EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 748 AIRFOIL (e748-il) Reynolds number: 50,000 Max Cl/Cd: 12.37 at α=-2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e748-il-50000.txt Download as CSV file: xf-e748-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 748 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2847 0.11799 0.11135 -0.0431 1.0000 0.1756
-10.250 -0.3199 0.11008 0.10359 -0.0461 1.0000 0.1627
-10.000 -0.4839 0.08268 0.07646 -0.0606 1.0000 0.1343
-9.750 -0.5180 0.07808 0.07197 -0.0600 1.0000 0.1332
-9.500 -0.5577 0.07421 0.06820 -0.0585 1.0000 0.1314
-9.250 -0.6109 0.07079 0.06487 -0.0564 1.0000 0.1289
-9.000 -0.6996 0.06305 0.05679 -0.0610 1.0000 0.1232
-8.750 -0.7184 0.05926 0.05275 -0.0618 1.0000 0.1233
-8.500 -0.7208 0.05667 0.05005 -0.0614 1.0000 0.1249
-8.250 -0.7205 0.05401 0.04722 -0.0615 1.0000 0.1269
-8.000 -0.7168 0.05131 0.04426 -0.0621 1.0000 0.1299
-7.750 -0.7090 0.04826 0.04065 -0.0640 1.0000 0.1344
-7.500 -0.6901 0.04716 0.03986 -0.0635 0.9970 0.1424
-7.250 -0.6460 0.04513 0.03778 -0.0683 0.9850 0.1582
-7.000 -0.6064 0.04310 0.03581 -0.0725 0.9733 0.1832
-6.750 -0.5704 0.04205 0.03532 -0.0752 0.9610 0.2226
-6.500 -0.5346 0.04519 0.03927 -0.0730 0.9467 0.2709
-6.250 -0.4908 0.05319 0.04751 -0.0663 0.9314 0.3095
-6.000 -0.4155 0.06812 0.06241 -0.0512 0.9162 0.3317
-5.750 -0.3837 0.07033 0.06447 -0.0494 0.9031 0.3604
-5.500 -0.3528 0.07203 0.06600 -0.0476 0.8912 0.3890
-5.250 -0.2933 0.07425 0.06797 -0.0467 0.8819 0.4249
-5.000 -0.2957 0.07349 0.06714 -0.0450 0.8689 0.4456
-4.750 -0.1492 0.07743 0.07069 -0.0438 0.8634 0.5335
-4.500 -0.1754 0.07628 0.06954 -0.0402 0.8504 0.5344
-4.250 -0.1803 0.07602 0.06926 -0.0367 0.8394 0.5593
-3.250 0.5238 0.04548 0.03689 -0.1253 0.8297 1.0000
-3.000 0.5336 0.04543 0.03679 -0.1246 0.8160 1.0000
-2.750 0.5547 0.04483 0.03610 -0.1260 0.8055 1.0000
-2.500 -0.1451 0.07046 0.06316 -0.0239 0.7784 0.6674
-2.250 -0.1417 0.06923 0.06183 -0.0243 0.7718 0.6673
-2.000 -0.1611 0.06892 0.06152 -0.0210 0.7644 0.6645
-1.750 -0.1511 0.06781 0.06028 -0.0232 0.7584 0.6675
-1.500 -0.1452 0.06738 0.05979 -0.0216 0.7522 0.6723
-1.250 -0.1510 0.06716 0.05953 -0.0207 0.7461 0.6736
-1.000 -0.1310 0.06662 0.05887 -0.0224 0.7405 0.6780
-0.750 -0.1101 0.06630 0.05842 -0.0251 0.7352 0.6820
-0.500 -0.1119 0.06658 0.05865 -0.0256 0.7305 0.6830
-0.250 -0.0913 0.06664 0.05859 -0.0292 0.7251 0.6858
0.000 -0.0618 0.06641 0.05827 -0.0306 0.7200 0.6902
0.250 -0.0485 0.06695 0.05873 -0.0321 0.7167 0.6921
0.500 -0.0429 0.06774 0.05948 -0.0331 0.7143 0.6937
0.750 -0.0308 0.06855 0.06024 -0.0350 0.7124 0.6957
1.000 -0.0151 0.06957 0.06120 -0.0376 0.7125 0.6976
1.250 0.0042 0.07079 0.06236 -0.0408 0.7144 0.6995
1.500 0.0279 0.07218 0.06367 -0.0446 0.7162 0.7018
1.750 -0.0752 0.07640 0.06830 -0.0396 0.8457 0.6980
2.000 -0.0548 0.07668 0.06851 -0.0420 0.8346 0.7005
2.250 -0.0102 0.07923 0.07091 -0.0485 0.8282 0.7032
2.500 0.0072 0.07939 0.07103 -0.0503 0.8158 0.7047
2.750 0.0442 0.08195 0.07351 -0.0540 0.8104 0.7080
3.000 0.0509 0.08171 0.07326 -0.0538 0.7989 0.7099
3.250 0.0968 0.08494 0.07640 -0.0593 0.7925 0.7132
3.500 0.1031 0.08472 0.07615 -0.0593 0.7800 0.7144
3.750 0.1524 0.08840 0.07973 -0.0655 0.7740 0.7180
4.000 0.1553 0.08815 0.07947 -0.0653 0.7619 0.7200
4.250 0.2013 0.09170 0.08295 -0.0706 0.7558 0.7239
4.500 0.2023 0.09155 0.08281 -0.0697 0.7432 0.7256
4.750 0.2473 0.09526 0.08648 -0.0743 0.7372 0.7293
5.000 0.2462 0.09515 0.08639 -0.0736 0.7253 0.7309
5.250 0.2905 0.09885 0.09003 -0.0784 0.7191 0.7356
5.500 0.2931 0.09925 0.09043 -0.0784 0.7067 0.7382
5.750 0.3357 0.10299 0.09414 -0.0824 0.7005 0.7434
6.000 0.3318 0.10317 0.09435 -0.0814 0.6892 0.7458
6.250 0.3703 0.10661 0.09777 -0.0849 0.6826 0.7512
6.500 0.3721 0.10749 0.09867 -0.0849 0.6715 0.7541
6.750 0.4117 0.11107 0.10222 -0.0888 0.6643 0.7595
7.000 0.4100 0.11195 0.10315 -0.0881 0.6544 0.7627
7.250 0.4406 0.11488 0.10609 -0.0905 0.6468 0.7695
7.500 0.4474 0.11671 0.10794 -0.0913 0.6380 0.7746
7.750 0.4731 0.11922 0.11049 -0.0928 0.6290 0.7816
8.000 0.4859 0.12177 0.11308 -0.0939 0.6229 0.7881
8.250 0.5020 0.12368 0.11503 -0.0952 0.6122 0.7950
8.500 0.5432 0.12856 0.11997 -0.0982 0.6077 0.8064
8.750 0.5308 0.12825 0.11971 -0.0974 0.5954 0.8108
9.000 0.5652 0.13227 0.12380 -0.0993 0.5901 0.8249
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Polar data table (+)
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