EPPLER 361 AIRFOIL (e361-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 361 AIRFOIL (e361-il) Reynolds number: 50,000 Max Cl/Cd: 31.52 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e361-il-50000-n5.txt Download as CSV file: xf-e361-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 361 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3919 0.13053 0.12369 -0.0103 1.0000 0.0590
-12.000 -0.4084 0.12503 0.11820 -0.0149 1.0000 0.0517
-11.750 -0.5082 0.12793 0.12052 -0.0100 1.0000 0.0512
-11.500 -0.4994 0.12421 0.11682 -0.0102 1.0000 0.0497
-11.250 -0.4958 0.12005 0.11269 -0.0116 1.0000 0.0481
-11.000 -0.4958 0.11526 0.10796 -0.0138 1.0000 0.0466
-10.750 -0.5121 0.10672 0.09949 -0.0206 1.0000 0.0430
-10.500 -0.5087 0.10275 0.09557 -0.0217 1.0000 0.0425
-10.250 -0.5088 0.09807 0.09094 -0.0237 1.0000 0.0420
-10.000 -0.5105 0.09312 0.08604 -0.0263 1.0000 0.0414
-9.750 -0.5161 0.08731 0.08027 -0.0300 1.0000 0.0407
-9.500 -0.5272 0.08163 0.07461 -0.0336 1.0000 0.0401
-9.250 -0.5423 0.07657 0.06954 -0.0360 1.0000 0.0395
-9.000 -0.5603 0.07218 0.06512 -0.0365 1.0000 0.0390
-8.750 -0.5770 0.06851 0.06138 -0.0354 1.0000 0.0386
-8.500 -0.5903 0.06463 0.05735 -0.0341 1.0000 0.0382
-8.250 -0.5997 0.06089 0.05339 -0.0324 1.0000 0.0378
-8.000 -0.6052 0.05731 0.04954 -0.0304 1.0000 0.0374
-7.750 -0.6059 0.05407 0.04606 -0.0283 1.0000 0.0377
-7.500 -0.6034 0.05114 0.04286 -0.0261 1.0000 0.0381
-7.250 -0.5988 0.04840 0.03986 -0.0238 1.0000 0.0389
-7.000 -0.5928 0.04577 0.03691 -0.0213 1.0000 0.0398
-6.750 -0.5858 0.04319 0.03397 -0.0186 1.0000 0.0411
-6.500 -0.5768 0.04076 0.03115 -0.0159 1.0000 0.0420
-6.250 -0.5657 0.03853 0.02852 -0.0133 1.0000 0.0427
-6.000 -0.5533 0.03643 0.02624 -0.0110 1.0000 0.0437
-5.750 -0.5409 0.03481 0.02450 -0.0088 1.0000 0.0448
-5.500 -0.5295 0.03350 0.02308 -0.0064 1.0000 0.0466
-5.250 -0.5168 0.03228 0.02167 -0.0041 0.9996 0.0493
-5.000 -0.4763 0.03035 0.01956 -0.0066 0.9886 0.0547
-4.750 -0.4348 0.02875 0.01774 -0.0089 0.9778 0.0627
-4.500 -0.3952 0.02733 0.01625 -0.0111 0.9666 0.0742
-4.250 -0.3578 0.02589 0.01487 -0.0132 0.9553 0.0928
-4.000 -0.3221 0.02440 0.01349 -0.0152 0.9440 0.1282
-3.750 -0.2956 0.02237 0.01229 -0.0162 0.9312 0.2292
-3.500 -0.2774 0.02033 0.01259 -0.0130 0.9210 0.6327
-3.250 -0.2332 0.02125 0.01346 -0.0121 0.9137 0.7870
-3.000 -0.1648 0.02283 0.01467 -0.0147 0.9109 0.8672
-2.750 -0.0854 0.02342 0.01479 -0.0221 0.9072 0.9043
-2.500 -0.0279 0.02331 0.01431 -0.0275 0.8980 0.9215
-2.250 0.0211 0.02310 0.01381 -0.0319 0.8863 0.9340
-2.000 0.0647 0.02289 0.01336 -0.0353 0.8747 0.9450
-1.750 0.1087 0.02263 0.01286 -0.0388 0.8635 0.9544
-1.500 0.1486 0.02241 0.01245 -0.0416 0.8510 0.9631
-1.250 0.1842 0.02227 0.01215 -0.0437 0.8391 0.9720
-1.000 0.2230 0.02203 0.01177 -0.0464 0.8282 0.9794
-0.750 0.2588 0.02186 0.01147 -0.0485 0.8174 0.9867
-0.500 0.2933 0.02174 0.01126 -0.0505 0.8062 0.9940
-0.250 0.3274 0.02161 0.01103 -0.0523 0.7962 1.0000
0.000 0.3473 0.02169 0.01106 -0.0514 0.7856 1.0000
0.250 0.3664 0.02184 0.01116 -0.0504 0.7750 1.0000
0.500 0.3867 0.02194 0.01121 -0.0494 0.7660 1.0000
0.750 0.4053 0.02213 0.01139 -0.0483 0.7555 1.0000
1.000 0.4245 0.02231 0.01156 -0.0471 0.7461 1.0000
1.250 0.4446 0.02247 0.01171 -0.0461 0.7369 1.0000
1.500 0.4633 0.02272 0.01197 -0.0450 0.7267 1.0000
2.000 0.5015 0.02313 0.01242 -0.0423 0.7069 1.0000
2.250 0.5197 0.02334 0.01266 -0.0408 0.6963 1.0000
2.500 0.5395 0.02342 0.01272 -0.0391 0.6861 1.0000
2.750 0.5558 0.02365 0.01299 -0.0372 0.6729 1.0000
3.250 0.5899 0.02388 0.01329 -0.0330 0.6453 1.0000
3.500 0.6073 0.02392 0.01334 -0.0307 0.6305 1.0000
3.750 0.6245 0.02393 0.01337 -0.0284 0.6150 1.0000
4.000 0.6416 0.02394 0.01340 -0.0261 0.5989 1.0000
4.250 0.6584 0.02395 0.01347 -0.0238 0.5820 1.0000
4.500 0.6750 0.02396 0.01353 -0.0214 0.5645 1.0000
4.750 0.6916 0.02397 0.01358 -0.0190 0.5461 1.0000
5.000 0.7085 0.02395 0.01361 -0.0166 0.5268 1.0000
5.250 0.7229 0.02408 0.01380 -0.0141 0.5044 1.0000
5.500 0.7383 0.02413 0.01389 -0.0116 0.4803 1.0000
5.750 0.7522 0.02428 0.01407 -0.0090 0.4517 1.0000
6.000 0.7661 0.02444 0.01421 -0.0063 0.4196 1.0000
6.250 0.7792 0.02472 0.01436 -0.0035 0.3841 1.0000
6.500 0.7907 0.02520 0.01464 -0.0007 0.3473 1.0000
6.750 0.8009 0.02591 0.01510 0.0021 0.3146 1.0000
7.000 0.8107 0.02680 0.01580 0.0048 0.2878 1.0000
7.250 0.8201 0.02778 0.01659 0.0073 0.2660 1.0000
7.500 0.8307 0.02880 0.01747 0.0096 0.2481 1.0000
7.750 0.8426 0.02984 0.01842 0.0116 0.2331 1.0000
8.000 0.8555 0.03087 0.01944 0.0135 0.2196 1.0000
8.250 0.8696 0.03192 0.02051 0.0152 0.2075 1.0000
8.500 0.8852 0.03300 0.02161 0.0166 0.1972 1.0000
8.750 0.9024 0.03407 0.02260 0.0179 0.1881 1.0000
9.000 0.9182 0.03521 0.02393 0.0192 0.1789 1.0000
9.250 0.9369 0.03637 0.02510 0.0202 0.1713 1.0000
9.500 0.9538 0.03763 0.02651 0.0213 0.1639 1.0000
9.750 0.9728 0.03888 0.02778 0.0221 0.1572 1.0000
10.000 0.9864 0.04034 0.02948 0.0234 0.1506 1.0000
10.250 1.0080 0.04164 0.03074 0.0239 0.1450 1.0000
10.500 1.0166 0.04342 0.03285 0.0255 0.1396 1.0000
10.750 1.0279 0.04502 0.03461 0.0268 0.1344 1.0000
11.000 1.0476 0.04657 0.03614 0.0273 0.1297 1.0000
11.250 1.0448 0.04879 0.03875 0.0297 0.1261 1.0000
11.500 1.0453 0.05090 0.04110 0.0316 0.1223 1.0000
11.750 1.0547 0.05263 0.04289 0.0327 0.1184 1.0000
12.000 1.0600 0.05488 0.04526 0.0339 0.1153 1.0000
12.250 1.0442 0.05823 0.04896 0.0354 0.1134 1.0000
12.500 1.0270 0.06201 0.05302 0.0361 0.1115 1.0000
12.750 1.0077 0.06635 0.05760 0.0359 0.1099 1.0000
13.000 0.9835 0.07157 0.06303 0.0348 0.1086 1.0000
13.250 0.9449 0.07929 0.07095 0.0317 0.1085 1.0000
13.500 0.8472 0.09871 0.09048 0.0201 0.1109 1.0000
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