Fage & Collins 1 (fg1-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 1 (fg1-il) Reynolds number: 50,000 Max Cl/Cd: 37.88 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg1-il-50000.txt Download as CSV file: xf-fg1-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 1
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4332 0.11211 0.10496 -0.0226 1.0000 0.1864
-9.000 -0.4090 0.10638 0.09920 -0.0202 1.0000 0.1994
-8.750 -0.4345 0.10648 0.09949 -0.0210 1.0000 0.2022
-8.500 -0.4130 0.10140 0.09439 -0.0188 1.0000 0.2159
-8.250 -0.4116 0.09824 0.09132 -0.0177 1.0000 0.2231
-8.000 -0.4233 0.09682 0.09003 -0.0164 1.0000 0.2323
-7.750 -0.4157 0.09328 0.08654 -0.0146 1.0000 0.2423
-7.500 -0.4434 0.09288 0.08632 -0.0140 1.0000 0.2495
-7.250 -0.4325 0.08924 0.08272 -0.0112 1.0000 0.2631
-7.000 -0.4311 0.08636 0.07991 -0.0090 1.0000 0.2763
-6.750 -0.4338 0.08386 0.07749 -0.0068 1.0000 0.2903
-6.500 -0.4368 0.08148 0.07519 -0.0044 1.0000 0.3063
-6.250 -0.4414 0.07931 0.07310 -0.0018 1.0000 0.3255
-6.000 -0.4577 0.07805 0.07193 -0.0004 1.0000 0.3456
-5.750 -0.4457 0.07477 0.06873 0.0051 1.0000 0.3744
-5.500 -0.4525 0.07299 0.06703 0.0094 1.0000 0.4086
-5.250 0.0026 0.04855 0.04124 -0.0278 1.0000 1.0000
-5.000 0.0107 0.04672 0.03949 -0.0279 1.0000 1.0000
-4.750 0.0186 0.04498 0.03782 -0.0278 1.0000 1.0000
-4.500 0.0136 0.04405 0.03702 -0.0245 1.0000 0.9949
-4.250 -0.0482 0.04602 0.03929 -0.0081 1.0000 0.9571
-4.000 -0.1057 0.04717 0.04070 0.0054 1.0000 0.9175
-3.750 -0.1613 0.04763 0.04142 0.0169 1.0000 0.8742
-3.500 -0.2157 0.04781 0.04183 0.0274 1.0000 0.8415
-3.250 -0.2702 0.04748 0.04174 0.0371 1.0000 0.8106
-3.000 -0.3250 0.04690 0.04138 0.0473 1.0000 0.7933
-2.750 -0.3780 0.04580 0.04048 0.0566 1.0000 0.7775
-2.500 -0.3963 0.04190 0.03636 0.0354 1.0000 0.6190
-2.250 -0.2199 0.03560 0.02654 -0.0140 1.0000 0.2139
-2.000 -0.1937 0.03393 0.02438 -0.0134 1.0000 0.1925
-1.750 -0.1687 0.03261 0.02261 -0.0124 1.0000 0.1767
-1.500 -0.1449 0.03158 0.02117 -0.0113 1.0000 0.1661
-1.250 -0.1213 0.03061 0.01982 -0.0101 1.0000 0.1572
-1.000 -0.0984 0.02989 0.01883 -0.0090 1.0000 0.1524
-0.750 -0.0753 0.02905 0.01786 -0.0083 1.0000 0.1491
-0.500 -0.0523 0.02843 0.01707 -0.0075 1.0000 0.1463
-0.250 -0.0299 0.02800 0.01651 -0.0067 1.0000 0.1468
0.000 -0.0028 0.02775 0.01612 -0.0069 1.0000 0.1486
0.250 0.0227 0.02761 0.01589 -0.0069 1.0000 0.1511
0.500 0.0460 0.02759 0.01580 -0.0067 1.0000 0.1526
0.750 0.0666 0.02776 0.01590 -0.0063 1.0000 0.1544
1.000 0.0869 0.02793 0.01613 -0.0062 1.0000 0.1586
1.250 0.1057 0.02834 0.01656 -0.0060 1.0000 0.1648
1.500 0.1638 0.02919 0.01763 -0.0132 0.9855 0.1957
1.750 0.2618 0.02840 0.01865 -0.0276 0.9666 1.0000
2.000 0.3209 0.02943 0.01937 -0.0343 0.9417 1.0000
2.250 0.3784 0.03023 0.02001 -0.0405 0.9167 1.0000
2.500 0.4416 0.03072 0.02045 -0.0471 0.8923 1.0000
2.750 0.4997 0.03063 0.02036 -0.0519 0.8629 1.0000
3.000 0.5626 0.02980 0.01962 -0.0564 0.8323 1.0000
3.500 0.6757 0.02757 0.01765 -0.0622 0.7752 1.0000
3.750 0.7309 0.02619 0.01642 -0.0645 0.7455 1.0000
4.000 0.7885 0.02464 0.01500 -0.0667 0.7113 1.0000
4.250 0.8316 0.02384 0.01419 -0.0669 0.6688 1.0000
4.500 0.8718 0.02353 0.01372 -0.0669 0.6201 1.0000
4.750 0.9053 0.02390 0.01384 -0.0663 0.5708 1.0000
5.000 0.9307 0.02483 0.01455 -0.0649 0.5262 1.0000
5.250 0.9536 0.02596 0.01553 -0.0634 0.4886 1.0000
5.500 0.9758 0.02710 0.01657 -0.0620 0.4573 1.0000
5.750 0.9995 0.02817 0.01753 -0.0608 0.4304 1.0000
6.000 1.0161 0.02929 0.01874 -0.0586 0.4059 1.0000
6.250 1.0390 0.03032 0.01965 -0.0573 0.3835 1.0000
6.500 1.0547 0.03149 0.02097 -0.0550 0.3623 1.0000
6.750 1.0741 0.03265 0.02217 -0.0533 0.3416 1.0000
7.000 1.0938 0.03388 0.02337 -0.0516 0.3210 1.0000
7.250 1.1077 0.03531 0.02497 -0.0491 0.3006 1.0000
7.500 1.1252 0.03671 0.02640 -0.0472 0.2801 1.0000
7.750 1.1417 0.03827 0.02795 -0.0451 0.2599 1.0000
8.000 1.1526 0.04013 0.03006 -0.0423 0.2415 1.0000
8.250 1.1652 0.04185 0.03186 -0.0397 0.2225 1.0000
8.500 1.1827 0.04349 0.03337 -0.0380 0.2031 1.0000
8.750 1.1920 0.04558 0.03556 -0.0352 0.1863 1.0000
9.000 1.1989 0.04779 0.03791 -0.0322 0.1710 1.0000
9.250 1.2074 0.05013 0.04035 -0.0296 0.1569 1.0000
9.500 1.1959 0.05341 0.04425 -0.0246 0.1504 1.0000
9.750 1.2021 0.05609 0.04699 -0.0221 0.1404 1.0000
10.000 1.1862 0.05980 0.05116 -0.0175 0.1369 1.0000
10.250 1.2017 0.06244 0.05369 -0.0162 0.1280 1.0000
10.500 1.1790 0.06642 0.05807 -0.0117 0.1271 1.0000
10.750 1.1534 0.07039 0.06231 -0.0074 0.1268 1.0000
11.000 1.1260 0.07453 0.06664 -0.0038 0.1270 1.0000
11.250 1.0998 0.07935 0.07161 -0.0019 0.1276 1.0000
11.500 1.0725 0.08486 0.07724 -0.0014 0.1282 1.0000
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Polar data table (+)
Polar graphs
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