EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 584 AIRFOIL (e584-il) Reynolds number: 500,000 Max Cl/Cd: 103.12 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e584-il-500000.txt Download as CSV file: xf-e584-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0544 0.09676 0.09334 -0.1203 0.7806 0.0196
-11.500 -0.0618 0.09105 0.08761 -0.1235 0.7729 0.0197
-11.250 -0.0596 0.08777 0.08430 -0.1241 0.7656 0.0199
-11.000 -0.0514 0.08613 0.08260 -0.1239 0.7592 0.0202
-10.750 -0.0493 0.08289 0.07936 -0.1251 0.7535 0.0203
-10.500 -0.0449 0.08035 0.07679 -0.1258 0.7484 0.0205
-10.250 -0.0443 0.07702 0.07343 -0.1272 0.7440 0.0207
-10.000 -0.0444 0.07361 0.07004 -0.1287 0.7403 0.0213
-9.750 -0.0488 0.06932 0.06577 -0.1309 0.7367 0.0214
-9.500 -0.0596 0.06379 0.06026 -0.1348 0.7332 0.0216
-9.250 -0.0815 0.05767 0.05408 -0.1387 0.7298 0.0214
-9.000 -0.1025 0.05350 0.04981 -0.1387 0.7268 0.0216
-8.750 -0.1209 0.05035 0.04661 -0.1366 0.7238 0.0218
-8.500 -0.1401 0.04780 0.04396 -0.1328 0.7207 0.0221
-8.250 -0.1913 0.04316 0.03863 -0.1243 0.7178 0.0236
-8.000 -0.1855 0.03943 0.03490 -0.1233 0.7154 0.0239
-7.750 -0.1748 0.03769 0.03310 -0.1220 0.7129 0.0242
-7.500 -0.1646 0.03614 0.03148 -0.1205 0.7106 0.0246
-7.250 -0.1545 0.03449 0.02973 -0.1188 0.7081 0.0252
-7.000 -0.1451 0.03254 0.02757 -0.1166 0.7058 0.0265
-6.500 -0.1380 0.02042 0.01375 -0.1069 0.7018 0.0130
-6.250 -0.1152 0.01877 0.01190 -0.1061 0.6998 0.0126
-6.000 -0.0906 0.01751 0.01043 -0.1056 0.6978 0.0122
-5.750 -0.0656 0.01647 0.00923 -0.1051 0.6957 0.0120
-5.500 -0.0416 0.01564 0.00832 -0.1044 0.6934 0.0120
-5.250 -0.0182 0.01497 0.00759 -0.1037 0.6911 0.0122
-5.000 0.0051 0.01441 0.00697 -0.1030 0.6889 0.0124
-4.750 0.0282 0.01391 0.00642 -0.1022 0.6868 0.0129
-4.500 0.0514 0.01347 0.00591 -0.1014 0.6845 0.0135
-4.250 0.0748 0.01305 0.00546 -0.1008 0.6823 0.0149
-4.000 0.0983 0.01271 0.00510 -0.1001 0.6801 0.0170
-3.750 0.1219 0.01238 0.00478 -0.0995 0.6778 0.0212
-3.500 0.1440 0.01191 0.00445 -0.0985 0.6754 0.0473
-3.250 0.1671 0.01154 0.00427 -0.0980 0.6731 0.0913
-3.000 0.1901 0.01117 0.00414 -0.0975 0.6708 0.1583
-2.750 0.2100 0.01055 0.00401 -0.0967 0.6685 0.2962
-2.500 0.2229 0.00941 0.00382 -0.0948 0.6663 0.5546
-2.250 0.2371 0.00921 0.00446 -0.0915 0.6640 0.7778
-2.000 0.2643 0.00952 0.00470 -0.0912 0.6615 0.8074
-1.750 0.2908 0.00988 0.00500 -0.0905 0.6591 0.8213
-1.500 0.3161 0.01029 0.00537 -0.0894 0.6568 0.8304
-1.250 0.3430 0.01065 0.00564 -0.0890 0.6546 0.8409
-1.000 0.3678 0.01110 0.00605 -0.0878 0.6523 0.8471
-0.750 0.3930 0.01128 0.00620 -0.0872 0.6500 0.8552
-0.500 0.4153 0.01149 0.00641 -0.0856 0.6475 0.8598
-0.250 0.4381 0.01184 0.00674 -0.0840 0.6450 0.8693
0.000 0.4592 0.01227 0.00717 -0.0813 0.6427 0.8801
0.250 0.4839 0.01255 0.00739 -0.0801 0.6405 0.8902
0.500 0.5138 0.01274 0.00752 -0.0804 0.6381 0.8933
0.750 0.5362 0.01268 0.00748 -0.0795 0.6357 0.8964
1.000 0.5587 0.01265 0.00745 -0.0788 0.6330 0.8996
1.250 0.5832 0.01265 0.00742 -0.0787 0.6301 0.9023
1.500 0.6091 0.01256 0.00730 -0.0785 0.6277 0.9037
1.750 0.6372 0.01255 0.00723 -0.0788 0.6254 0.9048
2.000 0.6630 0.01254 0.00722 -0.0786 0.6230 0.9060
2.250 0.6854 0.01245 0.00717 -0.0778 0.6199 0.9076
2.500 0.7099 0.01238 0.00710 -0.0774 0.6168 0.9087
2.750 0.7360 0.01232 0.00703 -0.0774 0.6140 0.9101
3.000 0.7640 0.01227 0.00694 -0.0778 0.6115 0.9111
3.250 0.7903 0.01223 0.00691 -0.0779 0.6088 0.9120
3.500 0.8131 0.01214 0.00687 -0.0773 0.6051 0.9135
3.750 0.8387 0.01205 0.00679 -0.0772 0.6015 0.9144
4.000 0.8664 0.01194 0.00667 -0.0776 0.5983 0.9151
4.250 0.8939 0.01187 0.00659 -0.0780 0.5952 0.9157
4.500 0.9177 0.01181 0.00659 -0.0776 0.5905 0.9168
4.750 0.9441 0.01172 0.00653 -0.0778 0.5865 0.9173
5.000 0.9704 0.01160 0.00640 -0.0778 0.5827 0.9178
5.250 0.9937 0.01154 0.00638 -0.0773 0.5782 0.9184
5.500 1.0167 0.01146 0.00635 -0.0767 0.5730 0.9190
5.750 1.0415 0.01141 0.00628 -0.0764 0.5685 0.9196
6.000 1.0634 0.01140 0.00631 -0.0756 0.5630 0.9207
6.250 1.0855 0.01139 0.00634 -0.0748 0.5570 0.9215
6.750 1.1305 0.01145 0.00645 -0.0736 0.5443 0.9229
7.000 1.1523 0.01150 0.00650 -0.0729 0.5376 0.9236
7.250 1.1708 0.01155 0.00659 -0.0714 0.5301 0.9246
7.500 1.1896 0.01162 0.00668 -0.0701 0.5225 0.9255
7.750 1.2082 0.01173 0.00684 -0.0688 0.5143 0.9265
8.000 1.2261 0.01189 0.00700 -0.0674 0.5055 0.9275
8.250 1.2430 0.01207 0.00722 -0.0658 0.4954 0.9290
8.500 1.2594 0.01231 0.00746 -0.0643 0.4851 0.9300
8.750 1.2743 0.01261 0.00775 -0.0625 0.4739 0.9310
9.000 1.2884 0.01293 0.00810 -0.0606 0.4617 0.9320
9.250 1.3000 0.01329 0.00846 -0.0583 0.4499 0.9334
9.500 1.3095 0.01374 0.00892 -0.0558 0.4377 0.9349
9.750 1.3174 0.01430 0.00946 -0.0531 0.4248 0.9366
10.000 1.3240 0.01496 0.01011 -0.0504 0.4108 0.9384
10.250 1.3310 0.01569 0.01085 -0.0479 0.3965 0.9404
10.500 1.3362 0.01657 0.01172 -0.0453 0.3817 0.9424
10.750 1.3397 0.01760 0.01274 -0.0427 0.3661 0.9447
11.000 1.3423 0.01868 0.01382 -0.0401 0.3515 0.9475
11.250 1.3433 0.01994 0.01506 -0.0374 0.3362 0.9505
11.500 1.3441 0.02132 0.01644 -0.0350 0.3209 0.9537
11.750 1.3444 0.02285 0.01795 -0.0327 0.3053 0.9573
12.000 1.3452 0.02451 0.01959 -0.0308 0.2895 0.9616
12.250 1.3460 0.02645 0.02149 -0.0294 0.2718 0.9673
12.500 1.3501 0.02850 0.02351 -0.0290 0.2548 0.9753
12.750 1.3521 0.03051 0.02549 -0.0281 0.2390 1.0000
13.000 1.3541 0.03260 0.02755 -0.0272 0.2236 1.0000
13.250 1.3574 0.03463 0.02955 -0.0264 0.2096 1.0000
13.500 1.3608 0.03668 0.03159 -0.0257 0.1962 1.0000
13.750 1.3629 0.03887 0.03374 -0.0250 0.1823 1.0000
14.000 1.3656 0.04102 0.03588 -0.0244 0.1695 1.0000
14.250 1.3670 0.04335 0.03818 -0.0238 0.1568 1.0000
14.500 1.3688 0.04569 0.04049 -0.0232 0.1448 1.0000
14.750 1.3691 0.04822 0.04298 -0.0227 0.1323 1.0000
15.000 1.3690 0.05083 0.04557 -0.0223 0.1202 1.0000
15.250 1.3687 0.05353 0.04822 -0.0220 0.1083 1.0000
15.750 1.3694 0.05900 0.05367 -0.0217 0.0877 1.0000
16.000 1.3702 0.06177 0.05643 -0.0217 0.0787 1.0000
16.250 1.3701 0.06470 0.05937 -0.0217 0.0711 1.0000
16.500 1.3689 0.06783 0.06249 -0.0218 0.0636 1.0000
16.750 1.3690 0.07088 0.06556 -0.0221 0.0568 1.0000
17.000 1.3686 0.07402 0.06872 -0.0225 0.0507 1.0000
17.250 1.3668 0.07738 0.07210 -0.0229 0.0453 1.0000
17.500 1.3635 0.08104 0.07577 -0.0235 0.0401 1.0000
17.750 1.3621 0.08450 0.07927 -0.0242 0.0353 1.0000
18.000 1.3604 0.08805 0.08287 -0.0249 0.0317 1.0000
18.250 1.3554 0.09210 0.08693 -0.0259 0.0282 1.0000
18.500 1.3549 0.09561 0.09053 -0.0269 0.0257 1.0000
18.750 1.3513 0.09960 0.09457 -0.0280 0.0231 1.0000
19.000 1.3490 0.10347 0.09849 -0.0293 0.0207 1.0000
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Polar data table (+)
Polar graphs
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