WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 74-080 (fx74080-il) Reynolds number: 500,000 Max Cl/Cd: 131.48 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74080-il-500000-n5.txt Download as CSV file: xf-fx74080-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 74-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1876 0.09632 0.09335 -0.0851 0.8632 0.0076
-9.250 -0.1766 0.09306 0.09005 -0.0878 0.8594 0.0077
-9.000 -0.1662 0.09009 0.08708 -0.0904 0.8557 0.0078
-8.750 -0.1560 0.08683 0.08381 -0.0933 0.8522 0.0080
-8.500 -0.1453 0.08357 0.08053 -0.0961 0.8491 0.0080
-7.750 -0.0569 0.05257 0.04964 -0.1021 0.8321 0.0080
-7.500 -0.0586 0.04818 0.04528 -0.1026 0.8297 0.0065
-7.250 -0.0568 0.04483 0.04195 -0.1041 0.8269 0.0056
-7.000 -0.0950 0.06210 0.05905 -0.1139 0.8320 0.0063
-6.750 -0.0842 0.05781 0.05476 -0.1186 0.8290 0.0055
-6.500 -0.0709 0.05347 0.05037 -0.1231 0.8261 0.0046
-6.250 -0.0557 0.04889 0.04571 -0.1272 0.8234 0.0045
-6.000 -0.0384 0.04467 0.04138 -0.1305 0.8213 0.0045
-5.750 -0.0205 0.04009 0.03665 -0.1330 0.8188 0.0043
-5.500 -0.0018 0.03649 0.03290 -0.1343 0.8161 0.0045
-5.250 0.0184 0.03321 0.02944 -0.1352 0.8134 0.0050
-5.000 0.0399 0.02987 0.02589 -0.1355 0.8109 0.0057
-4.250 0.1108 0.02228 0.01752 -0.1348 0.8043 0.0079
-4.000 0.1330 0.01925 0.01413 -0.1341 0.8020 0.0076
-3.750 0.1566 0.01686 0.01137 -0.1335 0.7999 0.0073
-3.500 0.1814 0.01478 0.00893 -0.1328 0.7979 0.0071
-3.250 0.2069 0.01314 0.00698 -0.1323 0.7961 0.0071
-3.000 0.2328 0.01186 0.00545 -0.1318 0.7945 0.0071
-2.750 0.2581 0.01092 0.00435 -0.1313 0.7927 0.0073
-2.500 0.2830 0.01024 0.00358 -0.1307 0.7905 0.0080
-2.250 0.3077 0.00956 0.00279 -0.1302 0.7884 0.0100
-2.000 0.3340 0.00936 0.00254 -0.1300 0.7862 0.0152
-1.750 0.3602 0.00908 0.00216 -0.1298 0.7842 0.0162
-1.500 0.3869 0.00885 0.00187 -0.1296 0.7823 0.0251
-1.250 0.4138 0.00870 0.00175 -0.1296 0.7806 0.0501
-1.000 0.4384 0.00836 0.00170 -0.1293 0.7782 0.1443
-0.750 0.4592 0.00753 0.00172 -0.1285 0.7755 0.4474
-0.500 0.4734 0.00670 0.00185 -0.1258 0.7728 0.7716
-0.250 0.4960 0.00662 0.00189 -0.1245 0.7705 0.8528
0.000 0.5181 0.00652 0.00190 -0.1230 0.7684 0.9086
0.250 0.5477 0.00644 0.00187 -0.1232 0.7663 0.9501
0.500 0.5893 0.00642 0.00185 -0.1265 0.7640 0.9727
0.750 0.6252 0.00643 0.00185 -0.1286 0.7614 0.9826
1.000 0.6602 0.00644 0.00186 -0.1305 0.7587 0.9925
1.250 0.6881 0.00649 0.00190 -0.1308 0.7561 1.0000
1.500 0.7140 0.00654 0.00194 -0.1306 0.7535 1.0000
1.750 0.7388 0.00658 0.00202 -0.1301 0.7497 1.0000
2.000 0.7644 0.00662 0.00209 -0.1299 0.7461 1.0000
2.250 0.7906 0.00667 0.00220 -0.1297 0.7429 1.0000
2.500 0.8166 0.00672 0.00230 -0.1295 0.7393 1.0000
2.750 0.8406 0.00670 0.00230 -0.1287 0.7290 1.0000
3.000 0.8618 0.00665 0.00224 -0.1272 0.7046 1.0000
3.250 0.8822 0.00671 0.00222 -0.1256 0.6703 1.0000
3.500 0.8967 0.00708 0.00231 -0.1227 0.6119 1.0000
3.750 0.8945 0.00827 0.00278 -0.1167 0.4689 1.0000
4.000 0.8755 0.01072 0.00391 -0.1082 0.2077 1.0000
4.250 0.8712 0.01257 0.00486 -0.1026 0.0225 1.0000
4.500 0.8905 0.01301 0.00531 -0.1011 0.0131 1.0000
4.750 0.9097 0.01344 0.00584 -0.0997 0.0066 1.0000
5.000 0.9271 0.01397 0.00643 -0.0978 0.0051 1.0000
5.250 0.9364 0.01492 0.00752 -0.0942 0.0038 1.0000
5.500 0.9490 0.01569 0.00838 -0.0915 0.0037 1.0000
5.750 0.9598 0.01663 0.00943 -0.0885 0.0035 1.0000
6.000 0.9702 0.01771 0.01061 -0.0855 0.0034 1.0000
6.250 0.9820 0.01895 0.01194 -0.0827 0.0034 1.0000
6.500 0.9980 0.02044 0.01354 -0.0808 0.0033 1.0000
6.750 1.0232 0.02222 0.01544 -0.0803 0.0034 1.0000
7.000 1.0628 0.02480 0.01822 -0.0825 0.0034 1.0000
7.250 1.0976 0.02778 0.02146 -0.0837 0.0035 1.0000
7.500 1.1241 0.03138 0.02547 -0.0833 0.0036 1.0000
7.750 1.1412 0.03535 0.02980 -0.0815 0.0038 1.0000
8.750 1.1746 0.04698 0.04253 -0.0699 0.0037 1.0000
9.000 1.1737 0.05031 0.04612 -0.0660 0.0037 1.0000
9.250 1.1944 0.05162 0.04759 -0.0644 0.0029 1.0000
9.500 1.1883 0.05472 0.05091 -0.0601 0.0030 1.0000
9.750 1.1789 0.05781 0.05421 -0.0554 0.0029 1.0000
10.000 1.1686 0.06079 0.05737 -0.0512 0.0028 1.0000
10.250 1.1553 0.06391 0.06067 -0.0473 0.0027 1.0000
10.500 1.1392 0.06734 0.06426 -0.0439 0.0027 1.0000
10.750 1.1219 0.07103 0.06812 -0.0412 0.0026 1.0000
11.000 1.1032 0.07481 0.07204 -0.0394 0.0028 1.0000
11.250 1.0855 0.07915 0.07653 -0.0381 0.0026 1.0000
11.500 1.0644 0.08388 0.08139 -0.0378 0.0027 1.0000
11.750 1.0450 0.08913 0.08677 -0.0384 0.0027 1.0000
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Polar data table (+)
Polar graphs
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