lrn1007 (lrn1007-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: lrn1007 (lrn1007-il) Reynolds number: 200,000 Max Cl/Cd: 98.72 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lrn1007-il-200000-n5.txt Download as CSV file: xf-lrn1007-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: lrn1007
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1044 0.09039 0.08623 -0.0788 0.8373 0.0048
-8.250 -0.0971 0.08786 0.08373 -0.0799 0.8361 0.0056
-8.000 -0.0919 0.08819 0.08413 -0.0828 0.8340 0.0072
-7.750 -0.0858 0.08611 0.08208 -0.0839 0.8329 0.0072
-7.500 -0.0783 0.08460 0.08061 -0.0871 0.8316 0.0073
-7.250 -0.0663 0.08226 0.07827 -0.0901 0.8305 0.0073
-7.000 -0.0592 0.07696 0.07300 -0.0872 0.8301 0.0076
-6.750 -0.0484 0.07431 0.07035 -0.0891 0.8288 0.0077
-6.500 -0.0365 0.07167 0.06771 -0.0913 0.8276 0.0079
-6.250 -0.0223 0.06911 0.06512 -0.0940 0.8264 0.0079
-6.000 -0.0066 0.06649 0.06250 -0.0969 0.8247 0.0079
-5.750 0.0107 0.06381 0.05983 -0.1001 0.8228 0.0079
-5.500 0.0504 0.06266 0.05853 -0.1094 0.8208 0.0073
-5.250 0.0705 0.05981 0.05563 -0.1119 0.8195 0.0073
-5.000 0.0923 0.05700 0.05276 -0.1144 0.8183 0.0073
-4.750 0.1154 0.05427 0.04992 -0.1170 0.8171 0.0073
-4.500 0.1375 0.05147 0.04704 -0.1191 0.8158 0.0072
-4.250 0.1618 0.04882 0.04428 -0.1213 0.8146 0.0072
-4.000 0.1866 0.04622 0.04158 -0.1233 0.8136 0.0072
-3.750 0.2120 0.04369 0.03894 -0.1253 0.8127 0.0072
-3.500 0.2386 0.04141 0.03655 -0.1272 0.8112 0.0072
-3.250 0.2661 0.03930 0.03431 -0.1289 0.8095 0.0072
-3.000 0.2934 0.03725 0.03212 -0.1303 0.8077 0.0072
-2.750 0.3214 0.03537 0.03007 -0.1315 0.8059 0.0072
-2.500 0.3493 0.03356 0.02810 -0.1324 0.8045 0.0072
-2.250 0.3783 0.03203 0.02637 -0.1331 0.8032 0.0072
-2.000 0.4023 0.02942 0.02363 -0.1345 0.8019 0.0081
-1.750 0.4315 0.02834 0.02236 -0.1348 0.8008 0.0103
-1.500 0.4630 0.02831 0.02205 -0.1343 0.7996 0.0113
-1.250 0.4899 0.02755 0.02111 -0.1343 0.7965 0.0114
-1.000 0.5169 0.02585 0.01921 -0.1344 0.7933 0.0118
-0.750 0.5419 0.02330 0.01655 -0.1354 0.7908 0.0146
-0.500 0.5703 0.02252 0.01556 -0.1352 0.7890 0.0183
-0.250 0.6002 0.02237 0.01510 -0.1347 0.7875 0.0213
1.000 0.7346 0.01780 0.00998 -0.1340 0.7741 0.0493
1.250 0.7607 0.01751 0.00972 -0.1330 0.7699 0.0314
1.500 0.7864 0.01712 0.00930 -0.1323 0.7657 0.0214
1.750 0.8134 0.01634 0.00856 -0.1320 0.7628 0.0171
2.000 0.8419 0.01577 0.00790 -0.1318 0.7605 0.0143
2.250 0.8655 0.01570 0.00775 -0.1312 0.7544 0.0128
2.500 0.8927 0.01546 0.00736 -0.1309 0.7503 0.0125
2.750 0.9246 0.01362 0.00711 -0.1318 0.7478 1.0000
3.000 0.9484 0.01374 0.00715 -0.1312 0.7413 1.0000
3.250 0.9753 0.01360 0.00696 -0.1309 0.7363 1.0000
3.500 1.0009 0.01354 0.00692 -0.1305 0.7305 1.0000
3.750 1.0256 0.01351 0.00696 -0.1301 0.7236 1.0000
4.000 1.0496 0.01351 0.00705 -0.1295 0.7159 1.0000
4.250 1.0748 0.01338 0.00700 -0.1291 0.7081 1.0000
4.750 1.1184 0.01353 0.00731 -0.1275 0.6805 1.0000
5.000 1.1437 0.01328 0.00711 -0.1269 0.6646 1.0000
5.250 1.1729 0.01275 0.00655 -0.1268 0.6464 1.0000
5.500 1.2006 0.01239 0.00612 -0.1264 0.6197 1.0000
5.750 1.2241 0.01240 0.00594 -0.1253 0.5751 1.0000
6.000 1.2408 0.01293 0.00617 -0.1233 0.5211 1.0000
6.250 1.2367 0.01456 0.00703 -0.1181 0.4087 1.0000
6.500 1.2302 0.01625 0.00811 -0.1129 0.3164 1.0000
6.750 1.2170 0.01816 0.00933 -0.1068 0.2178 1.0000
7.000 1.2075 0.02031 0.01076 -0.1020 0.1179 1.0000
7.250 1.1954 0.02310 0.01273 -0.0972 0.0103 1.0000
7.500 1.2063 0.02431 0.01406 -0.0950 0.0061 1.0000
7.750 1.2170 0.02561 0.01564 -0.0927 0.0049 1.0000
8.000 1.2210 0.02753 0.01780 -0.0899 0.0023 1.0000
8.250 1.2266 0.02938 0.01990 -0.0873 0.0020 1.0000
8.500 1.2290 0.03153 0.02225 -0.0844 0.0019 1.0000
8.750 1.2318 0.03381 0.02468 -0.0817 0.0018 1.0000
|
Polar data table (+)
Polar graphs
<< Back to lrn1007 (lrn1007-il)