WORTMANN FX 76-100 (fx76100-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 76-100 (fx76100-il) Reynolds number: 50,000 Max Cl/Cd: 25.55 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76100-il-50000.txt Download as CSV file: xf-fx76100-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 76-100
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6750 0.09203 0.08468 -0.0120 1.0000 0.1714
-9.500 -0.6747 0.08633 0.07898 -0.0137 1.0000 0.1676
-9.250 -0.7829 0.07077 0.06337 -0.0231 1.0000 0.1419
-9.000 -0.7914 0.06570 0.05813 -0.0226 1.0000 0.1404
-8.750 -0.8012 0.06075 0.05293 -0.0215 1.0000 0.1400
-8.500 -0.8110 0.05593 0.04773 -0.0199 1.0000 0.1404
-8.250 -0.8051 0.05230 0.04396 -0.0184 1.0000 0.1439
-8.000 -0.7962 0.04913 0.04061 -0.0167 1.0000 0.1478
-7.750 -0.7921 0.04528 0.03633 -0.0146 1.0000 0.1503
-7.500 -0.7881 0.04178 0.03215 -0.0120 1.0000 0.1550
-7.250 -0.7701 0.03960 0.03002 -0.0106 1.0000 0.1638
-7.000 -0.7594 0.03663 0.02646 -0.0082 1.0000 0.1713
-6.750 -0.7411 0.03466 0.02440 -0.0066 1.0000 0.1836
-6.500 -0.7234 0.03274 0.02234 -0.0048 1.0000 0.1986
-6.250 -0.7052 0.03084 0.02033 -0.0030 1.0000 0.2167
-6.000 -0.6862 0.02936 0.01895 -0.0012 1.0000 0.2406
-5.750 -0.6683 0.02790 0.01757 0.0009 1.0000 0.2705
-5.500 -0.6516 0.02655 0.01623 0.0032 1.0000 0.3066
-5.250 -0.6333 0.02541 0.01536 0.0055 1.0000 0.3448
-5.000 -0.6165 0.02441 0.01440 0.0079 1.0000 0.3854
-4.750 -0.5980 0.02355 0.01377 0.0102 1.0000 0.4248
-4.500 -0.5799 0.02271 0.01307 0.0126 1.0000 0.4653
-4.250 -0.5611 0.02196 0.01248 0.0150 1.0000 0.5065
-4.000 -0.5415 0.02126 0.01198 0.0175 1.0000 0.5499
-3.750 -0.5217 0.02061 0.01150 0.0201 1.0000 0.5976
-3.500 -0.5012 0.02005 0.01114 0.0227 1.0000 0.6509
-3.250 -0.4790 0.01973 0.01105 0.0258 1.0000 0.7092
-3.000 -0.4524 0.01976 0.01120 0.0286 1.0000 0.7726
-2.750 -0.4050 0.02039 0.01177 0.0285 1.0000 0.8382
-2.500 -0.3073 0.02152 0.01247 0.0189 1.0000 0.8999
-2.250 -0.1735 0.02175 0.01213 0.0002 1.0000 0.9510
-2.000 -0.0562 0.02068 0.01068 -0.0181 1.0000 0.9957
-1.750 -0.0379 0.01989 0.00982 -0.0189 1.0000 1.0000
-1.500 -0.0319 0.01933 0.00925 -0.0169 1.0000 1.0000
-1.250 -0.0259 0.01889 0.00880 -0.0147 1.0000 1.0000
-1.000 -0.0198 0.01856 0.00846 -0.0122 1.0000 1.0000
-0.750 -0.0141 0.01831 0.00821 -0.0094 1.0000 1.0000
-0.500 -0.0088 0.01813 0.00805 -0.0064 1.0000 1.0000
-0.250 -0.0042 0.01803 0.00795 -0.0033 1.0000 1.0000
0.000 0.0000 0.01800 0.00791 0.0000 1.0000 1.0000
0.250 0.0043 0.01803 0.00795 0.0033 1.0000 1.0000
0.500 0.0089 0.01813 0.00804 0.0065 1.0000 1.0000
0.750 0.0141 0.01830 0.00821 0.0094 1.0000 1.0000
1.000 0.0199 0.01855 0.00846 0.0122 1.0000 1.0000
1.250 0.0259 0.01889 0.00880 0.0147 1.0000 1.0000
1.500 0.0319 0.01933 0.00925 0.0169 1.0000 1.0000
1.750 0.0380 0.01988 0.00982 0.0189 1.0000 1.0000
2.000 0.0558 0.02067 0.01066 0.0182 0.9958 1.0000
2.250 0.1744 0.02174 0.01213 -0.0003 0.9507 1.0000
2.500 0.3074 0.02152 0.01246 -0.0189 0.8999 1.0000
2.750 0.4050 0.02038 0.01177 -0.0284 0.8381 1.0000
3.000 0.4522 0.01976 0.01119 -0.0286 0.7724 1.0000
3.250 0.4789 0.01973 0.01105 -0.0257 0.7090 1.0000
3.500 0.5012 0.02005 0.01113 -0.0227 0.6507 1.0000
3.750 0.5216 0.02061 0.01150 -0.0200 0.5972 1.0000
4.000 0.5414 0.02126 0.01195 -0.0175 0.5497 1.0000
4.250 0.5611 0.02196 0.01248 -0.0151 0.5067 1.0000
4.500 0.5799 0.02272 0.01308 -0.0126 0.4652 1.0000
4.750 0.5980 0.02355 0.01378 -0.0102 0.4248 1.0000
5.000 0.6165 0.02442 0.01441 -0.0079 0.3854 1.0000
5.250 0.6332 0.02540 0.01534 -0.0054 0.3448 1.0000
5.500 0.6515 0.02654 0.01621 -0.0032 0.3066 1.0000
5.750 0.6682 0.02789 0.01756 -0.0009 0.2705 1.0000
6.000 0.6860 0.02935 0.01895 0.0012 0.2403 1.0000
6.250 0.7053 0.03084 0.02032 0.0030 0.2165 1.0000
6.500 0.7232 0.03275 0.02236 0.0048 0.1983 1.0000
6.750 0.7410 0.03467 0.02441 0.0066 0.1834 1.0000
7.000 0.7595 0.03663 0.02644 0.0082 0.1711 1.0000
7.250 0.7701 0.03963 0.03005 0.0106 0.1638 1.0000
7.500 0.7883 0.04179 0.03216 0.0120 0.1551 1.0000
7.750 0.7920 0.04530 0.03635 0.0146 0.1503 1.0000
8.000 0.7963 0.04911 0.04059 0.0167 0.1478 1.0000
8.250 0.8031 0.05251 0.04422 0.0184 0.1444 1.0000
8.500 0.8114 0.05595 0.04775 0.0198 0.1404 1.0000
8.750 0.8016 0.06075 0.05294 0.0215 0.1400 1.0000
9.000 0.7921 0.06567 0.05810 0.0226 0.1404 1.0000
9.250 0.7823 0.07083 0.06343 0.0231 0.1419 1.0000
9.500 0.6036 0.10102 0.09344 -0.0039 0.2501 1.0000
9.750 0.5866 0.11180 0.10416 -0.0130 0.3222 1.0000
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Polar data table (+)
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