.17047 0.16309 -0.0259 0.6908 0.8066
-3.500 -0.1046 0.16864 0.16126 -0.0213 0.6810 0.8190
-3.250 -0.0859 0.16815 0.16068 -0.0225 0.6745 0.8342
-3.000 -0.0606 0.16892 0.16133 -0.0244 0.6707 0.8527
-2.750 -0.0236 0.17110 0.16338 -0.0283 0.6685 0.8722
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