EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 49 AIRFOIL (e49-il) Reynolds number: 200,000 Max Cl/Cd: 82.29 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e49-il-200000.txt Download as CSV file: xf-e49-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 49 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4131 0.12974 0.12666 -0.0114 1.0000 0.0172
-8.250 -0.4197 0.12843 0.12539 -0.0107 1.0000 0.0173
-8.000 -0.4259 0.12681 0.12381 -0.0094 1.0000 0.0173
-7.750 -0.4300 0.12522 0.12225 -0.0092 0.9992 0.0174
-7.500 -0.4186 0.12281 0.11985 -0.0137 0.9964 0.0175
-7.000 -0.4109 0.11249 0.10956 -0.0140 0.9932 0.0184
-6.750 -0.4022 0.10874 0.10581 -0.0139 0.9902 0.0190
-6.500 -0.3886 0.10540 0.10247 -0.0166 0.9871 0.0195
-6.250 -0.3729 0.10257 0.09964 -0.0204 0.9850 0.0201
-6.000 -0.3684 0.09921 0.09629 -0.0212 0.9805 0.0205
-5.750 -0.3475 0.09560 0.09267 -0.0264 0.9764 0.0213
-5.500 -0.3187 0.09224 0.08928 -0.0335 0.9741 0.0224
-5.250 -0.3105 0.08858 0.08562 -0.0351 0.9684 0.0230
-5.000 -0.2754 0.08431 0.08130 -0.0435 0.9643 0.0243
-4.750 -0.2252 0.08024 0.07714 -0.0555 0.9623 0.0263
-4.500 -0.1730 0.07580 0.07256 -0.0680 0.9547 0.0281
-4.250 -0.1050 0.07101 0.06751 -0.0821 0.9518 0.0285
-4.000 -0.0862 0.06407 0.06061 -0.0855 0.9436 0.0304
-3.750 -0.0456 0.06065 0.05712 -0.0913 0.9355 0.0357
-3.500 0.0443 0.05653 0.05243 -0.1075 0.9316 0.0419
-3.250 0.0840 0.05081 0.04669 -0.1145 0.9299 0.0445
-3.000 0.1308 0.04833 0.04406 -0.1206 0.9283 0.0501
-2.750 0.1795 0.04462 0.03992 -0.1268 0.9213 0.0587
-2.500 0.2279 0.04239 0.03732 -0.1324 0.9191 0.0721
-2.250 0.2707 0.04062 0.03541 -0.1369 0.9174 0.0875
-1.250 0.4398 0.03392 0.02705 -0.1476 0.9056 0.0626
-1.000 0.4708 0.03299 0.02582 -0.1477 0.8996 0.0500
-0.750 0.5066 0.03230 0.02486 -0.1487 0.8959 0.0438
-0.500 0.5450 0.03183 0.02431 -0.1507 0.8937 0.0426
-0.250 0.5857 0.03113 0.02364 -0.1533 0.8923 0.0458
0.000 0.6091 0.03076 0.02330 -0.1528 0.8837 0.0517
0.250 0.6485 0.03043 0.02287 -0.1550 0.8812 0.0560
0.500 0.6883 0.02852 0.02303 -0.1577 0.8802 1.0000
0.750 0.7134 0.02835 0.02266 -0.1572 0.8713 1.0000
1.000 0.7547 0.02795 0.02211 -0.1596 0.8683 1.0000
1.250 0.7826 0.02764 0.02175 -0.1597 0.8601 1.0000
1.500 0.8206 0.02717 0.02123 -0.1615 0.8563 1.0000
1.750 0.8609 0.02668 0.02070 -0.1638 0.8542 1.0000
2.000 0.8831 0.02651 0.02053 -0.1628 0.8445 1.0000
2.250 0.9222 0.02593 0.01995 -0.1649 0.8419 1.0000
2.500 0.9460 0.02571 0.01980 -0.1641 0.8326 1.0000
2.750 0.9846 0.02497 0.01909 -0.1659 0.8293 1.0000
3.000 1.0115 0.02444 0.01861 -0.1655 0.8196 1.0000
3.250 1.0520 0.02329 0.01753 -0.1673 0.8155 1.0000
3.500 1.0772 0.02280 0.01716 -0.1665 0.8049 1.0000
3.750 1.1144 0.02176 0.01621 -0.1677 0.8010 1.0000
4.000 1.1382 0.02134 0.01589 -0.1667 0.7891 1.0000
4.250 1.1658 0.02078 0.01544 -0.1663 0.7770 1.0000
4.500 1.1990 0.02001 0.01478 -0.1669 0.7640 1.0000
4.750 1.2593 0.01759 0.01239 -0.1716 0.7270 1.0000
5.000 1.3298 0.01616 0.01042 -0.1789 0.6243 1.0000
5.250 1.3298 0.01739 0.01101 -0.1732 0.5182 1.0000
5.500 1.3191 0.01921 0.01212 -0.1661 0.4120 1.0000
5.750 1.3158 0.02095 0.01331 -0.1607 0.3228 1.0000
6.000 1.3131 0.02301 0.01464 -0.1559 0.2129 1.0000
6.500 1.3144 0.02778 0.01810 -0.1478 0.0242 1.0000
6.750 1.3294 0.02886 0.01934 -0.1457 0.0213 1.0000
7.000 1.3429 0.03008 0.02074 -0.1435 0.0196 1.0000
7.250 1.3536 0.03151 0.02235 -0.1409 0.0187 1.0000
7.500 1.3613 0.03321 0.02421 -0.1378 0.0182 1.0000
7.750 1.3670 0.03516 0.02630 -0.1346 0.0177 1.0000
8.000 1.3706 0.03789 0.02915 -0.1312 0.0167 1.0000
8.250 1.3850 0.03926 0.03063 -0.1295 0.0159 1.0000
8.500 1.4024 0.04128 0.03283 -0.1280 0.0156 1.0000
8.750 1.4316 0.04373 0.03543 -0.1281 0.0156 1.0000
9.000 1.5116 0.04997 0.04204 -0.1358 0.0168 1.0000
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Polar data table (+)
Polar graphs
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