EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il) Reynolds number: 500,000 Max Cl/Cd: 46.48 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ea61009-il-500000.txt Download as CSV file: xf-ea61009-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EA 6(-1)-009 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.250 -1.0635 0.07234 0.06977 -0.0058 1.0000 0.0151
-14.000 -1.1036 0.06013 0.05731 -0.0152 1.0000 0.0148
-13.750 -1.1327 0.05221 0.04916 -0.0203 1.0000 0.0147
-13.500 -1.1550 0.04652 0.04323 -0.0227 1.0000 0.0148
-13.250 -1.1720 0.04222 0.03870 -0.0233 1.0000 0.0148
-13.000 -1.1831 0.03900 0.03526 -0.0227 1.0000 0.0151
-12.750 -1.1922 0.03629 0.03233 -0.0212 1.0000 0.0152
-12.500 -1.1965 0.03424 0.03006 -0.0188 1.0000 0.0154
-12.250 -1.2036 0.03127 0.02682 -0.0163 1.0000 0.0158
-12.000 -1.1951 0.02959 0.02501 -0.0149 1.0000 0.0164
-11.750 -1.1794 0.02865 0.02400 -0.0139 1.0000 0.0169
-11.500 -1.1610 0.02795 0.02324 -0.0132 1.0000 0.0176
-11.250 -1.1429 0.02702 0.02218 -0.0124 1.0000 0.0185
-11.000 -1.1247 0.02587 0.02082 -0.0116 1.0000 0.0194
-10.750 -1.1090 0.02422 0.01903 -0.0107 1.0000 0.0204
-10.500 -1.0857 0.02405 0.01885 -0.0103 1.0000 0.0214
-10.250 -1.0622 0.02381 0.01857 -0.0099 1.0000 0.0224
-10.000 -1.0400 0.02309 0.01770 -0.0094 1.0000 0.0239
-9.750 -1.0191 0.02196 0.01642 -0.0088 1.0000 0.0253
-9.500 -0.9936 0.02222 0.01673 -0.0086 1.0000 0.0264
-9.250 -0.9678 0.02256 0.01706 -0.0084 1.0000 0.0277
-9.000 -0.9432 0.02233 0.01672 -0.0081 1.0000 0.0296
-8.750 -0.9205 0.02135 0.01556 -0.0076 1.0000 0.0313
-8.500 -0.8957 0.02120 0.01545 -0.0074 1.0000 0.0326
-8.250 -0.8703 0.02123 0.01545 -0.0073 1.0000 0.0339
-8.000 -0.8448 0.02111 0.01527 -0.0071 1.0000 0.0358
-7.750 -0.8190 0.02107 0.01511 -0.0068 1.0000 0.0376
-7.500 -0.7956 0.01948 0.01338 -0.0065 1.0000 0.0394
-7.250 -0.7704 0.01896 0.01288 -0.0064 1.0000 0.0410
-7.000 -0.7445 0.01861 0.01252 -0.0063 1.0000 0.0427
-6.750 -0.7184 0.01817 0.01202 -0.0061 1.0000 0.0445
-6.500 -0.6919 0.01782 0.01159 -0.0060 1.0000 0.0463
-6.250 -0.6650 0.01776 0.01144 -0.0058 1.0000 0.0474
-6.000 -0.6403 0.01591 0.00953 -0.0056 1.0000 0.0494
-5.750 -0.6145 0.01497 0.00862 -0.0055 1.0000 0.0508
-5.500 -0.5884 0.01434 0.00800 -0.0054 1.0000 0.0522
-5.250 -0.5623 0.01382 0.00746 -0.0053 1.0000 0.0537
-5.000 -0.5338 0.01324 0.00688 -0.0057 0.9938 0.0549
-4.750 -0.4982 0.01266 0.00628 -0.0075 0.9785 0.0562
-4.500 -0.4634 0.01217 0.00576 -0.0092 0.9666 0.0574
-4.000 -0.4026 0.01160 0.00511 -0.0102 0.9424 0.0593
-3.750 -0.3787 0.01098 0.00443 -0.0094 0.9303 0.0605
-3.500 -0.3546 0.01052 0.00393 -0.0086 0.9198 0.0623
-3.250 -0.3300 0.01021 0.00358 -0.0078 0.9109 0.0640
-3.000 -0.3041 0.00994 0.00330 -0.0074 0.9022 0.0659
-2.750 -0.2785 0.00975 0.00306 -0.0068 0.8939 0.0680
-2.500 -0.2526 0.00957 0.00284 -0.0063 0.8843 0.0703
-2.250 -0.2268 0.00942 0.00265 -0.0056 0.8731 0.0719
-2.000 -0.2010 0.00926 0.00244 -0.0050 0.8616 0.0753
-1.750 -0.1751 0.00907 0.00224 -0.0043 0.8507 0.0822
-1.500 -0.1497 0.00847 0.00204 -0.0040 0.8411 0.1810
-1.250 -0.1262 0.00752 0.00180 -0.0037 0.8316 0.3695
-1.000 -0.1039 0.00663 0.00162 -0.0028 0.8182 0.5625
-0.750 -0.0794 0.00629 0.00160 -0.0019 0.8037 0.6579
-0.500 -0.0537 0.00617 0.00162 -0.0011 0.7892 0.7095
-0.250 -0.0270 0.00613 0.00164 -0.0005 0.7758 0.7385
0.000 0.0000 0.00613 0.00164 0.0000 0.7600 0.7600
0.250 0.0270 0.00613 0.00164 0.0005 0.7386 0.7759
0.500 0.0537 0.00617 0.00162 0.0011 0.7094 0.7892
0.750 0.0794 0.00629 0.00160 0.0019 0.6576 0.8035
1.000 0.1038 0.00663 0.00162 0.0028 0.5620 0.8182
1.250 0.1262 0.00753 0.00180 0.0037 0.3690 0.8317
1.500 0.1497 0.00847 0.00204 0.0040 0.1808 0.8411
1.750 0.1751 0.00907 0.00224 0.0043 0.0821 0.8507
2.000 0.2011 0.00926 0.00243 0.0050 0.0752 0.8613
2.250 0.2268 0.00942 0.00265 0.0056 0.0719 0.8729
2.500 0.2525 0.00957 0.00284 0.0063 0.0703 0.8843
2.750 0.2785 0.00975 0.00306 0.0068 0.0680 0.8940
3.000 0.3041 0.00994 0.00330 0.0074 0.0658 0.9023
3.250 0.3300 0.01021 0.00358 0.0079 0.0640 0.9109
3.500 0.3546 0.01052 0.00393 0.0086 0.0622 0.9198
3.750 0.3787 0.01099 0.00445 0.0094 0.0605 0.9303
4.000 0.4026 0.01160 0.00511 0.0102 0.0593 0.9425
4.500 0.4635 0.01217 0.00576 0.0091 0.0574 0.9667
4.750 0.4984 0.01266 0.00628 0.0075 0.0562 0.9786
5.250 0.5624 0.01382 0.00747 0.0053 0.0537 1.0000
5.500 0.5884 0.01434 0.00799 0.0054 0.0522 1.0000
5.750 0.6146 0.01497 0.00862 0.0055 0.0508 1.0000
6.000 0.6404 0.01589 0.00952 0.0056 0.0494 1.0000
6.250 0.6650 0.01777 0.01145 0.0058 0.0474 1.0000
6.500 0.6920 0.01782 0.01159 0.0059 0.0463 1.0000
6.750 0.7185 0.01818 0.01203 0.0061 0.0446 1.0000
7.000 0.7447 0.01862 0.01252 0.0062 0.0427 1.0000
7.250 0.7706 0.01894 0.01285 0.0063 0.0410 1.0000
7.500 0.7958 0.01948 0.01338 0.0064 0.0394 1.0000
7.750 0.8193 0.02104 0.01507 0.0067 0.0376 1.0000
8.000 0.8451 0.02110 0.01527 0.0070 0.0358 1.0000
8.250 0.8706 0.02122 0.01544 0.0072 0.0339 1.0000
8.500 0.8960 0.02116 0.01541 0.0074 0.0325 1.0000
8.750 0.9207 0.02135 0.01556 0.0076 0.0313 1.0000
9.000 0.9435 0.02235 0.01674 0.0080 0.0296 1.0000
9.250 0.9682 0.02255 0.01705 0.0083 0.0277 1.0000
9.500 0.9941 0.02220 0.01671 0.0085 0.0264 1.0000
9.750 1.0197 0.02194 0.01639 0.0086 0.0253 1.0000
10.000 1.0405 0.02309 0.01770 0.0093 0.0238 1.0000
10.250 1.0626 0.02384 0.01861 0.0098 0.0225 1.0000
10.500 1.0860 0.02407 0.01888 0.0102 0.0214 1.0000
10.750 1.1093 0.02422 0.01902 0.0106 0.0204 1.0000
11.000 1.1252 0.02581 0.02075 0.0115 0.0194 1.0000
11.250 1.1433 0.02699 0.02215 0.0124 0.0185 1.0000
11.500 1.1612 0.02797 0.02327 0.0131 0.0176 1.0000
11.750 1.1795 0.02869 0.02404 0.0139 0.0169 1.0000
12.000 1.1955 0.02958 0.02500 0.0148 0.0164 1.0000
12.250 1.2041 0.03126 0.02681 0.0162 0.0159 1.0000
12.500 1.1975 0.03420 0.03002 0.0187 0.0154 1.0000
12.750 1.1927 0.03630 0.03235 0.0211 0.0152 1.0000
13.000 1.1835 0.03902 0.03529 0.0226 0.0150 1.0000
13.250 1.1710 0.04239 0.03889 0.0232 0.0149 1.0000
13.500 1.1541 0.04672 0.04344 0.0226 0.0148 1.0000
13.750 1.1331 0.05224 0.04919 0.0202 0.0148 1.0000
14.000 1.1040 0.06017 0.05736 0.0151 0.0148 1.0000
14.250 1.0590 0.07346 0.07090 0.0048 0.0151 1.0000
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Polar data table (+)
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