EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 422 AIRFOIL (e422-il) Reynolds number: 200,000 Max Cl/Cd: 72.78 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e422-il-200000-n5.txt Download as CSV file: xf-e422-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 422 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 0.0099 0.10710 0.10228 -0.0829 0.7119 0.0297
-10.250 0.0128 0.10425 0.09938 -0.0844 0.6986 0.0300
-10.000 0.0171 0.10154 0.09661 -0.0855 0.6860 0.0301
-9.000 0.0379 0.08829 0.08315 -0.0885 0.6459 0.0188
-8.750 0.0453 0.08599 0.08080 -0.0890 0.6372 0.0184
-8.500 0.0514 0.08342 0.07822 -0.0897 0.6288 0.0180
-8.250 0.0545 0.08041 0.07518 -0.0905 0.6218 0.0175
-8.000 0.0443 0.07433 0.06912 -0.0928 0.6176 0.0159
-7.750 0.0472 0.07155 0.06634 -0.0936 0.6105 0.0158
-7.500 0.0497 0.06895 0.06372 -0.0943 0.6042 0.0157
-7.250 0.0474 0.06582 0.06061 -0.0950 0.5984 0.0156
-7.000 0.0425 0.06260 0.05742 -0.0961 0.5927 0.0155
-6.500 -0.0053 0.02850 0.02211 -0.1265 0.5914 0.0140
-6.250 0.0138 0.02602 0.01916 -0.1270 0.5852 0.0141
-6.000 0.0353 0.02425 0.01705 -0.1271 0.5787 0.0145
-5.750 0.0578 0.02277 0.01524 -0.1268 0.5721 0.0149
-5.250 0.1055 0.02059 0.01247 -0.1259 0.5604 0.0157
-5.000 0.1301 0.01979 0.01149 -0.1254 0.5547 0.0163
-4.750 0.1552 0.01925 0.01082 -0.1250 0.5497 0.0171
-4.500 0.1810 0.01873 0.01013 -0.1246 0.5446 0.0185
-4.250 0.2066 0.01817 0.00947 -0.1242 0.5391 0.0196
-4.000 0.2323 0.01772 0.00890 -0.1238 0.5341 0.0208
-3.750 0.2583 0.01730 0.00830 -0.1233 0.5297 0.0220
-3.500 0.2847 0.01686 0.00780 -0.1230 0.5249 0.0236
-3.250 0.3114 0.01650 0.00731 -0.1226 0.5204 0.0260
-3.000 0.3380 0.01617 0.00688 -0.1222 0.5164 0.0300
-2.750 0.3644 0.01583 0.00646 -0.1218 0.5128 0.0384
-2.500 0.3911 0.01542 0.00611 -0.1215 0.5087 0.0563
-2.250 0.4178 0.01514 0.00593 -0.1213 0.5044 0.0869
-2.000 0.4447 0.01505 0.00586 -0.1210 0.5004 0.1135
-1.750 0.4718 0.01507 0.00582 -0.1207 0.4969 0.1358
-1.500 0.4990 0.01513 0.00582 -0.1204 0.4938 0.1528
-1.250 0.5262 0.01514 0.00584 -0.1201 0.4903 0.1662
-1.000 0.5532 0.01515 0.00583 -0.1198 0.4867 0.1778
-0.750 0.5802 0.01517 0.00577 -0.1195 0.4832 0.1882
-0.500 0.6069 0.01518 0.00574 -0.1191 0.4800 0.1981
-0.250 0.6339 0.01524 0.00570 -0.1188 0.4772 0.2076
0.000 0.6607 0.01524 0.00573 -0.1185 0.4741 0.2178
0.250 0.6875 0.01526 0.00576 -0.1182 0.4710 0.2278
0.500 0.7141 0.01530 0.00579 -0.1179 0.4680 0.2391
0.750 0.7406 0.01534 0.00583 -0.1175 0.4651 0.2505
1.000 0.7672 0.01540 0.00585 -0.1172 0.4623 0.2637
1.250 0.7939 0.01549 0.00590 -0.1169 0.4598 0.2789
1.500 0.8200 0.01553 0.00603 -0.1165 0.4569 0.2962
1.750 0.8461 0.01559 0.00615 -0.1161 0.4541 0.3177
2.000 0.8721 0.01564 0.00628 -0.1158 0.4514 0.3437
2.250 0.8980 0.01568 0.00641 -0.1154 0.4487 0.3793
2.500 0.9235 0.01569 0.00652 -0.1150 0.4462 0.4318
2.750 0.9458 0.01517 0.00666 -0.1139 0.4439 0.7008
3.250 1.0208 0.01531 0.00704 -0.1178 0.4383 1.0000
3.500 1.0460 0.01552 0.00723 -0.1173 0.4358 1.0000
3.750 1.0711 0.01573 0.00741 -0.1168 0.4332 1.0000
4.000 1.0962 0.01594 0.00757 -0.1163 0.4307 1.0000
4.250 1.1215 0.01617 0.00773 -0.1158 0.4284 1.0000
4.500 1.1474 0.01643 0.00791 -0.1155 0.4262 1.0000
4.750 1.1714 0.01668 0.00819 -0.1148 0.4239 1.0000
5.000 1.1954 0.01693 0.00848 -0.1142 0.4213 1.0000
5.250 1.2194 0.01718 0.00875 -0.1136 0.4187 1.0000
5.500 1.2433 0.01743 0.00900 -0.1130 0.4161 1.0000
5.750 1.2674 0.01767 0.00923 -0.1124 0.4136 1.0000
6.000 1.2921 0.01793 0.00946 -0.1119 0.4115 1.0000
6.250 1.3176 0.01822 0.00972 -0.1116 0.4096 1.0000
6.500 1.3394 0.01853 0.01010 -0.1107 0.4070 1.0000
6.750 1.3613 0.01883 0.01047 -0.1098 0.4041 1.0000
7.000 1.3835 0.01912 0.01081 -0.1089 0.4013 1.0000
7.250 1.4060 0.01940 0.01114 -0.1082 0.3988 1.0000
7.500 1.4287 0.01968 0.01142 -0.1074 0.3964 1.0000
7.750 1.4526 0.01996 0.01167 -0.1069 0.3940 1.0000
8.000 1.4736 0.02030 0.01209 -0.1059 0.3914 1.0000
8.250 1.4920 0.02066 0.01256 -0.1046 0.3882 1.0000
8.500 1.5110 0.02099 0.01296 -0.1033 0.3849 1.0000
8.750 1.5304 0.02128 0.01330 -0.1021 0.3817 1.0000
9.000 1.5514 0.02155 0.01357 -0.1011 0.3788 1.0000
9.250 1.5705 0.02190 0.01395 -0.0999 0.3759 1.0000
9.500 1.5836 0.02233 0.01453 -0.0977 0.3722 1.0000
9.750 1.5968 0.02271 0.01501 -0.0955 0.3687 1.0000
10.000 1.6111 0.02307 0.01542 -0.0935 0.3654 1.0000
10.250 1.6285 0.02338 0.01573 -0.0921 0.3623 1.0000
10.500 1.6389 0.02392 0.01638 -0.0897 0.3588 1.0000
10.750 1.6473 0.02452 0.01711 -0.0872 0.3546 1.0000
11.000 1.6577 0.02507 0.01773 -0.0850 0.3506 1.0000
11.250 1.6715 0.02553 0.01821 -0.0833 0.3472 1.0000
11.500 1.6782 0.02635 0.01915 -0.0810 0.3430 1.0000
11.750 1.6832 0.02728 0.02021 -0.0786 0.3384 1.0000
12.000 1.6912 0.02811 0.02110 -0.0767 0.3341 1.0000
12.250 1.6993 0.02901 0.02205 -0.0749 0.3300 1.0000
12.500 1.6991 0.03051 0.02372 -0.0727 0.3247 1.0000
12.750 1.7028 0.03183 0.02511 -0.0710 0.3196 1.0000
13.000 1.7071 0.03321 0.02654 -0.0695 0.3149 1.0000
13.250 1.7030 0.03538 0.02886 -0.0679 0.3088 1.0000
13.500 1.7037 0.03721 0.03073 -0.0666 0.3032 1.0000
13.750 1.6981 0.03978 0.03343 -0.0653 0.2969 1.0000
14.000 1.6929 0.04242 0.03615 -0.0643 0.2904 1.0000
14.250 1.6863 0.04533 0.03913 -0.0635 0.2838 1.0000
14.500 1.6766 0.04870 0.04259 -0.0628 0.2765 1.0000
14.750 1.6679 0.05209 0.04605 -0.0623 0.2694 1.0000
15.000 1.6559 0.05598 0.05000 -0.0620 0.2614 1.0000
15.250 1.6445 0.05999 0.05409 -0.0619 0.2537 1.0000
15.500 1.6347 0.06383 0.05793 -0.0618 0.2453 1.0000
15.750 1.6206 0.06844 0.06263 -0.0621 0.2369 1.0000
16.000 1.6117 0.07239 0.06659 -0.0623 0.2286 1.0000
16.250 1.6000 0.07686 0.07112 -0.0627 0.2202 1.0000
16.500 1.5914 0.08097 0.07526 -0.0632 0.2123 1.0000
16.750 1.5836 0.08501 0.07930 -0.0637 0.2044 1.0000
17.000 1.5752 0.08926 0.08360 -0.0644 0.1967 1.0000
17.250 1.5695 0.09307 0.08740 -0.0650 0.1894 1.0000
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Polar data table (+)
Polar graphs
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