E10(08%) (e228-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E10(08%) (e228-il) Reynolds number: 500,000 Max Cl/Cd: 66.19 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e228-il-500000.txt Download as CSV file: xf-e228-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7261 0.10502 0.10288 0.0093 1.0000 0.0150
-12.000 -0.7234 0.10188 0.09975 0.0074 1.0000 0.0154
-11.750 -0.8068 0.07266 0.07034 -0.0105 1.0000 0.0117
-11.500 -0.7866 0.05199 0.04953 -0.0191 1.0000 0.0112
-11.250 -0.9290 0.04724 0.04402 -0.0262 1.0000 0.0102
-11.000 -0.9444 0.04414 0.04070 -0.0246 1.0000 0.0101
-10.750 -0.9601 0.04121 0.03755 -0.0215 1.0000 0.0101
-10.500 -0.9661 0.03863 0.03472 -0.0186 1.0000 0.0100
-10.250 -0.9708 0.03511 0.03089 -0.0161 1.0000 0.0101
-10.000 -0.9675 0.03215 0.02765 -0.0140 1.0000 0.0102
-9.750 -0.9583 0.02977 0.02506 -0.0123 1.0000 0.0105
-9.500 -0.9449 0.02794 0.02304 -0.0109 1.0000 0.0108
-9.250 -0.9284 0.02656 0.02152 -0.0098 1.0000 0.0113
-9.000 -0.9111 0.02503 0.01982 -0.0086 1.0000 0.0118
-8.750 -0.8928 0.02346 0.01806 -0.0074 1.0000 0.0121
-8.500 -0.8734 0.02202 0.01646 -0.0063 1.0000 0.0127
-8.250 -0.8520 0.02103 0.01533 -0.0054 1.0000 0.0134
-8.000 -0.8285 0.02055 0.01471 -0.0047 1.0000 0.0140
-7.750 -0.8142 0.01786 0.01184 -0.0029 1.0000 0.0154
-7.500 -0.7931 0.01692 0.01084 -0.0019 1.0000 0.0164
-7.250 -0.7712 0.01611 0.00997 -0.0010 1.0000 0.0176
-7.000 -0.7491 0.01535 0.00914 -0.0001 1.0000 0.0188
-6.750 -0.7261 0.01478 0.00850 0.0008 1.0000 0.0198
-6.500 -0.7080 0.01364 0.00726 0.0024 1.0000 0.0219
-6.250 -0.6873 0.01300 0.00660 0.0036 1.0000 0.0240
-6.000 -0.6670 0.01251 0.00605 0.0050 1.0000 0.0260
-5.750 -0.6478 0.01214 0.00561 0.0067 1.0000 0.0278
-5.500 -0.6327 0.01155 0.00500 0.0090 1.0000 0.0326
-5.250 -0.6035 0.01093 0.00444 0.0085 0.9968 0.0465
-5.000 -0.5693 0.01008 0.00391 0.0066 0.9915 0.1043
-4.750 -0.5336 0.00954 0.00358 0.0045 0.9865 0.1521
-4.500 -0.4964 0.00910 0.00330 0.0022 0.9824 0.1957
-4.250 -0.4632 0.00871 0.00307 0.0009 0.9746 0.2381
-4.000 -0.4302 0.00831 0.00286 -0.0004 0.9671 0.2876
-3.750 -0.4007 0.00798 0.00268 -0.0008 0.9572 0.3345
-3.500 -0.3757 0.00768 0.00254 -0.0002 0.9451 0.3827
-3.250 -0.3521 0.00742 0.00242 0.0008 0.9326 0.4260
-3.000 -0.3288 0.00721 0.00229 0.0019 0.9202 0.4631
-2.750 -0.3056 0.00700 0.00218 0.0031 0.9079 0.5035
-2.500 -0.2821 0.00681 0.00208 0.0042 0.8957 0.5428
-2.250 -0.2581 0.00663 0.00199 0.0052 0.8834 0.5798
-2.000 -0.2339 0.00647 0.00189 0.0062 0.8710 0.6157
-1.750 -0.2093 0.00632 0.00182 0.0071 0.8579 0.6514
-1.500 -0.1844 0.00618 0.00176 0.0079 0.8447 0.6861
-1.250 -0.1593 0.00606 0.00171 0.0088 0.8313 0.7198
-1.000 -0.1341 0.00596 0.00167 0.0096 0.8177 0.7525
-0.750 -0.1087 0.00588 0.00164 0.0104 0.8037 0.7839
-0.500 -0.0831 0.00581 0.00162 0.0112 0.7892 0.8136
-0.250 -0.0571 0.00577 0.00162 0.0120 0.7743 0.8418
0.000 -0.0306 0.00575 0.00162 0.0126 0.7589 0.8677
0.250 -0.0029 0.00576 0.00164 0.0130 0.7430 0.8907
0.500 0.0260 0.00581 0.00167 0.0131 0.7264 0.9113
0.750 0.0571 0.00589 0.00172 0.0127 0.7087 0.9278
1.000 0.0896 0.00600 0.00178 0.0120 0.6900 0.9412
1.250 0.1251 0.00614 0.00185 0.0106 0.6705 0.9502
1.500 0.1596 0.00628 0.00193 0.0094 0.6493 0.9589
2.000 0.2327 0.00659 0.00208 0.0059 0.6026 0.9715
2.250 0.2719 0.00674 0.00215 0.0035 0.5759 0.9760
2.500 0.3061 0.00692 0.00225 0.0022 0.5490 0.9826
2.750 0.3461 0.00707 0.00230 -0.0005 0.5186 0.9858
3.000 0.3845 0.00724 0.00238 -0.0028 0.4868 0.9900
3.250 0.4216 0.00744 0.00247 -0.0049 0.4542 0.9943
3.500 0.4608 0.00761 0.00253 -0.0075 0.4183 0.9979
3.750 0.4938 0.00782 0.00262 -0.0089 0.3828 1.0000
4.000 0.5168 0.00801 0.00272 -0.0081 0.3508 1.0000
4.250 0.5397 0.00825 0.00284 -0.0073 0.3173 1.0000
4.500 0.5624 0.00853 0.00300 -0.0065 0.2828 1.0000
4.750 0.5851 0.00884 0.00319 -0.0057 0.2475 1.0000
5.000 0.6075 0.00920 0.00341 -0.0049 0.2131 1.0000
5.250 0.6300 0.00956 0.00366 -0.0041 0.1813 1.0000
5.500 0.6522 0.00997 0.00394 -0.0032 0.1494 1.0000
5.750 0.6740 0.01043 0.00426 -0.0023 0.1192 1.0000
6.000 0.6956 0.01093 0.00463 -0.0013 0.0916 1.0000
6.250 0.7175 0.01137 0.00500 -0.0004 0.0717 1.0000
6.500 0.7391 0.01185 0.00541 0.0006 0.0558 1.0000
6.750 0.7605 0.01238 0.00588 0.0016 0.0425 1.0000
7.000 0.7812 0.01299 0.00646 0.0028 0.0313 1.0000
7.250 0.8013 0.01369 0.00714 0.0041 0.0223 1.0000
7.500 0.8222 0.01426 0.00776 0.0052 0.0180 1.0000
7.750 0.8401 0.01523 0.00881 0.0068 0.0153 1.0000
8.000 0.8601 0.01589 0.00955 0.0081 0.0138 1.0000
8.250 0.8792 0.01662 0.01034 0.0095 0.0126 1.0000
8.500 0.8950 0.01772 0.01151 0.0113 0.0117 1.0000
8.750 0.9050 0.01958 0.01352 0.0138 0.0111 1.0000
9.000 0.9226 0.02049 0.01454 0.0153 0.0108 1.0000
9.250 0.9400 0.02142 0.01561 0.0168 0.0104 1.0000
9.500 0.9565 0.02243 0.01673 0.0183 0.0100 1.0000
9.750 0.9722 0.02351 0.01792 0.0199 0.0095 1.0000
10.000 0.9870 0.02463 0.01916 0.0214 0.0091 1.0000
10.250 0.9989 0.02615 0.02084 0.0233 0.0089 1.0000
10.500 1.0104 0.02752 0.02235 0.0250 0.0087 1.0000
10.750 1.0195 0.02902 0.02399 0.0270 0.0085 1.0000
11.000 1.0230 0.03102 0.02619 0.0294 0.0085 1.0000
11.250 1.0231 0.03263 0.02794 0.0323 0.0084 1.0000
11.500 1.0202 0.03460 0.03006 0.0348 0.0082 1.0000
11.750 1.0164 0.03681 0.03242 0.0366 0.0081 1.0000
12.000 1.0068 0.03993 0.03580 0.0378 0.0083 1.0000
12.250 0.9992 0.04294 0.03895 0.0381 0.0081 1.0000
12.500 0.9859 0.04698 0.04316 0.0375 0.0080 1.0000
12.750 0.9714 0.05163 0.04800 0.0357 0.0079 1.0000
13.000 0.9538 0.05723 0.05378 0.0329 0.0078 1.0000
13.250 0.9438 0.06232 0.05907 0.0296 0.0080 1.0000
13.500 0.9259 0.06925 0.06619 0.0250 0.0081 1.0000
13.750 0.9036 0.07764 0.07477 0.0193 0.0082 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E10(08%) (e228-il)