E10(08%) (e228-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E10(08%) (e228-il) Reynolds number: 50,000 Max Cl/Cd: 27.01 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e228-il-50000.txt Download as CSV file: xf-e228-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E10(08%)
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6618 0.09176 0.08524 -0.0040 1.0000 0.1379
-9.250 -0.7056 0.08120 0.07477 -0.0141 1.0000 0.1257
-9.000 -0.7125 0.07584 0.06941 -0.0151 1.0000 0.1217
-8.750 -0.7707 0.06812 0.06122 -0.0184 1.0000 0.1136
-8.500 -0.7640 0.06304 0.05607 -0.0181 1.0000 0.1118
-8.250 -0.7645 0.05809 0.05088 -0.0176 1.0000 0.1099
-8.000 -0.7652 0.05316 0.04555 -0.0167 1.0000 0.1084
-7.750 -0.7613 0.04867 0.04059 -0.0154 1.0000 0.1081
-7.500 -0.7537 0.04483 0.03619 -0.0138 1.0000 0.1108
-7.250 -0.7441 0.04132 0.03194 -0.0119 1.0000 0.1139
-7.000 -0.7234 0.03810 0.02871 -0.0110 1.0000 0.1193
-6.750 -0.7042 0.03500 0.02509 -0.0095 1.0000 0.1252
-6.500 -0.6828 0.03249 0.02239 -0.0083 1.0000 0.1371
-6.250 -0.6617 0.03017 0.01978 -0.0068 1.0000 0.1549
-6.000 -0.6396 0.02781 0.01763 -0.0054 1.0000 0.1843
-5.750 -0.6230 0.02601 0.01621 -0.0033 1.0000 0.2345
-5.500 -0.6096 0.02460 0.01520 -0.0005 1.0000 0.2996
-5.250 -0.5957 0.02344 0.01435 0.0025 1.0000 0.3668
-5.000 -0.5801 0.02251 0.01377 0.0056 1.0000 0.4297
-4.750 -0.5641 0.02177 0.01329 0.0088 1.0000 0.4906
-4.500 -0.5476 0.02118 0.01291 0.0122 1.0000 0.5494
-4.250 -0.5304 0.02074 0.01266 0.0158 1.0000 0.6061
-4.000 -0.5120 0.02046 0.01250 0.0194 1.0000 0.6606
-3.750 -0.4926 0.02032 0.01242 0.0231 1.0000 0.7139
-3.500 -0.4677 0.02044 0.01249 0.0263 1.0000 0.7651
-3.250 -0.4303 0.02084 0.01276 0.0276 1.0000 0.8158
-3.000 -0.3595 0.02163 0.01314 0.0231 1.0000 0.8655
-2.750 -0.2553 0.02213 0.01307 0.0112 1.0000 0.9104
-2.500 -0.1592 0.02169 0.01217 -0.0014 1.0000 0.9498
-2.250 -0.0707 0.02055 0.01069 -0.0142 1.0000 0.9858
-2.000 -0.0259 0.01949 0.00950 -0.0200 1.0000 1.0000
-1.750 -0.0161 0.01894 0.00893 -0.0192 1.0000 1.0000
-1.500 -0.0080 0.01851 0.00850 -0.0179 1.0000 1.0000
-1.250 -0.0033 0.01821 0.00821 -0.0159 1.0000 1.0000
-1.000 -0.0045 0.01804 0.00806 -0.0128 1.0000 1.0000
-0.750 -0.0112 0.01799 0.00802 -0.0087 1.0000 1.0000
-0.500 -0.0205 0.01804 0.00803 -0.0040 1.0000 1.0000
-0.250 -0.0283 0.01816 0.00810 0.0004 1.0000 1.0000
0.000 -0.0322 0.01834 0.00822 0.0042 1.0000 1.0000
0.250 -0.0323 0.01859 0.00840 0.0073 1.0000 1.0000
0.500 -0.0293 0.01890 0.00865 0.0099 1.0000 1.0000
0.750 -0.0244 0.01928 0.00897 0.0122 1.0000 1.0000
1.000 -0.0177 0.01973 0.00937 0.0140 1.0000 1.0000
1.250 -0.0095 0.02024 0.00984 0.0155 1.0000 1.0000
1.500 0.0647 0.02142 0.01113 0.0047 0.9762 1.0000
1.750 0.1366 0.02240 0.01227 -0.0051 0.9515 1.0000
2.000 0.2107 0.02314 0.01320 -0.0146 0.9256 1.0000
2.250 0.2935 0.02351 0.01388 -0.0248 0.8987 1.0000
2.500 0.3589 0.02357 0.01420 -0.0310 0.8698 1.0000
2.750 0.4067 0.02356 0.01441 -0.0334 0.8398 1.0000
3.000 0.4423 0.02355 0.01459 -0.0333 0.8097 1.0000
3.250 0.4701 0.02354 0.01470 -0.0315 0.7796 1.0000
3.500 0.4935 0.02351 0.01478 -0.0288 0.7493 1.0000
3.750 0.5147 0.02346 0.01484 -0.0255 0.7186 1.0000
4.000 0.5349 0.02335 0.01479 -0.0219 0.6872 1.0000
4.250 0.5545 0.02324 0.01470 -0.0181 0.6548 1.0000
4.500 0.5726 0.02331 0.01480 -0.0146 0.6180 1.0000
4.750 0.5916 0.02330 0.01476 -0.0110 0.5803 1.0000
5.000 0.6108 0.02336 0.01477 -0.0075 0.5398 1.0000
5.250 0.6292 0.02363 0.01496 -0.0043 0.4945 1.0000
5.500 0.6473 0.02403 0.01521 -0.0012 0.4461 1.0000
5.750 0.6653 0.02463 0.01558 0.0017 0.3957 1.0000
6.000 0.6826 0.02552 0.01623 0.0043 0.3442 1.0000
6.250 0.7000 0.02671 0.01718 0.0067 0.2959 1.0000
6.500 0.7173 0.02813 0.01845 0.0088 0.2528 1.0000
6.750 0.7354 0.02975 0.01990 0.0107 0.2161 1.0000
7.000 0.7545 0.03176 0.02183 0.0123 0.1874 1.0000
7.250 0.7719 0.03397 0.02421 0.0141 0.1635 1.0000
7.500 0.7915 0.03641 0.02654 0.0154 0.1451 1.0000
7.750 0.8086 0.03921 0.02956 0.0169 0.1315 1.0000
8.000 0.8193 0.04251 0.03348 0.0189 0.1223 1.0000
8.250 0.8304 0.04584 0.03713 0.0204 0.1140 1.0000
8.500 0.8344 0.05008 0.04192 0.0222 0.1112 1.0000
8.750 0.8375 0.05402 0.04621 0.0236 0.1079 1.0000
9.000 0.8472 0.05769 0.04989 0.0246 0.1029 1.0000
9.250 0.8377 0.06231 0.05492 0.0258 0.1025 1.0000
9.500 0.8271 0.06703 0.05990 0.0265 0.1028 1.0000
9.750 0.8154 0.07192 0.06495 0.0268 0.1033 1.0000
10.000 0.7173 0.08439 0.07761 0.0175 0.1244 1.0000
10.250 0.7021 0.09237 0.08551 0.0128 0.1286 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E10(08%) (e228-il)