GOE 445 AIRFOIL (goe445-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 445 AIRFOIL (goe445-il) Reynolds number: 50,000 Max Cl/Cd: 19.11 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe445-il-50000-n5.txt Download as CSV file: xf-goe445-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 445 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5323 0.09962 0.09319 -0.0014 1.0000 0.0493
-9.250 -0.5407 0.09399 0.08760 -0.0053 1.0000 0.0429
-8.750 -0.6385 0.09453 0.08781 -0.0037 1.0000 0.0414
-8.500 -0.6397 0.08978 0.08312 -0.0064 1.0000 0.0398
-8.250 -0.6449 0.08466 0.07805 -0.0100 1.0000 0.0381
-8.000 -0.6524 0.07954 0.07291 -0.0129 1.0000 0.0364
-7.750 -0.6548 0.07479 0.06800 -0.0151 1.0000 0.0337
-7.500 -0.6532 0.07058 0.06372 -0.0154 1.0000 0.0329
-7.250 -0.6513 0.06632 0.05933 -0.0159 1.0000 0.0322
-7.000 -0.6478 0.06202 0.05483 -0.0161 1.0000 0.0319
-6.750 -0.6418 0.05786 0.05042 -0.0159 1.0000 0.0315
-6.500 -0.6335 0.05378 0.04601 -0.0154 1.0000 0.0314
-6.250 -0.6228 0.04988 0.04173 -0.0146 1.0000 0.0314
-6.000 -0.6097 0.04621 0.03762 -0.0135 1.0000 0.0314
-5.750 -0.5944 0.04268 0.03361 -0.0122 1.0000 0.0314
-5.500 -0.5767 0.03930 0.02972 -0.0108 1.0000 0.0312
-5.250 -0.5568 0.03613 0.02605 -0.0093 1.0000 0.0310
-5.000 -0.5346 0.03323 0.02265 -0.0079 1.0000 0.0310
-4.750 -0.5105 0.03061 0.01959 -0.0065 1.0000 0.0315
-4.500 -0.4849 0.02840 0.01686 -0.0052 1.0000 0.0337
-4.250 -0.4609 0.02628 0.01460 -0.0040 1.0000 0.0378
-4.000 -0.4367 0.02455 0.01264 -0.0025 1.0000 0.0412
-3.750 -0.4141 0.02296 0.01081 -0.0010 1.0000 0.0462
-3.500 -0.3914 0.02152 0.00921 0.0001 1.0000 0.0596
-3.250 -0.3693 0.01975 0.00753 0.0012 1.0000 0.0945
-3.000 -0.3175 0.01661 0.00797 0.0030 1.0000 0.9182
-2.750 -0.2616 0.01648 0.00706 -0.0023 1.0000 0.9508
-2.500 -0.1947 0.01624 0.00608 -0.0104 1.0000 0.9871
-2.250 -0.1565 0.01586 0.00533 -0.0135 1.0000 1.0000
-2.000 -0.1401 0.01558 0.00485 -0.0121 1.0000 1.0000
-1.750 -0.1232 0.01536 0.00445 -0.0107 1.0000 1.0000
-1.500 -0.1061 0.01517 0.00407 -0.0093 1.0000 1.0000
-1.250 -0.0887 0.01503 0.00379 -0.0078 1.0000 1.0000
-1.000 -0.0711 0.01491 0.00358 -0.0062 1.0000 1.0000
-0.750 -0.0534 0.01483 0.00342 -0.0047 1.0000 1.0000
-0.500 -0.0357 0.01477 0.00329 -0.0031 1.0000 1.0000
-0.250 -0.0179 0.01473 0.00322 -0.0016 1.0000 1.0000
0.000 0.0000 0.01472 0.00319 0.0000 1.0000 1.0000
0.250 0.0179 0.01474 0.00322 0.0016 1.0000 1.0000
0.500 0.0357 0.01477 0.00329 0.0031 1.0000 1.0000
0.750 0.0534 0.01483 0.00342 0.0047 1.0000 1.0000
1.000 0.0711 0.01492 0.00358 0.0062 1.0000 1.0000
1.250 0.0887 0.01503 0.00380 0.0078 1.0000 1.0000
1.500 0.1061 0.01518 0.00407 0.0093 1.0000 1.0000
1.750 0.1232 0.01536 0.00445 0.0107 1.0000 1.0000
2.000 0.1401 0.01558 0.00485 0.0122 1.0000 1.0000
2.250 0.1565 0.01586 0.00533 0.0135 1.0000 1.0000
2.500 0.1947 0.01624 0.00608 0.0104 0.9871 1.0000
2.750 0.2613 0.01648 0.00706 0.0024 0.9510 1.0000
3.000 0.3174 0.01661 0.00797 -0.0030 0.9182 1.0000
3.250 0.3695 0.01975 0.00753 -0.0013 0.0943 1.0000
3.500 0.3917 0.02155 0.00923 -0.0001 0.0592 1.0000
3.750 0.4143 0.02297 0.01082 0.0010 0.0460 1.0000
4.000 0.4370 0.02455 0.01264 0.0025 0.0411 1.0000
4.250 0.4611 0.02628 0.01460 0.0040 0.0378 1.0000
4.500 0.4851 0.02840 0.01686 0.0051 0.0336 1.0000
4.750 0.5106 0.03059 0.01956 0.0065 0.0315 1.0000
5.000 0.5347 0.03322 0.02264 0.0078 0.0310 1.0000
5.250 0.5569 0.03613 0.02604 0.0093 0.0310 1.0000
5.500 0.5768 0.03930 0.02972 0.0108 0.0312 1.0000
5.750 0.5945 0.04262 0.03353 0.0122 0.0316 1.0000
6.000 0.6098 0.04615 0.03756 0.0135 0.0315 1.0000
6.250 0.6228 0.04987 0.04172 0.0146 0.0314 1.0000
6.500 0.6335 0.05376 0.04600 0.0154 0.0314 1.0000
6.750 0.6420 0.05777 0.05032 0.0159 0.0316 1.0000
7.000 0.6477 0.06201 0.05483 0.0161 0.0318 1.0000
7.250 0.6516 0.06623 0.05924 0.0159 0.0324 1.0000
7.500 0.6535 0.07051 0.06366 0.0155 0.0330 1.0000
7.750 0.6550 0.07473 0.06794 0.0151 0.0338 1.0000
8.000 0.6532 0.07936 0.07273 0.0132 0.0361 1.0000
8.250 0.6452 0.08463 0.07802 0.0100 0.0383 1.0000
8.500 0.6398 0.08980 0.08314 0.0064 0.0397 1.0000
8.750 0.6380 0.09472 0.08800 0.0035 0.0412 1.0000
9.250 0.6365 0.10494 0.09811 -0.0031 0.0514 1.0000
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Polar data table (+)
Polar graphs
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