WORTMANN FX 76-120 (fx76120-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 76-120 (fx76120-il) Reynolds number: 50,000 Max Cl/Cd: 25.03 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76120-il-50000.txt Download as CSV file: xf-fx76120-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 76-120
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7080 0.08225 0.07449 -0.0254 1.0000 0.1809
-10.000 -0.7327 0.07533 0.06758 -0.0276 1.0000 0.1792
-9.750 -0.7674 0.06914 0.06139 -0.0275 1.0000 0.1771
-9.500 -0.8045 0.06324 0.05538 -0.0260 1.0000 0.1750
-9.250 -0.8315 0.05805 0.04996 -0.0236 1.0000 0.1748
-9.000 -0.8474 0.05364 0.04523 -0.0209 1.0000 0.1766
-8.750 -0.8604 0.04954 0.04070 -0.0177 1.0000 0.1795
-8.500 -0.8493 0.04724 0.03834 -0.0158 1.0000 0.1870
-8.250 -0.8473 0.04442 0.03519 -0.0130 1.0000 0.1941
-8.000 -0.8371 0.04208 0.03273 -0.0107 1.0000 0.2027
-7.750 -0.8350 0.03961 0.02977 -0.0074 1.0000 0.2130
-7.500 -0.8170 0.03800 0.02825 -0.0057 1.0000 0.2263
-7.250 -0.8029 0.03640 0.02659 -0.0035 1.0000 0.2415
-7.000 -0.7894 0.03479 0.02488 -0.0011 1.0000 0.2586
-6.750 -0.7770 0.03331 0.02325 0.0015 1.0000 0.2778
-6.500 -0.7581 0.03220 0.02233 0.0034 1.0000 0.2985
-6.250 -0.7418 0.03111 0.02126 0.0057 1.0000 0.3206
-6.000 -0.7285 0.02995 0.01995 0.0082 1.0000 0.3435
-5.750 -0.7089 0.02909 0.01927 0.0102 1.0000 0.3658
-5.500 -0.6923 0.02817 0.01834 0.0124 1.0000 0.3888
-5.250 -0.6755 0.02724 0.01742 0.0147 1.0000 0.4119
-5.000 -0.6565 0.02646 0.01672 0.0167 1.0000 0.4350
-4.750 -0.6403 0.02558 0.01579 0.0189 1.0000 0.4594
-4.500 -0.6200 0.02487 0.01524 0.0208 1.0000 0.4834
-4.250 -0.6030 0.02410 0.01444 0.0230 1.0000 0.5099
-4.000 -0.5825 0.02349 0.01400 0.0250 1.0000 0.5370
-3.750 -0.5634 0.02288 0.01350 0.0272 1.0000 0.5672
-3.500 -0.5441 0.02233 0.01309 0.0294 1.0000 0.6006
-3.250 -0.5244 0.02188 0.01277 0.0318 1.0000 0.6381
-3.000 -0.5041 0.02155 0.01260 0.0343 1.0000 0.6801
-2.750 -0.4818 0.02145 0.01265 0.0368 1.0000 0.7259
-2.500 -0.4537 0.02169 0.01302 0.0390 1.0000 0.7742
-2.250 -0.4122 0.02235 0.01368 0.0391 1.0000 0.8241
-2.000 -0.3378 0.02346 0.01461 0.0334 1.0000 0.8717
-1.750 -0.2277 0.02432 0.01519 0.0203 1.0000 0.9141
-1.500 -0.1155 0.02428 0.01490 0.0051 1.0000 0.9525
-1.250 -0.0075 0.02340 0.01383 -0.0110 1.0000 0.9885
-1.000 0.0307 0.02256 0.01294 -0.0156 1.0000 1.0000
-0.750 0.0262 0.02216 0.01257 -0.0124 1.0000 1.0000
-0.500 0.0192 0.02189 0.01233 -0.0086 1.0000 1.0000
-0.250 0.0101 0.02174 0.01219 -0.0044 1.0000 1.0000
0.000 0.0000 0.02169 0.01214 0.0000 1.0000 1.0000
0.250 -0.0102 0.02174 0.01219 0.0044 1.0000 1.0000
0.500 -0.0192 0.02189 0.01232 0.0086 1.0000 1.0000
0.750 -0.0263 0.02216 0.01257 0.0124 1.0000 1.0000
1.000 -0.0307 0.02255 0.01293 0.0156 1.0000 1.0000
1.250 0.0076 0.02340 0.01382 0.0109 0.9885 1.0000
1.500 0.1153 0.02428 0.01490 -0.0051 0.9525 1.0000
1.750 0.2273 0.02433 0.01520 -0.0202 0.9141 1.0000
2.000 0.3379 0.02345 0.01462 -0.0334 0.8716 1.0000
2.250 0.4122 0.02235 0.01367 -0.0391 0.8240 1.0000
2.500 0.4537 0.02169 0.01301 -0.0390 0.7743 1.0000
2.750 0.4818 0.02145 0.01265 -0.0368 0.7259 1.0000
3.000 0.5041 0.02155 0.01260 -0.0343 0.6801 1.0000
3.250 0.5243 0.02188 0.01278 -0.0318 0.6382 1.0000
3.500 0.5440 0.02233 0.01308 -0.0294 0.6007 1.0000
3.750 0.5633 0.02288 0.01350 -0.0272 0.5672 1.0000
4.000 0.5825 0.02349 0.01400 -0.0250 0.5372 1.0000
4.250 0.6030 0.02410 0.01445 -0.0230 0.5100 1.0000
4.500 0.6200 0.02487 0.01523 -0.0208 0.4833 1.0000
4.750 0.6402 0.02558 0.01579 -0.0189 0.4593 1.0000
5.000 0.6565 0.02645 0.01671 -0.0167 0.4349 1.0000
5.250 0.6755 0.02724 0.01742 -0.0146 0.4119 1.0000
5.500 0.6923 0.02816 0.01833 -0.0125 0.3889 1.0000
5.750 0.7088 0.02908 0.01927 -0.0102 0.3659 1.0000
6.000 0.7284 0.02995 0.01995 -0.0082 0.3436 1.0000
6.250 0.7418 0.03111 0.02126 -0.0057 0.3206 1.0000
6.500 0.7580 0.03220 0.02233 -0.0034 0.2986 1.0000
6.750 0.7769 0.03331 0.02326 -0.0015 0.2778 1.0000
7.000 0.7894 0.03480 0.02488 0.0011 0.2586 1.0000
7.250 0.8029 0.03640 0.02660 0.0035 0.2416 1.0000
7.500 0.8172 0.03800 0.02825 0.0057 0.2264 1.0000
7.750 0.8350 0.03960 0.02976 0.0074 0.2130 1.0000
8.000 0.8369 0.04212 0.03278 0.0108 0.2029 1.0000
8.250 0.8474 0.04441 0.03518 0.0130 0.1941 1.0000
8.500 0.8498 0.04719 0.03828 0.0158 0.1868 1.0000
8.750 0.8604 0.04956 0.04071 0.0177 0.1795 1.0000
9.000 0.8473 0.05362 0.04522 0.0210 0.1764 1.0000
9.250 0.8314 0.05806 0.04997 0.0237 0.1747 1.0000
9.500 0.8048 0.06323 0.05536 0.0259 0.1750 1.0000
9.750 0.7678 0.06917 0.06142 0.0274 0.1771 1.0000
10.000 0.7328 0.07540 0.06766 0.0275 0.1793 1.0000
10.250 0.7093 0.08220 0.07443 0.0254 0.1809 1.0000
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Polar data table (+)
Polar graphs
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