EPPLER 485 AIRFOIL (e485-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 485 AIRFOIL (e485-il) Reynolds number: 100,000 Max Cl/Cd: 44.81 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e485-il-100000.txt Download as CSV file: xf-e485-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 485 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5041 0.11681 0.11176 -0.0157 1.0000 0.1184
-11.000 -0.5051 0.11284 0.10783 -0.0173 1.0000 0.1234
-10.750 -0.5602 0.10689 0.10208 -0.0288 1.0000 0.1274
-10.500 -0.5194 0.10331 0.09843 -0.0223 1.0000 0.1301
-10.250 -0.4999 0.07239 0.06784 -0.0414 1.0000 0.0689
-10.000 -0.5307 0.06449 0.05990 -0.0454 1.0000 0.0663
-9.750 -0.5740 0.05763 0.05291 -0.0476 1.0000 0.0642
-9.500 -0.6524 0.06527 0.06024 -0.0435 1.0000 0.0673
-9.250 -0.7071 0.05933 0.05374 -0.0386 1.0000 0.0588
-9.000 -0.7123 0.05507 0.04936 -0.0364 1.0000 0.0575
-8.750 -0.7182 0.05119 0.04527 -0.0335 1.0000 0.0559
-8.500 -0.7250 0.04720 0.04095 -0.0300 1.0000 0.0544
-8.250 -0.7288 0.04354 0.03690 -0.0262 1.0000 0.0533
-8.000 -0.7292 0.04012 0.03305 -0.0224 1.0000 0.0529
-7.750 -0.7243 0.03741 0.02997 -0.0190 1.0000 0.0538
-7.500 -0.7172 0.03541 0.02764 -0.0158 1.0000 0.0565
-7.250 -0.7101 0.03357 0.02533 -0.0122 1.0000 0.0590
-7.000 -0.6995 0.03095 0.02238 -0.0093 1.0000 0.0611
-6.750 -0.6863 0.02932 0.02078 -0.0072 1.0000 0.0656
-6.500 -0.6736 0.02810 0.01928 -0.0044 1.0000 0.0711
-6.250 -0.6567 0.02609 0.01723 -0.0026 1.0000 0.0762
-6.000 -0.6428 0.02517 0.01616 -0.0002 1.0000 0.0845
-5.750 -0.6271 0.02378 0.01484 0.0017 1.0000 0.0936
-5.500 -0.6125 0.02270 0.01379 0.0038 1.0000 0.1058
-5.250 -0.5982 0.02170 0.01287 0.0060 1.0000 0.1211
-5.000 -0.5841 0.02085 0.01203 0.0081 1.0000 0.1415
-4.750 -0.5718 0.01986 0.01128 0.0104 1.0000 0.1692
-4.500 -0.5604 0.01884 0.01061 0.0127 1.0000 0.2108
-4.250 -0.5509 0.01762 0.00998 0.0152 1.0000 0.2900
-4.000 -0.5446 0.01629 0.00962 0.0184 1.0000 0.4378
-3.750 -0.5376 0.01561 0.00986 0.0227 1.0000 0.6038
-3.500 -0.5066 0.01617 0.01078 0.0236 0.9930 0.7290
-3.250 -0.4714 0.01708 0.01163 0.0237 0.9842 0.7928
-3.000 -0.4360 0.01805 0.01246 0.0240 0.9755 0.8313
-2.750 -0.3910 0.01916 0.01339 0.0226 0.9687 0.8623
-2.500 -0.3413 0.02012 0.01414 0.0201 0.9616 0.8871
-2.250 -0.2642 0.02115 0.01492 0.0124 0.9589 0.9056
-2.000 -0.1735 0.02180 0.01532 0.0015 0.9577 0.9203
-1.750 -0.0926 0.02200 0.01532 -0.0083 0.9548 0.9336
-1.500 -0.0241 0.02190 0.01507 -0.0162 0.9482 0.9461
-1.250 0.0475 0.02163 0.01468 -0.0249 0.9431 0.9570
-1.000 0.1211 0.02109 0.01406 -0.0341 0.9369 0.9652
-0.750 0.1906 0.02046 0.01336 -0.0425 0.9301 0.9730
-0.500 0.2548 0.01978 0.01264 -0.0500 0.9213 0.9807
-0.250 0.3208 0.01890 0.01173 -0.0576 0.9122 0.9872
0.000 0.3739 0.01819 0.01101 -0.0628 0.8982 0.9946
0.250 0.4191 0.01754 0.01035 -0.0664 0.8825 1.0000
0.500 0.4399 0.01739 0.01016 -0.0652 0.8635 1.0000
0.750 0.4585 0.01728 0.01002 -0.0635 0.8444 1.0000
1.000 0.4766 0.01717 0.00988 -0.0616 0.8262 1.0000
1.250 0.4945 0.01707 0.00975 -0.0596 0.8087 1.0000
1.500 0.5120 0.01698 0.00963 -0.0575 0.7910 1.0000
1.750 0.5287 0.01694 0.00958 -0.0554 0.7718 1.0000
2.000 0.5463 0.01686 0.00949 -0.0533 0.7532 1.0000
2.250 0.5646 0.01676 0.00935 -0.0513 0.7350 1.0000
2.500 0.5834 0.01666 0.00920 -0.0494 0.7172 1.0000
2.750 0.6009 0.01663 0.00917 -0.0474 0.6961 1.0000
3.000 0.6196 0.01655 0.00907 -0.0455 0.6762 1.0000
3.250 0.6387 0.01650 0.00896 -0.0436 0.6562 1.0000
3.500 0.6569 0.01650 0.00895 -0.0417 0.6336 1.0000
3.750 0.6762 0.01648 0.00886 -0.0399 0.6124 1.0000
4.000 0.6941 0.01654 0.00891 -0.0380 0.5881 1.0000
4.250 0.7125 0.01663 0.00893 -0.0361 0.5645 1.0000
4.500 0.7308 0.01675 0.00897 -0.0342 0.5405 1.0000
4.750 0.7480 0.01695 0.00913 -0.0322 0.5154 1.0000
5.000 0.7653 0.01719 0.00930 -0.0303 0.4913 1.0000
5.250 0.7821 0.01747 0.00951 -0.0283 0.4672 1.0000
5.500 0.7981 0.01781 0.00980 -0.0262 0.4431 1.0000
5.750 0.8145 0.01820 0.01006 -0.0241 0.4211 1.0000
6.000 0.8291 0.01861 0.01047 -0.0219 0.3981 1.0000
6.250 0.8445 0.01907 0.01084 -0.0197 0.3775 1.0000
6.500 0.8583 0.01956 0.01132 -0.0173 0.3567 1.0000
6.750 0.8721 0.02007 0.01178 -0.0149 0.3370 1.0000
7.000 0.8861 0.02062 0.01225 -0.0126 0.3188 1.0000
7.250 0.8991 0.02120 0.01280 -0.0101 0.3010 1.0000
7.500 0.9115 0.02180 0.01344 -0.0076 0.2835 1.0000
7.750 0.9242 0.02244 0.01407 -0.0051 0.2668 1.0000
8.000 0.9372 0.02311 0.01472 -0.0027 0.2508 1.0000
8.250 0.9505 0.02383 0.01543 -0.0004 0.2354 1.0000
8.500 0.9641 0.02459 0.01617 0.0018 0.2203 1.0000
8.750 0.9785 0.02542 0.01700 0.0038 0.2059 1.0000
9.000 0.9927 0.02629 0.01791 0.0058 0.1920 1.0000
9.250 1.0069 0.02722 0.01887 0.0077 0.1785 1.0000
9.500 1.0217 0.02826 0.01994 0.0094 0.1661 1.0000
9.750 1.0359 0.02932 0.02102 0.0111 0.1542 1.0000
10.000 1.0518 0.03050 0.02214 0.0126 0.1431 1.0000
10.250 1.0649 0.03155 0.02324 0.0143 0.1326 1.0000
10.500 1.0755 0.03296 0.02489 0.0164 0.1233 1.0000
10.750 1.0901 0.03449 0.02643 0.0178 0.1146 1.0000
11.000 1.1013 0.03573 0.02772 0.0196 0.1064 1.0000
11.250 1.1093 0.03764 0.02986 0.0217 0.0996 1.0000
11.500 1.1230 0.03907 0.03122 0.0229 0.0925 1.0000
11.750 1.1235 0.04115 0.03362 0.0257 0.0876 1.0000
12.000 1.1238 0.04278 0.03543 0.0285 0.0829 1.0000
12.250 1.1340 0.04503 0.03764 0.0296 0.0776 1.0000
12.500 1.1222 0.04718 0.04016 0.0330 0.0749 1.0000
12.750 1.1159 0.04959 0.04281 0.0351 0.0720 1.0000
13.000 1.1328 0.05219 0.04524 0.0352 0.0666 1.0000
13.250 1.1131 0.05497 0.04837 0.0375 0.0657 1.0000
13.500 1.0931 0.05840 0.05212 0.0387 0.0648 1.0000
13.750 1.0708 0.06262 0.05664 0.0389 0.0640 1.0000
14.000 1.0475 0.06746 0.06175 0.0381 0.0637 1.0000
14.250 1.0213 0.07323 0.06773 0.0362 0.0638 1.0000
14.500 0.9921 0.08005 0.07477 0.0331 0.0644 1.0000
14.750 0.9615 0.08790 0.08278 0.0288 0.0652 1.0000
15.000 0.9311 0.09675 0.09175 0.0239 0.0662 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 485 AIRFOIL (e485-il)