Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 4 (fg4-il) Reynolds number: 50,000 Max Cl/Cd: 32.84 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg4-il-50000-n5.txt Download as CSV file: xf-fg4-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 4
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3528 0.10448 0.09829 -0.0182 1.0000 0.1366
-7.500 -0.3838 0.10406 0.09800 -0.0164 1.0000 0.1386
-7.250 -0.3971 0.10176 0.09571 -0.0227 0.9934 0.1410
-7.000 -0.3652 0.09686 0.09089 -0.0197 0.9910 0.1449
-6.500 -0.3391 0.08974 0.08372 -0.0297 0.9696 0.1615
-6.250 -0.3140 0.08628 0.08030 -0.0296 0.9633 0.1690
-6.000 -0.3069 0.08276 0.07673 -0.0341 0.9496 0.1815
-5.750 -0.2828 0.07948 0.07347 -0.0352 0.9420 0.1910
-5.500 -0.2695 0.07611 0.07007 -0.0372 0.9305 0.2040
-5.000 -0.2430 0.07057 0.06447 -0.0393 0.9078 0.2408
-4.750 -0.2193 0.06747 0.06140 -0.0400 0.9009 0.2624
-4.500 -0.1775 0.06004 0.05269 -0.0510 0.8865 0.1205
-4.250 -0.1593 0.05568 0.04777 -0.0505 0.8746 0.0914
-4.000 -0.1293 0.05276 0.04477 -0.0517 0.8682 0.0864
-3.750 -0.1156 0.05068 0.04249 -0.0500 0.8552 0.0846
-3.500 -0.0959 0.04861 0.04016 -0.0490 0.8447 0.0834
-3.250 -0.0721 0.04642 0.03761 -0.0484 0.8356 0.0811
-3.000 -0.0549 0.04520 0.03568 -0.0457 0.8231 0.0774
-2.750 -0.0239 0.04293 0.03329 -0.0463 0.8167 0.0762
-2.500 -0.0090 0.04163 0.03182 -0.0440 0.8040 0.0753
-2.250 0.0152 0.04015 0.03010 -0.0430 0.7947 0.0744
-2.000 0.0420 0.03870 0.02837 -0.0423 0.7858 0.0735
-1.750 0.0656 0.03757 0.02700 -0.0411 0.7755 0.0728
-1.500 0.0995 0.03612 0.02527 -0.0413 0.7681 0.0722
-1.250 0.1251 0.03519 0.02411 -0.0404 0.7575 0.0729
-1.000 0.1645 0.03393 0.02260 -0.0415 0.7504 0.0746
-0.750 0.1936 0.03321 0.02166 -0.0412 0.7397 0.0759
-0.500 0.2406 0.03190 0.02016 -0.0437 0.7325 0.0767
-0.250 0.2833 0.03111 0.01919 -0.0459 0.7218 0.0774
0.000 0.3484 0.02969 0.01771 -0.0521 0.7142 0.0795
0.250 0.3845 0.02915 0.01712 -0.0533 0.7026 0.0821
0.500 0.4349 0.02829 0.01612 -0.0568 0.6940 0.0879
0.750 0.4625 0.02808 0.01585 -0.0565 0.6811 0.0921
1.000 0.5095 0.02743 0.01512 -0.0596 0.6711 0.0990
1.250 0.5408 0.02724 0.01489 -0.0599 0.6581 0.1080
1.500 0.5751 0.02693 0.01476 -0.0611 0.6452 0.1401
1.750 0.7337 0.02505 0.01456 -0.0872 0.6257 1.0000
2.000 0.7598 0.02521 0.01450 -0.0865 0.6108 1.0000
2.250 0.7844 0.02536 0.01443 -0.0855 0.5945 1.0000
2.500 0.8061 0.02553 0.01441 -0.0839 0.5772 1.0000
2.750 0.8246 0.02574 0.01445 -0.0817 0.5590 1.0000
3.000 0.8410 0.02606 0.01464 -0.0793 0.5423 1.0000
3.250 0.8557 0.02640 0.01488 -0.0767 0.5255 1.0000
3.500 0.8706 0.02676 0.01515 -0.0741 0.5091 1.0000
3.750 0.8858 0.02714 0.01543 -0.0717 0.4936 1.0000
4.000 0.9004 0.02750 0.01569 -0.0691 0.4777 1.0000
4.250 0.9145 0.02787 0.01596 -0.0665 0.4624 1.0000
4.500 0.9284 0.02827 0.01630 -0.0639 0.4485 1.0000
4.750 0.9387 0.02875 0.01674 -0.0608 0.4338 1.0000
5.000 0.9512 0.02923 0.01718 -0.0582 0.4205 1.0000
5.250 0.9647 0.02968 0.01758 -0.0557 0.4078 1.0000
5.500 0.9775 0.03018 0.01801 -0.0531 0.3950 1.0000
5.750 0.9883 0.03077 0.01858 -0.0504 0.3818 1.0000
6.000 1.0008 0.03135 0.01911 -0.0480 0.3701 1.0000
6.250 1.0139 0.03193 0.01964 -0.0458 0.3594 1.0000
6.500 1.0256 0.03265 0.02040 -0.0435 0.3488 1.0000
6.750 1.0383 0.03330 0.02098 -0.0413 0.3391 1.0000
7.000 1.0492 0.03411 0.02184 -0.0391 0.3293 1.0000
7.250 1.0598 0.03488 0.02259 -0.0368 0.3195 1.0000
7.500 1.0687 0.03578 0.02353 -0.0344 0.3091 1.0000
7.750 1.0774 0.03672 0.02449 -0.0322 0.2994 1.0000
8.000 1.0850 0.03772 0.02549 -0.0299 0.2893 1.0000
8.250 1.0928 0.03884 0.02670 -0.0278 0.2805 1.0000
8.500 1.1011 0.03995 0.02789 -0.0259 0.2727 1.0000
8.750 1.1081 0.04120 0.02922 -0.0240 0.2645 1.0000
9.000 1.1134 0.04257 0.03066 -0.0221 0.2556 1.0000
9.250 1.1162 0.04414 0.03231 -0.0201 0.2451 1.0000
9.500 1.1190 0.04576 0.03394 -0.0183 0.2354 1.0000
9.750 1.1195 0.04773 0.03604 -0.0168 0.2240 1.0000
10.000 1.1191 0.04983 0.03819 -0.0153 0.2123 1.0000
10.250 1.1174 0.05213 0.04053 -0.0141 0.2003 1.0000
10.500 1.1175 0.05454 0.04307 -0.0132 0.1903 1.0000
10.750 1.1152 0.05722 0.04584 -0.0124 0.1788 1.0000
11.000 1.1127 0.06003 0.04869 -0.0118 0.1686 1.0000
11.250 1.1092 0.06308 0.05179 -0.0114 0.1582 1.0000
11.500 1.1039 0.06645 0.05520 -0.0111 0.1471 1.0000
11.750 1.0997 0.06975 0.05852 -0.0110 0.1401 1.0000
12.000 1.0948 0.07327 0.06210 -0.0110 0.1327 1.0000
12.250 1.0889 0.07695 0.06576 -0.0111 0.1265 1.0000
12.500 1.0851 0.08050 0.06938 -0.0114 0.1219 1.0000
12.750 1.0813 0.08408 0.07299 -0.0117 0.1184 1.0000
13.250 1.0757 0.09112 0.08009 -0.0124 0.1127 1.0000
13.500 1.0734 0.09470 0.08377 -0.0128 0.1101 1.0000
13.750 1.0722 0.09816 0.08731 -0.0133 0.1082 1.0000
14.000 1.0716 0.10151 0.09071 -0.0138 0.1066 1.0000
14.250 1.0719 0.10473 0.09399 -0.0143 0.1050 1.0000
14.500 1.0740 0.10761 0.09689 -0.0147 0.1037 1.0000
14.750 1.0720 0.11149 0.10089 -0.0156 0.1026 1.0000
15.000 1.0675 0.11594 0.10552 -0.0168 0.1018 1.0000
15.250 1.0575 0.12156 0.11134 -0.0186 0.1006 1.0000
15.500 1.0425 0.12844 0.11843 -0.0211 0.1000 1.0000
15.750 1.0041 0.14098 0.13122 -0.0265 0.0990 1.0000
16.000 0.9539 0.15796 0.14827 -0.0340 0.0982 1.0000
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Polar data table (+)
Polar graphs
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