E71 (5.15%) (e71-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E71 (5.15%) (e71-il) Reynolds number: 200,000 Max Cl/Cd: 103.48 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e71-il-200000-n5.txt Download as CSV file: xf-e71-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E71 (5.15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3794 0.10452 0.10112 -0.0218 1.0000 0.0134
-7.500 -0.3826 0.10235 0.09900 -0.0206 1.0000 0.0134
-7.250 -0.3874 0.10034 0.09704 -0.0191 1.0000 0.0134
-7.000 -0.3840 0.09755 0.09428 -0.0200 0.9986 0.0134
-6.750 -0.3713 0.09147 0.08825 -0.0250 0.9953 0.0138
-6.500 -0.3571 0.08709 0.08386 -0.0278 0.9925 0.0144
-6.250 -0.3421 0.08403 0.08081 -0.0293 0.9895 0.0159
-6.000 -0.3205 0.08035 0.07712 -0.0346 0.9856 0.0182
-5.750 -0.2742 0.07534 0.07207 -0.0514 0.9807 0.0226
-5.500 -0.2446 0.07050 0.06719 -0.0597 0.9758 0.0228
-5.250 -0.2216 0.06359 0.06027 -0.0671 0.9724 0.0236
-5.000 -0.2002 0.06038 0.05705 -0.0694 0.9703 0.0252
-4.750 -0.1741 0.05676 0.05338 -0.0743 0.9657 0.0270
-3.750 0.0249 0.03312 0.02879 -0.1162 0.9584 0.0307
-3.500 0.0852 0.02589 0.02075 -0.1253 0.9589 0.0216
-3.250 0.1303 0.02237 0.01664 -0.1304 0.9586 0.0203
-3.000 0.1727 0.01981 0.01354 -0.1340 0.9582 0.0193
-2.750 0.2124 0.01798 0.01125 -0.1367 0.9575 0.0186
-2.500 0.2461 0.01666 0.00962 -0.1379 0.9549 0.0182
-2.250 0.2789 0.01564 0.00840 -0.1389 0.9519 0.0181
-2.000 0.3135 0.01479 0.00742 -0.1404 0.9495 0.0183
-1.750 0.3493 0.01412 0.00662 -0.1421 0.9474 0.0189
-1.500 0.3861 0.01360 0.00599 -0.1440 0.9455 0.0203
-1.250 0.4173 0.01326 0.00555 -0.1447 0.9411 0.0223
-1.000 0.4501 0.01292 0.00521 -0.1457 0.9368 0.0326
-0.750 0.4864 0.01251 0.00490 -0.1475 0.9338 0.0717
-0.500 0.5253 0.01181 0.00480 -0.1503 0.9318 0.2627
-0.250 0.5543 0.01149 0.00475 -0.1506 0.9245 0.3715
0.000 0.5904 0.01095 0.00469 -0.1524 0.9208 0.5445
0.500 0.6409 0.00982 0.00435 -0.1502 0.9077 1.0000
0.750 0.6727 0.00972 0.00421 -0.1508 0.8995 1.0000
1.000 0.7106 0.00954 0.00399 -0.1526 0.8928 1.0000
1.250 0.7434 0.00945 0.00391 -0.1534 0.8821 1.0000
1.500 0.7786 0.00933 0.00377 -0.1546 0.8705 1.0000
1.750 0.8153 0.00919 0.00363 -0.1562 0.8564 1.0000
2.000 0.8526 0.00908 0.00351 -0.1578 0.8396 1.0000
2.250 0.8867 0.00906 0.00352 -0.1588 0.8179 1.0000
2.500 0.9204 0.00908 0.00349 -0.1597 0.7893 1.0000
2.750 0.9512 0.00921 0.00353 -0.1599 0.7532 1.0000
3.000 0.9789 0.00946 0.00363 -0.1595 0.7081 1.0000
3.250 1.0032 0.00987 0.00380 -0.1584 0.6504 1.0000
3.500 1.0243 0.01045 0.00407 -0.1567 0.5810 1.0000
3.750 1.0357 0.01177 0.00462 -0.1534 0.4368 1.0000
4.000 1.0469 0.01344 0.00532 -0.1507 0.2743 1.0000
4.250 1.0672 0.01438 0.00589 -0.1495 0.2014 1.0000
4.500 1.0885 0.01525 0.00649 -0.1485 0.1425 1.0000
4.750 1.1086 0.01635 0.00723 -0.1474 0.0779 1.0000
5.000 1.1282 0.01758 0.00813 -0.1460 0.0246 1.0000
5.250 1.1494 0.01861 0.00907 -0.1448 0.0107 1.0000
5.500 1.1716 0.01952 0.01012 -0.1436 0.0089 1.0000
5.750 1.1939 0.02041 0.01120 -0.1425 0.0084 1.0000
6.000 1.2153 0.02143 0.01252 -0.1412 0.0081 1.0000
6.250 1.2353 0.02265 0.01393 -0.1396 0.0078 1.0000
6.500 1.2544 0.02407 0.01553 -0.1380 0.0076 1.0000
6.750 1.2733 0.02570 0.01734 -0.1363 0.0075 1.0000
7.000 1.2926 0.02758 0.01941 -0.1346 0.0074 1.0000
7.250 1.3128 0.02974 0.02180 -0.1331 0.0073 1.0000
7.500 1.3333 0.03225 0.02460 -0.1316 0.0073 1.0000
7.750 1.3527 0.03471 0.02740 -0.1300 0.0068 1.0000
8.000 1.3701 0.03708 0.03012 -0.1283 0.0061 1.0000
8.250 1.3849 0.03961 0.03301 -0.1263 0.0055 1.0000
8.500 1.3958 0.04312 0.03706 -0.1237 0.0053 1.0000
8.750 1.4021 0.04706 0.04149 -0.1207 0.0053 1.0000
9.000 1.4031 0.05128 0.04619 -0.1172 0.0053 1.0000
9.250 1.3978 0.05585 0.05122 -0.1133 0.0052 1.0000
9.500 1.3860 0.06025 0.05600 -0.1089 0.0053 1.0000
9.750 1.3685 0.06437 0.06043 -0.1043 0.0053 1.0000
10.000 1.3490 0.06886 0.06520 -0.1007 0.0053 1.0000
10.250 1.3281 0.07384 0.07044 -0.0983 0.0054 1.0000
10.500 1.3069 0.07936 0.07619 -0.0976 0.0054 1.0000
10.750 1.2844 0.08576 0.08280 -0.0986 0.0055 1.0000
11.000 1.2622 0.09314 0.09037 -0.1017 0.0055 1.0000
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Polar data table (+)
Polar graphs
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