EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Reynolds number: 50,000 Max Cl/Cd: 23.83 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ea61012-il-50000-n5.txt Download as CSV file: xf-ea61012-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EA 6(-1)-012 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7454 0.09180 0.08372 -0.0190 1.0000 0.0896
-11.500 -0.7797 0.08308 0.07495 -0.0246 1.0000 0.0892
-11.250 -0.8117 0.07629 0.06805 -0.0279 1.0000 0.0889
-11.000 -0.8415 0.07093 0.06253 -0.0292 1.0000 0.0889
-10.750 -0.8674 0.06674 0.05814 -0.0285 1.0000 0.0890
-10.500 -0.8870 0.06292 0.05403 -0.0270 1.0000 0.0895
-10.250 -0.9000 0.05924 0.04999 -0.0255 1.0000 0.0901
-10.000 -0.9005 0.05597 0.04645 -0.0244 1.0000 0.0909
-9.750 -0.8917 0.05313 0.04343 -0.0235 1.0000 0.0918
-9.500 -0.8813 0.05048 0.04058 -0.0227 1.0000 0.0927
-9.250 -0.8692 0.04801 0.03786 -0.0218 1.0000 0.0937
-9.000 -0.8550 0.04569 0.03532 -0.0209 1.0000 0.0949
-8.750 -0.8393 0.04355 0.03295 -0.0201 1.0000 0.0966
-8.500 -0.8231 0.04164 0.03077 -0.0193 1.0000 0.0993
-8.250 -0.8064 0.03977 0.02854 -0.0183 1.0000 0.1021
-8.000 -0.7863 0.03793 0.02649 -0.0177 1.0000 0.1043
-7.750 -0.7627 0.03627 0.02477 -0.0174 1.0000 0.1063
-7.500 -0.7388 0.03478 0.02321 -0.0170 1.0000 0.1083
-7.250 -0.7143 0.03341 0.02175 -0.0166 1.0000 0.1108
-7.000 -0.6890 0.03215 0.02038 -0.0161 1.0000 0.1136
-6.750 -0.6633 0.03104 0.01910 -0.0157 1.0000 0.1170
-6.500 -0.6392 0.02999 0.01811 -0.0151 1.0000 0.1215
-6.250 -0.6170 0.02909 0.01726 -0.0143 1.0000 0.1274
-6.000 -0.5946 0.02827 0.01634 -0.0134 1.0000 0.1333
-5.750 -0.5753 0.02740 0.01555 -0.0122 1.0000 0.1384
-5.500 -0.5592 0.02662 0.01482 -0.0105 1.0000 0.1448
-5.250 -0.5464 0.02589 0.01414 -0.0083 1.0000 0.1523
-5.000 -0.5374 0.02519 0.01351 -0.0056 1.0000 0.1616
-4.750 -0.5307 0.02447 0.01292 -0.0027 1.0000 0.1750
-4.500 -0.5247 0.02370 0.01232 0.0002 1.0000 0.1979
-4.250 -0.5198 0.02273 0.01171 0.0031 1.0000 0.2371
-4.000 -0.5133 0.02155 0.01116 0.0056 0.9989 0.3215
-3.750 -0.4915 0.02065 0.01116 0.0064 0.9895 0.4582
-3.500 -0.4644 0.02089 0.01184 0.0076 0.9818 0.5740
-3.250 -0.4368 0.02125 0.01220 0.0083 0.9736 0.6340
-3.000 -0.4118 0.02190 0.01284 0.0100 0.9655 0.6892
-2.750 -0.3869 0.02283 0.01378 0.0125 0.9585 0.7382
-2.500 -0.3614 0.02352 0.01445 0.0150 0.9521 0.7720
-2.250 -0.3299 0.02385 0.01468 0.0154 0.9465 0.7950
-2.000 -0.2971 0.02399 0.01470 0.0149 0.9412 0.8144
-1.750 -0.2644 0.02404 0.01466 0.0143 0.9351 0.8275
-1.500 -0.2266 0.02404 0.01456 0.0124 0.9303 0.8375
-1.250 -0.1916 0.02398 0.01441 0.0107 0.9252 0.8481
-1.000 -0.1584 0.02398 0.01435 0.0094 0.9190 0.8571
-0.750 -0.1212 0.02397 0.01428 0.0074 0.9138 0.8659
-0.500 -0.0836 0.02401 0.01428 0.0053 0.9089 0.8759
-0.250 -0.0447 0.02410 0.01437 0.0031 0.9025 0.8857
0.000 0.0000 0.02412 0.01437 0.0000 0.8958 0.8958
0.250 0.0446 0.02410 0.01437 -0.0031 0.8857 0.9025
0.500 0.0836 0.02401 0.01428 -0.0053 0.8759 0.9089
0.750 0.1211 0.02397 0.01428 -0.0074 0.8660 0.9138
1.000 0.1584 0.02398 0.01435 -0.0094 0.8571 0.9190
1.250 0.1915 0.02398 0.01441 -0.0106 0.8481 0.9253
1.500 0.2266 0.02403 0.01456 -0.0124 0.8375 0.9303
1.750 0.2644 0.02404 0.01466 -0.0143 0.8275 0.9351
2.000 0.2972 0.02398 0.01470 -0.0150 0.8146 0.9412
2.250 0.3299 0.02385 0.01468 -0.0154 0.7950 0.9465
2.500 0.3615 0.02351 0.01444 -0.0149 0.7719 0.9521
2.750 0.3869 0.02282 0.01376 -0.0125 0.7380 0.9585
3.000 0.4119 0.02190 0.01284 -0.0100 0.6896 0.9655
3.250 0.4367 0.02125 0.01220 -0.0083 0.6343 0.9736
3.500 0.4645 0.02089 0.01184 -0.0076 0.5751 0.9818
3.750 0.4915 0.02064 0.01116 -0.0064 0.4587 0.9896
4.000 0.5134 0.02154 0.01115 -0.0056 0.3226 0.9989
4.250 0.5199 0.02271 0.01170 -0.0032 0.2381 1.0000
4.500 0.5246 0.02370 0.01232 -0.0002 0.1981 1.0000
4.750 0.5306 0.02446 0.01292 0.0027 0.1752 1.0000
5.000 0.5374 0.02518 0.01350 0.0056 0.1618 1.0000
5.250 0.5464 0.02589 0.01413 0.0083 0.1523 1.0000
5.500 0.5592 0.02661 0.01482 0.0105 0.1449 1.0000
5.750 0.5753 0.02740 0.01555 0.0122 0.1384 1.0000
6.000 0.5946 0.02827 0.01634 0.0134 0.1333 1.0000
6.250 0.6170 0.02909 0.01726 0.0143 0.1273 1.0000
6.500 0.6392 0.02999 0.01810 0.0151 0.1215 1.0000
6.750 0.6634 0.03103 0.01909 0.0157 0.1170 1.0000
7.000 0.6890 0.03215 0.02038 0.0161 0.1136 1.0000
7.250 0.7143 0.03341 0.02175 0.0166 0.1108 1.0000
7.500 0.7388 0.03478 0.02321 0.0170 0.1083 1.0000
7.750 0.7627 0.03627 0.02477 0.0174 0.1063 1.0000
8.000 0.7863 0.03793 0.02649 0.0177 0.1043 1.0000
8.250 0.8064 0.03977 0.02855 0.0183 0.1021 1.0000
8.500 0.8231 0.04164 0.03077 0.0193 0.0993 1.0000
8.750 0.8394 0.04354 0.03293 0.0201 0.0965 1.0000
9.000 0.8551 0.04569 0.03531 0.0209 0.0949 1.0000
9.250 0.8693 0.04801 0.03785 0.0218 0.0937 1.0000
9.500 0.8815 0.05049 0.04058 0.0226 0.0927 1.0000
9.750 0.8919 0.05313 0.04343 0.0235 0.0917 1.0000
10.000 0.9009 0.05598 0.04645 0.0243 0.0909 1.0000
10.250 0.9003 0.05924 0.04999 0.0255 0.0901 1.0000
10.500 0.8875 0.06291 0.05403 0.0270 0.0895 1.0000
10.750 0.8671 0.06677 0.05817 0.0284 0.0890 1.0000
11.000 0.8410 0.07100 0.06260 0.0291 0.0888 1.0000
11.250 0.8114 0.07636 0.06812 0.0278 0.0889 1.0000
11.500 0.7796 0.08316 0.07504 0.0244 0.0892 1.0000
11.750 0.7448 0.09203 0.08397 0.0188 0.0896 1.0000
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Polar data table (+)
Polar graphs
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