EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 582 AIRFOIL (e582-il) Reynolds number: 500,000 Max Cl/Cd: 106.89 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e582-il-500000-n5.txt Download as CSV file: xf-e582-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 582 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0908 0.07255 0.06950 -0.1263 0.8479 0.0044
-10.000 -0.0911 0.06920 0.06610 -0.1279 0.8362 0.0043
-9.500 -0.1262 0.05533 0.05219 -0.1370 0.8143 0.0042
-9.250 -0.1618 0.04788 0.04459 -0.1393 0.8039 0.0042
-9.000 -0.1821 0.04425 0.04081 -0.1376 0.7951 0.0041
-8.750 -0.2164 0.03832 0.03462 -0.1337 0.7873 0.0041
-8.500 -0.2628 0.02843 0.02397 -0.1275 0.7802 0.0041
-8.250 -0.2678 0.02390 0.01877 -0.1241 0.7753 0.0042
-8.000 -0.2555 0.02173 0.01618 -0.1223 0.7705 0.0044
-7.750 -0.2406 0.01989 0.01402 -0.1209 0.7660 0.0045
-7.500 -0.2207 0.01883 0.01275 -0.1200 0.7624 0.0047
-7.250 -0.1996 0.01786 0.01162 -0.1193 0.7587 0.0048
-7.000 -0.1771 0.01712 0.01075 -0.1188 0.7548 0.0049
-6.750 -0.1540 0.01643 0.00992 -0.1182 0.7511 0.0051
-6.500 -0.1305 0.01579 0.00914 -0.1178 0.7478 0.0053
-6.250 -0.1066 0.01516 0.00841 -0.1173 0.7446 0.0055
-6.000 -0.0826 0.01457 0.00771 -0.1168 0.7411 0.0057
-5.750 -0.0578 0.01415 0.00720 -0.1165 0.7376 0.0062
-5.500 -0.0327 0.01378 0.00673 -0.1162 0.7345 0.0065
-5.250 -0.0091 0.01319 0.00607 -0.1157 0.7317 0.0069
-5.000 0.0159 0.01279 0.00565 -0.1155 0.7285 0.0072
-4.750 0.0409 0.01239 0.00521 -0.1151 0.7252 0.0075
-4.500 0.0663 0.01203 0.00479 -0.1149 0.7219 0.0079
-4.250 0.0921 0.01173 0.00442 -0.1147 0.7190 0.0084
-4.000 0.1182 0.01145 0.00406 -0.1145 0.7162 0.0092
-3.750 0.1443 0.01117 0.00377 -0.1144 0.7130 0.0107
-3.500 0.1706 0.01091 0.00350 -0.1143 0.7098 0.0143
-3.250 0.1969 0.01066 0.00328 -0.1142 0.7067 0.0252
-3.000 0.2231 0.01038 0.00310 -0.1142 0.7037 0.0537
-2.750 0.2495 0.01010 0.00296 -0.1143 0.7009 0.0948
-2.500 0.2754 0.00970 0.00284 -0.1144 0.6977 0.1667
-2.250 0.3012 0.00923 0.00270 -0.1146 0.6943 0.2715
-2.000 0.3275 0.00871 0.00256 -0.1150 0.6910 0.3974
-1.750 0.3539 0.00797 0.00240 -0.1155 0.6879 0.5828
-1.500 0.3785 0.00784 0.00272 -0.1147 0.6849 0.7282
-1.250 0.4067 0.00794 0.00278 -0.1148 0.6813 0.7519
-1.000 0.4344 0.00803 0.00284 -0.1148 0.6776 0.7640
-0.750 0.4623 0.00813 0.00288 -0.1148 0.6741 0.7731
-0.500 0.4899 0.00829 0.00297 -0.1148 0.6709 0.7858
-0.250 0.5157 0.00849 0.00320 -0.1141 0.6671 0.8003
0.000 0.5403 0.00864 0.00337 -0.1133 0.6630 0.8081
0.250 0.5681 0.00869 0.00337 -0.1134 0.6591 0.8114
0.500 0.5965 0.00873 0.00335 -0.1137 0.6553 0.8133
0.750 0.6249 0.00874 0.00334 -0.1140 0.6506 0.8148
1.000 0.6526 0.00876 0.00333 -0.1142 0.6457 0.8159
1.500 0.7072 0.00882 0.00334 -0.1144 0.6361 0.8177
1.750 0.7344 0.00886 0.00336 -0.1144 0.6309 0.8185
2.000 0.7614 0.00891 0.00338 -0.1144 0.6262 0.8195
2.250 0.7885 0.00895 0.00343 -0.1145 0.6204 0.8205
2.500 0.8152 0.00900 0.00346 -0.1145 0.6142 0.8214
2.750 0.8418 0.00906 0.00351 -0.1145 0.6080 0.8222
3.000 0.8682 0.00912 0.00356 -0.1144 0.6008 0.8231
3.250 0.8943 0.00920 0.00363 -0.1143 0.5941 0.8241
3.500 0.9203 0.00928 0.00370 -0.1142 0.5862 0.8253
3.750 0.9459 0.00938 0.00378 -0.1140 0.5788 0.8264
4.000 0.9712 0.00948 0.00388 -0.1138 0.5699 0.8273
4.250 0.9963 0.00959 0.00398 -0.1135 0.5611 0.8282
4.500 1.0202 0.00973 0.00409 -0.1130 0.5512 0.8291
4.750 1.0445 0.00986 0.00422 -0.1126 0.5403 0.8300
5.000 1.0676 0.01002 0.00436 -0.1119 0.5286 0.8308
5.250 1.0892 0.01019 0.00452 -0.1109 0.5156 0.8317
5.500 1.1098 0.01039 0.00470 -0.1098 0.5020 0.8326
5.750 1.1291 0.01062 0.00491 -0.1084 0.4870 0.8338
6.000 1.1463 0.01087 0.00513 -0.1066 0.4712 0.8350
6.250 1.1616 0.01115 0.00537 -0.1044 0.4546 0.8363
6.500 1.1759 0.01150 0.00567 -0.1021 0.4365 0.8375
6.750 1.1893 0.01191 0.00603 -0.0997 0.4183 0.8389
7.000 1.2028 0.01235 0.00642 -0.0974 0.4000 0.8403
7.250 1.2153 0.01284 0.00685 -0.0950 0.3800 0.8417
7.500 1.2264 0.01340 0.00735 -0.0924 0.3597 0.8432
7.750 1.2370 0.01402 0.00790 -0.0899 0.3402 0.8447
8.000 1.2481 0.01464 0.00847 -0.0875 0.3216 0.8461
8.250 1.2584 0.01529 0.00909 -0.0851 0.3039 0.8475
8.500 1.2680 0.01601 0.00977 -0.0826 0.2862 0.8490
8.750 1.2765 0.01683 0.01054 -0.0801 0.2683 0.8508
9.000 1.2854 0.01768 0.01136 -0.0778 0.2515 0.8528
9.250 1.2941 0.01859 0.01223 -0.0756 0.2342 0.8548
9.500 1.3020 0.01960 0.01319 -0.0734 0.2162 0.8567
9.750 1.3089 0.02072 0.01425 -0.0712 0.1979 0.8587
10.000 1.3167 0.02186 0.01533 -0.0692 0.1819 0.8605
10.500 1.3303 0.02429 0.01771 -0.0653 0.1503 0.8644
10.750 1.3372 0.02558 0.01897 -0.0635 0.1358 0.8666
11.000 1.3449 0.02686 0.02024 -0.0619 0.1241 0.8690
11.250 1.3515 0.02827 0.02162 -0.0603 0.1113 0.8715
11.500 1.3585 0.02969 0.02303 -0.0588 0.1000 0.8740
11.750 1.3652 0.03116 0.02451 -0.0573 0.0888 0.8766
12.000 1.3706 0.03274 0.02609 -0.0559 0.0777 0.8796
12.250 1.3759 0.03440 0.02774 -0.0545 0.0678 0.8829
12.500 1.3799 0.03622 0.02954 -0.0531 0.0572 0.8868
13.000 1.3869 0.04004 0.03336 -0.0506 0.0393 0.8961
13.250 1.3909 0.04199 0.03534 -0.0495 0.0331 0.9022
13.500 1.3939 0.04409 0.03745 -0.0485 0.0268 0.9093
14.000 1.3993 0.04846 0.04194 -0.0467 0.0175 0.9424
14.250 1.4022 0.05073 0.04425 -0.0461 0.0140 1.0000
14.500 1.4083 0.05289 0.04648 -0.0458 0.0125 1.0000
14.750 1.4120 0.05535 0.04899 -0.0455 0.0106 1.0000
15.000 1.4166 0.05777 0.05148 -0.0454 0.0092 1.0000
15.250 1.4196 0.06042 0.05419 -0.0453 0.0076 1.0000
15.500 1.4231 0.06308 0.05692 -0.0453 0.0065 1.0000
15.750 1.4255 0.06592 0.05985 -0.0453 0.0057 1.0000
16.000 1.4283 0.06876 0.06277 -0.0455 0.0049 1.0000
16.250 1.4290 0.07193 0.06602 -0.0458 0.0041 1.0000
16.500 1.4300 0.07514 0.06933 -0.0462 0.0035 1.0000
16.750 1.4302 0.07852 0.07280 -0.0468 0.0031 1.0000
17.000 1.4291 0.08213 0.07650 -0.0474 0.0026 1.0000
17.250 1.4288 0.08569 0.08017 -0.0482 0.0023 1.0000
17.500 1.4265 0.08961 0.08419 -0.0491 0.0020 1.0000
17.750 1.4237 0.09370 0.08839 -0.0502 0.0018 1.0000
18.000 1.4207 0.09787 0.09268 -0.0515 0.0015 1.0000
18.250 1.4172 0.10217 0.09709 -0.0529 0.0014 1.0000
18.500 1.4128 0.10669 0.10174 -0.0544 0.0012 1.0000
18.750 1.4077 0.11139 0.10656 -0.0562 0.0011 1.0000
19.000 1.4019 0.11628 0.11157 -0.0582 0.0010 1.0000
19.250 1.3959 0.12126 0.11667 -0.0603 0.0009 1.0000
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