EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 584 AIRFOIL (e584-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.98 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e584-il-1000000.txt Download as CSV file: xf-e584-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 584 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.0588 0.08964 0.08643 -0.1217 0.6949 0.0110
-11.250 -0.0533 0.08716 0.08395 -0.1228 0.6926 0.0112
-11.000 -0.0536 0.08338 0.08017 -0.1243 0.6905 0.0113
-10.750 -0.0503 0.08048 0.07727 -0.1255 0.6883 0.0116
-10.500 -0.0538 0.07621 0.07301 -0.1273 0.6864 0.0116
-10.250 -0.0543 0.07271 0.06951 -0.1289 0.6844 0.0119
-10.000 -0.0665 0.06684 0.06366 -0.1319 0.6828 0.0118
-9.750 -0.0834 0.05968 0.05653 -0.1377 0.6812 0.0119
-9.500 -0.0783 0.04095 0.03791 -0.1331 0.6776 0.0128
-9.250 -0.0998 0.03710 0.03400 -0.1336 0.6763 0.0126
-9.000 -0.1279 0.03288 0.02968 -0.1319 0.6750 0.0126
-8.750 -0.1509 0.02988 0.02656 -0.1285 0.6735 0.0126
-8.500 -0.2035 0.02463 0.02077 -0.1197 0.6721 0.0133
-8.250 -0.2251 0.02004 0.01594 -0.1152 0.6705 0.0136
-8.000 -0.2153 0.01854 0.01438 -0.1136 0.6687 0.0138
-7.750 -0.2053 0.01718 0.01292 -0.1120 0.6670 0.0139
-7.500 -0.1941 0.01583 0.01148 -0.1103 0.6660 0.0141
-7.250 -0.1821 0.01444 0.00996 -0.1086 0.6648 0.0144
-7.000 -0.1953 0.01811 0.01211 -0.1053 0.6653 0.0083
-6.750 -0.1729 0.01674 0.01066 -0.1046 0.6641 0.0080
-6.500 -0.1504 0.01556 0.00935 -0.1039 0.6628 0.0078
-6.250 -0.1274 0.01458 0.00825 -0.1031 0.6613 0.0076
-6.000 -0.1041 0.01387 0.00746 -0.1024 0.6597 0.0075
-5.750 -0.0809 0.01325 0.00675 -0.1017 0.6580 0.0074
-5.500 -0.0575 0.01274 0.00618 -0.1010 0.6564 0.0074
-5.250 -0.0338 0.01231 0.00568 -0.1004 0.6546 0.0075
-5.000 -0.0092 0.01198 0.00528 -0.1000 0.6526 0.0075
-4.750 0.0146 0.01159 0.00487 -0.0994 0.6514 0.0077
-4.500 0.0390 0.01127 0.00453 -0.0988 0.6499 0.0079
-4.250 0.0641 0.01101 0.00424 -0.0984 0.6482 0.0081
-4.000 0.0885 0.01067 0.00387 -0.0979 0.6464 0.0088
-3.750 0.1143 0.01048 0.00365 -0.0977 0.6447 0.0099
-3.500 0.1400 0.01025 0.00341 -0.0974 0.6429 0.0136
-3.250 0.1645 0.00995 0.00321 -0.0970 0.6411 0.0377
-3.000 0.1909 0.00980 0.00315 -0.0970 0.6389 0.0638
-2.750 0.2163 0.00958 0.00306 -0.0968 0.6374 0.0964
-2.500 0.2410 0.00929 0.00295 -0.0964 0.6359 0.1443
-2.250 0.2635 0.00878 0.00284 -0.0959 0.6341 0.2549
-2.000 0.2822 0.00781 0.00266 -0.0951 0.6322 0.4882
-1.750 0.3014 0.00692 0.00273 -0.0938 0.6303 0.7696
-1.500 0.3301 0.00705 0.00284 -0.0939 0.6285 0.7944
-1.250 0.3594 0.00719 0.00290 -0.0943 0.6267 0.8067
-1.000 0.3874 0.00744 0.00313 -0.0942 0.6246 0.8159
-0.750 0.4160 0.00756 0.00321 -0.0944 0.6230 0.8230
-0.500 0.4425 0.00763 0.00331 -0.0941 0.6212 0.8277
-0.250 0.4697 0.00773 0.00341 -0.0939 0.6190 0.8322
0.000 0.4978 0.00785 0.00350 -0.0940 0.6169 0.8376
0.250 0.5226 0.00802 0.00369 -0.0931 0.6149 0.8443
0.500 0.5468 0.00835 0.00403 -0.0919 0.6129 0.8537
0.750 0.5706 0.00852 0.00419 -0.0908 0.6108 0.8595
1.000 0.5969 0.00855 0.00422 -0.0905 0.6087 0.8614
1.250 0.6242 0.00852 0.00420 -0.0906 0.6063 0.8627
1.500 0.6518 0.00849 0.00416 -0.0908 0.6036 0.8639
1.750 0.6797 0.00845 0.00411 -0.0910 0.6010 0.8649
2.000 0.7076 0.00841 0.00406 -0.0913 0.5984 0.8660
2.250 0.7359 0.00841 0.00402 -0.0917 0.5957 0.8668
2.500 0.7639 0.00837 0.00401 -0.0920 0.5927 0.8677
2.750 0.7919 0.00834 0.00398 -0.0923 0.5891 0.8686
3.000 0.8196 0.00830 0.00393 -0.0926 0.5854 0.8693
3.250 0.8470 0.00831 0.00390 -0.0928 0.5815 0.8699
3.500 0.8749 0.00831 0.00392 -0.0932 0.5775 0.8707
3.750 0.9024 0.00831 0.00393 -0.0935 0.5731 0.8711
4.000 0.9291 0.00835 0.00393 -0.0936 0.5686 0.8715
4.250 0.9562 0.00837 0.00395 -0.0938 0.5641 0.8719
4.500 0.9828 0.00835 0.00395 -0.0939 0.5593 0.8725
4.750 1.0081 0.00839 0.00397 -0.0937 0.5541 0.8731
5.000 1.0335 0.00843 0.00402 -0.0935 0.5491 0.8738
5.250 1.0592 0.00846 0.00408 -0.0934 0.5436 0.8744
5.500 1.0833 0.00854 0.00414 -0.0930 0.5375 0.8750
5.750 1.1085 0.00860 0.00422 -0.0928 0.5315 0.8755
6.000 1.1326 0.00867 0.00430 -0.0924 0.5241 0.8760
6.250 1.1559 0.00876 0.00439 -0.0919 0.5172 0.8766
6.500 1.1787 0.00884 0.00448 -0.0912 0.5087 0.8772
6.750 1.1991 0.00895 0.00458 -0.0901 0.5003 0.8779
7.000 1.2175 0.00909 0.00470 -0.0886 0.4900 0.8787
7.250 1.2371 0.00924 0.00485 -0.0873 0.4796 0.8794
7.500 1.2547 0.00946 0.00505 -0.0857 0.4682 0.8802
7.750 1.2705 0.00973 0.00529 -0.0838 0.4554 0.8812
8.000 1.2871 0.01001 0.00555 -0.0821 0.4438 0.8823
8.250 1.3037 0.01030 0.00582 -0.0804 0.4310 0.8831
8.500 1.3184 0.01063 0.00613 -0.0784 0.4182 0.8839
8.750 1.3316 0.01103 0.00649 -0.0762 0.4040 0.8848
9.000 1.3430 0.01148 0.00691 -0.0738 0.3893 0.8856
9.250 1.3528 0.01201 0.00739 -0.0711 0.3735 0.8864
9.500 1.3606 0.01263 0.00796 -0.0683 0.3566 0.8872
9.750 1.3676 0.01328 0.00857 -0.0654 0.3409 0.8884
10.000 1.3738 0.01401 0.00926 -0.0626 0.3262 0.8896
10.250 1.3781 0.01487 0.01009 -0.0595 0.3105 0.8909
10.500 1.3803 0.01590 0.01107 -0.0564 0.2932 0.8922
10.750 1.3818 0.01705 0.01217 -0.0534 0.2765 0.8935
11.000 1.3819 0.01836 0.01343 -0.0505 0.2593 0.8950
11.250 1.3831 0.01971 0.01474 -0.0478 0.2438 0.8966
11.500 1.3845 0.02114 0.01612 -0.0454 0.2288 0.8980
11.750 1.3870 0.02258 0.01754 -0.0432 0.2154 0.8993
12.000 1.3889 0.02412 0.01904 -0.0412 0.2021 0.9005
12.250 1.3908 0.02574 0.02062 -0.0393 0.1892 0.9016
12.500 1.3922 0.02745 0.02229 -0.0374 0.1764 0.9026
12.750 1.3928 0.02925 0.02405 -0.0357 0.1628 0.9042
13.000 1.3941 0.03106 0.02584 -0.0341 0.1502 0.9058
13.250 1.3935 0.03310 0.02783 -0.0325 0.1360 0.9073
13.500 1.3929 0.03520 0.02988 -0.0310 0.1221 0.9089
13.750 1.3950 0.03713 0.03178 -0.0298 0.1112 0.9104
14.000 1.3980 0.03904 0.03369 -0.0288 0.1017 0.9120
14.250 1.3929 0.04167 0.03622 -0.0274 0.0857 0.9136
14.500 1.3958 0.04371 0.03825 -0.0265 0.0774 0.9151
14.750 1.4004 0.04566 0.04021 -0.0259 0.0711 0.9166
15.000 1.3996 0.04814 0.04265 -0.0251 0.0611 0.9182
15.250 1.4014 0.05040 0.04492 -0.0245 0.0551 0.9204
15.500 1.4037 0.05266 0.04720 -0.0239 0.0487 0.9226
15.750 1.4056 0.05505 0.04961 -0.0235 0.0432 0.9249
16.000 1.4069 0.05755 0.05211 -0.0232 0.0376 0.9274
16.250 1.4077 0.06020 0.05479 -0.0230 0.0333 0.9302
16.500 1.4100 0.06269 0.05731 -0.0228 0.0292 0.9336
16.750 1.4111 0.06532 0.06000 -0.0227 0.0258 0.9385
17.000 1.4124 0.06799 0.06272 -0.0226 0.0231 0.9446
17.250 1.4146 0.07073 0.06554 -0.0229 0.0206 0.9571
17.500 1.4203 0.07383 0.06870 -0.0244 0.0184 0.9768
17.750 1.4195 0.07687 0.07177 -0.0247 0.0161 1.0000
18.000 1.4214 0.07987 0.07484 -0.0253 0.0148 1.0000
18.250 1.4214 0.08314 0.07816 -0.0260 0.0132 1.0000
18.500 1.4228 0.08629 0.08137 -0.0267 0.0122 1.0000
18.750 1.4212 0.08987 0.08500 -0.0276 0.0109 1.0000
19.000 1.4224 0.09308 0.08828 -0.0285 0.0099 1.0000
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Polar data table (+)
Polar graphs
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