WORTMANN FX 77-080 (fx77080-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 77-080 (fx77080-il) Reynolds number: 500,000 Max Cl/Cd: 58.42 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77080-il-500000.txt Download as CSV file: xf-fx77080-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6290 0.09078 0.08857 -0.0048 1.0000 0.0176
-12.000 -0.9149 0.06235 0.05974 -0.0192 1.0000 0.0146
-11.750 -0.9382 0.05360 0.05078 -0.0278 1.0000 0.0145
-11.500 -0.9700 0.04669 0.04359 -0.0315 1.0000 0.0140
-11.250 -0.9861 0.04320 0.03989 -0.0304 1.0000 0.0142
-11.000 -1.0004 0.03988 0.03631 -0.0276 1.0000 0.0142
-10.750 -1.0039 0.03692 0.03307 -0.0254 1.0000 0.0144
-10.500 -1.0040 0.03392 0.02975 -0.0232 1.0000 0.0145
-10.250 -0.9990 0.03129 0.02682 -0.0210 1.0000 0.0147
-10.000 -0.9901 0.02899 0.02422 -0.0190 1.0000 0.0150
-9.750 -0.9768 0.02723 0.02221 -0.0173 1.0000 0.0152
-9.500 -0.9606 0.02591 0.02066 -0.0157 1.0000 0.0156
-9.250 -0.9483 0.02357 0.01804 -0.0138 1.0000 0.0159
-9.000 -0.9352 0.02136 0.01565 -0.0119 1.0000 0.0168
-8.750 -0.9154 0.02056 0.01482 -0.0107 1.0000 0.0177
-8.500 -0.8952 0.01972 0.01388 -0.0095 1.0000 0.0183
-8.250 -0.8752 0.01877 0.01282 -0.0082 1.0000 0.0191
-8.000 -0.8542 0.01801 0.01193 -0.0070 1.0000 0.0203
-7.750 -0.8325 0.01737 0.01119 -0.0058 1.0000 0.0210
-7.500 -0.8165 0.01576 0.00946 -0.0038 1.0000 0.0224
-7.250 -0.7958 0.01507 0.00873 -0.0026 1.0000 0.0240
-7.000 -0.7738 0.01458 0.00820 -0.0015 1.0000 0.0258
-6.750 -0.7513 0.01415 0.00769 -0.0004 1.0000 0.0276
-6.500 -0.7323 0.01326 0.00673 0.0013 1.0000 0.0301
-6.250 -0.7112 0.01271 0.00617 0.0027 1.0000 0.0331
-6.000 -0.6890 0.01232 0.00574 0.0038 1.0000 0.0360
-5.750 -0.6686 0.01170 0.00510 0.0054 1.0000 0.0408
-5.500 -0.6468 0.01132 0.00469 0.0066 1.0000 0.0461
-5.250 -0.6258 0.01082 0.00422 0.0080 1.0000 0.0541
-5.000 -0.6047 0.01040 0.00385 0.0094 1.0000 0.0679
-4.750 -0.5836 0.01000 0.00357 0.0108 1.0000 0.0908
-4.500 -0.5616 0.00974 0.00337 0.0119 1.0000 0.1112
-4.250 -0.5396 0.00951 0.00319 0.0131 1.0000 0.1276
-4.000 -0.5176 0.00931 0.00303 0.0143 1.0000 0.1421
-3.750 -0.4957 0.00911 0.00288 0.0155 1.0000 0.1564
-3.500 -0.4739 0.00892 0.00274 0.0168 1.0000 0.1714
-3.250 -0.4522 0.00874 0.00260 0.0180 1.0000 0.1875
-3.000 -0.4308 0.00854 0.00250 0.0193 1.0000 0.2101
-2.750 -0.4099 0.00832 0.00241 0.0206 1.0000 0.2417
-2.500 -0.3806 0.00800 0.00234 0.0200 0.9982 0.2968
-2.250 -0.3447 0.00760 0.00225 0.0180 0.9942 0.3739
-2.000 -0.3079 0.00718 0.00219 0.0159 0.9903 0.4608
-1.750 -0.2730 0.00673 0.00211 0.0143 0.9848 0.5537
-1.500 -0.2380 0.00635 0.00203 0.0128 0.9791 0.6338
-1.250 -0.2011 0.00597 0.00196 0.0111 0.9734 0.7101
-1.000 -0.1674 0.00564 0.00190 0.0103 0.9655 0.7806
-0.750 -0.1243 0.00538 0.00184 0.0075 0.9598 0.8379
-0.500 -0.0848 0.00523 0.00181 0.0055 0.9486 0.8783
-0.250 -0.0439 0.00517 0.00181 0.0031 0.9381 0.9061
0.000 -0.0002 0.00515 0.00180 0.0000 0.9245 0.9239
0.250 0.0443 0.00517 0.00180 -0.0032 0.9042 0.9376
0.500 0.0847 0.00524 0.00180 -0.0054 0.8747 0.9484
0.750 0.1243 0.00538 0.00184 -0.0075 0.8374 0.9598
1.000 0.1691 0.00565 0.00192 -0.0106 0.7831 0.9661
1.250 0.2024 0.00598 0.00198 -0.0114 0.7110 0.9736
1.500 0.2380 0.00634 0.00203 -0.0128 0.6343 0.9791
1.750 0.2725 0.00674 0.00211 -0.0142 0.5513 0.9847
2.000 0.3083 0.00718 0.00219 -0.0160 0.4608 0.9903
2.250 0.3452 0.00760 0.00225 -0.0181 0.3738 0.9943
2.500 0.3813 0.00800 0.00234 -0.0201 0.2967 0.9984
2.750 0.4099 0.00832 0.00242 -0.0206 0.2413 1.0000
3.000 0.4308 0.00854 0.00250 -0.0193 0.2094 1.0000
3.250 0.4522 0.00874 0.00261 -0.0180 0.1874 1.0000
3.500 0.4738 0.00893 0.00274 -0.0167 0.1706 1.0000
3.750 0.4955 0.00913 0.00288 -0.0155 0.1553 1.0000
4.000 0.5175 0.00931 0.00303 -0.0143 0.1419 1.0000
4.250 0.5396 0.00951 0.00319 -0.0131 0.1278 1.0000
4.500 0.5616 0.00974 0.00337 -0.0119 0.1112 1.0000
4.750 0.5836 0.00999 0.00358 -0.0107 0.0917 1.0000
5.000 0.6047 0.01039 0.00385 -0.0094 0.0686 1.0000
5.250 0.6259 0.01082 0.00422 -0.0080 0.0544 1.0000
5.500 0.6467 0.01132 0.00469 -0.0066 0.0460 1.0000
5.750 0.6686 0.01170 0.00510 -0.0054 0.0408 1.0000
6.000 0.6890 0.01232 0.00574 -0.0038 0.0360 1.0000
6.250 0.7113 0.01269 0.00615 -0.0027 0.0329 1.0000
6.500 0.7322 0.01327 0.00674 -0.0013 0.0299 1.0000
6.750 0.7516 0.01410 0.00765 0.0003 0.0274 1.0000
7.000 0.7741 0.01453 0.00815 0.0014 0.0255 1.0000
7.250 0.7958 0.01507 0.00873 0.0026 0.0239 1.0000
7.500 0.8163 0.01579 0.00948 0.0039 0.0223 1.0000
7.750 0.8324 0.01740 0.01121 0.0059 0.0209 1.0000
8.000 0.8542 0.01802 0.01195 0.0070 0.0201 1.0000
8.250 0.8746 0.01893 0.01299 0.0083 0.0194 1.0000
8.500 0.8952 0.01974 0.01391 0.0096 0.0184 1.0000
8.750 0.9156 0.02050 0.01474 0.0107 0.0175 1.0000
9.000 0.9352 0.02134 0.01562 0.0119 0.0167 1.0000
9.250 0.9478 0.02369 0.01817 0.0138 0.0159 1.0000
9.500 0.9616 0.02568 0.02043 0.0156 0.0155 1.0000
9.750 0.9772 0.02716 0.02213 0.0172 0.0153 1.0000
10.000 0.9895 0.02911 0.02436 0.0190 0.0150 1.0000
10.250 0.9999 0.03115 0.02666 0.0209 0.0147 1.0000
10.500 1.0051 0.03377 0.02959 0.0231 0.0144 1.0000
10.750 1.0054 0.03675 0.03287 0.0253 0.0144 1.0000
11.000 1.0023 0.03968 0.03609 0.0275 0.0140 1.0000
11.250 0.9868 0.04315 0.03984 0.0303 0.0139 1.0000
11.500 0.9624 0.04771 0.04466 0.0311 0.0143 1.0000
11.750 0.9463 0.05246 0.04961 0.0284 0.0140 1.0000
12.000 0.9131 0.06319 0.06060 0.0180 0.0144 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 77-080 (fx77080-il)