EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 908 AIRFOIL (e908-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.03 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e908-il-1000000.txt Download as CSV file: xf-e908-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 908 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2238 0.08109 0.07946 -0.0816 0.9831 0.0057
-9.500 -0.2197 0.07654 0.07491 -0.0838 0.9826 0.0057
-7.250 -0.2669 0.04605 0.04414 -0.1173 0.9617 0.0056
-7.000 -0.2496 0.04077 0.03865 -0.1210 0.9603 0.0057
-6.750 -0.2303 0.03600 0.03362 -0.1240 0.9593 0.0058
-6.500 -0.2090 0.03150 0.02880 -0.1264 0.9585 0.0058
-6.250 -0.2148 0.02969 0.02682 -0.1209 0.9515 0.0058
-6.000 -0.1944 0.02612 0.02288 -0.1213 0.9499 0.0058
-5.750 -0.1773 0.01917 0.01524 -0.1214 0.9484 0.0051
-4.250 -0.0256 0.01086 0.00590 -0.1200 0.9396 0.0096
-4.000 0.0024 0.00979 0.00467 -0.1199 0.9380 0.0077
-3.750 0.0330 0.00919 0.00396 -0.1206 0.9369 0.0072
-3.500 0.0647 0.00859 0.00319 -0.1215 0.9358 0.0076
-3.250 0.0958 0.00785 0.00252 -0.1223 0.9348 0.0669
-3.000 0.1262 0.00719 0.00230 -0.1235 0.9338 0.1939
-2.750 0.1564 0.00671 0.00215 -0.1247 0.9327 0.3016
-2.500 0.1726 0.00631 0.00214 -0.1226 0.9291 0.4241
-2.250 0.1954 0.00574 0.00215 -0.1220 0.9267 0.6231
-2.000 0.2247 0.00567 0.00207 -0.1225 0.9251 0.6491
-1.750 0.2554 0.00560 0.00201 -0.1232 0.9238 0.6647
-1.500 0.2867 0.00555 0.00195 -0.1242 0.9225 0.6772
-1.000 0.3499 0.00547 0.00188 -0.1262 0.9201 0.6988
-0.750 0.3726 0.00549 0.00193 -0.1251 0.9170 0.7062
-0.500 0.3987 0.00548 0.00193 -0.1249 0.9143 0.7136
-0.250 0.4277 0.00544 0.00191 -0.1252 0.9122 0.7212
0.000 0.4582 0.00539 0.00189 -0.1260 0.9103 0.7308
0.250 0.4895 0.00534 0.00188 -0.1269 0.9085 0.7420
0.500 0.5187 0.00532 0.00192 -0.1273 0.9063 0.7545
0.750 0.5416 0.00531 0.00201 -0.1263 0.9024 0.7655
1.000 0.5697 0.00527 0.00203 -0.1264 0.8992 0.7756
1.250 0.6006 0.00521 0.00201 -0.1272 0.8962 0.7847
1.500 0.6263 0.00506 0.00190 -0.1265 0.8866 0.7933
1.750 0.6454 0.00471 0.00146 -0.1239 0.8431 0.8014
2.000 0.6499 0.00518 0.00139 -0.1182 0.7175 0.8110
2.250 0.6323 0.00667 0.00186 -0.1085 0.4874 0.8240
2.500 0.6204 0.00910 0.00271 -0.1011 0.1016 0.8392
2.750 0.6375 0.00981 0.00319 -0.0989 0.0083 0.8549
3.000 0.6594 0.01006 0.00362 -0.0976 0.0074 0.8751
3.250 0.6786 0.01024 0.00394 -0.0957 0.0062 0.9082
3.500 0.7042 0.01050 0.00438 -0.0952 0.0055 1.0000
3.750 0.7266 0.01096 0.00485 -0.0942 0.0041 1.0000
4.000 0.7460 0.01170 0.00569 -0.0924 0.0036 1.0000
4.250 0.7633 0.01276 0.00686 -0.0900 0.0037 1.0000
5.250 0.8659 0.01205 0.00723 -0.0855 0.0058 1.0000
5.500 0.8892 0.01328 0.00862 -0.0843 0.0050 1.0000
5.750 0.9101 0.01523 0.01079 -0.0826 0.0046 1.0000
6.000 0.9280 0.01750 0.01329 -0.0805 0.0042 1.0000
6.250 0.9437 0.01999 0.01601 -0.0781 0.0039 1.0000
6.500 0.9566 0.02278 0.01904 -0.0753 0.0037 1.0000
6.750 0.9675 0.02570 0.02217 -0.0725 0.0035 1.0000
7.000 0.9758 0.02885 0.02553 -0.0694 0.0034 1.0000
7.250 0.9819 0.03217 0.02906 -0.0662 0.0032 1.0000
7.500 0.9856 0.03564 0.03271 -0.0629 0.0032 1.0000
7.750 0.9860 0.03936 0.03662 -0.0593 0.0031 1.0000
8.000 0.9831 0.04325 0.04069 -0.0554 0.0030 1.0000
8.250 0.9768 0.04723 0.04485 -0.0513 0.0030 1.0000
8.500 0.9653 0.05090 0.04867 -0.0467 0.0029 1.0000
8.750 0.9487 0.05411 0.05201 -0.0416 0.0029 1.0000
9.000 0.9303 0.05755 0.05558 -0.0372 0.0029 1.0000
9.250 0.9103 0.06141 0.05956 -0.0336 0.0029 1.0000
9.500 0.8889 0.06576 0.06403 -0.0310 0.0029 1.0000
9.750 0.8664 0.07074 0.06913 -0.0295 0.0029 1.0000
10.000 0.8428 0.07646 0.07496 -0.0295 0.0030 1.0000
10.250 0.8181 0.08320 0.08180 -0.0312 0.0030 1.0000
10.500 0.7910 0.09218 0.09089 -0.0357 0.0031 1.0000
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Polar data table (+)
Polar graphs
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