WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Reynolds number: 50,000 Max Cl/Cd: 19.64 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx71089a-il-50000-n5.txt Download as CSV file: xf-fx71089a-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 71-089A 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6722 0.09103 0.08268 -0.0065 1.0000 0.0925
-9.500 -0.6877 0.08343 0.07511 -0.0121 1.0000 0.0913
-9.250 -0.7168 0.07553 0.06718 -0.0172 1.0000 0.0901
-9.000 -0.7444 0.06919 0.06070 -0.0191 1.0000 0.0892
-8.750 -0.7612 0.06368 0.05496 -0.0198 1.0000 0.0886
-8.500 -0.7685 0.05901 0.05001 -0.0197 1.0000 0.0885
-8.250 -0.7691 0.05494 0.04562 -0.0192 1.0000 0.0885
-8.000 -0.7637 0.05159 0.04198 -0.0184 1.0000 0.0892
-7.750 -0.7547 0.04865 0.03875 -0.0175 1.0000 0.0904
-7.500 -0.7438 0.04582 0.03558 -0.0165 1.0000 0.0917
-7.250 -0.7308 0.04312 0.03252 -0.0155 1.0000 0.0929
-7.000 -0.7157 0.04058 0.02961 -0.0144 1.0000 0.0938
-6.750 -0.6983 0.03825 0.02692 -0.0133 1.0000 0.0946
-6.500 -0.6793 0.03616 0.02447 -0.0122 1.0000 0.0956
-6.250 -0.6587 0.03428 0.02222 -0.0112 1.0000 0.0967
-6.000 -0.6368 0.03277 0.02073 -0.0104 1.0000 0.0985
-5.750 -0.6147 0.03150 0.01942 -0.0095 1.0000 0.1011
-5.500 -0.5921 0.03023 0.01803 -0.0086 1.0000 0.1040
-5.250 -0.5687 0.02896 0.01659 -0.0076 1.0000 0.1069
-5.000 -0.5444 0.02776 0.01518 -0.0067 1.0000 0.1096
-4.750 -0.5209 0.02661 0.01412 -0.0058 1.0000 0.1125
-4.500 -0.4974 0.02563 0.01316 -0.0048 1.0000 0.1164
-4.250 -0.4736 0.02474 0.01219 -0.0038 1.0000 0.1225
-4.000 -0.4509 0.02384 0.01140 -0.0027 1.0000 0.1297
-3.750 -0.4277 0.02302 0.01056 -0.0017 1.0000 0.1397
-3.500 -0.4053 0.02215 0.00981 -0.0006 1.0000 0.1519
-3.250 -0.3830 0.02130 0.00910 0.0004 1.0000 0.1712
-3.000 -0.3614 0.02040 0.00846 0.0014 1.0000 0.2036
-2.750 -0.3422 0.01945 0.00796 0.0028 1.0000 0.2596
-2.500 -0.3254 0.01841 0.00759 0.0046 1.0000 0.3571
-2.250 -0.3105 0.01745 0.00743 0.0072 1.0000 0.4868
-2.000 -0.2944 0.01678 0.00749 0.0106 1.0000 0.6278
-1.750 -0.2689 0.01651 0.00774 0.0132 1.0000 0.7623
-1.500 -0.2245 0.01659 0.00794 0.0120 1.0000 0.8589
-1.250 -0.1626 0.01679 0.00804 0.0069 1.0000 0.9271
-1.000 -0.0856 0.01688 0.00795 -0.0019 1.0000 0.9751
-0.750 -0.0302 0.01670 0.00766 -0.0077 1.0000 1.0000
-0.500 -0.0203 0.01655 0.00750 -0.0052 1.0000 1.0000
-0.250 -0.0102 0.01647 0.00741 -0.0026 1.0000 1.0000
0.000 0.0000 0.01644 0.00738 0.0000 1.0000 1.0000
0.250 0.0102 0.01647 0.00741 0.0026 1.0000 1.0000
0.500 0.0203 0.01655 0.00750 0.0052 1.0000 1.0000
0.750 0.0302 0.01670 0.00766 0.0077 1.0000 1.0000
1.000 0.0856 0.01688 0.00795 0.0019 0.9751 1.0000
1.250 0.1623 0.01679 0.00804 -0.0068 0.9273 1.0000
1.500 0.2245 0.01659 0.00794 -0.0120 0.8589 1.0000
1.750 0.2689 0.01651 0.00774 -0.0132 0.7626 1.0000
2.000 0.2944 0.01678 0.00749 -0.0106 0.6279 1.0000
2.250 0.3105 0.01745 0.00743 -0.0073 0.4875 1.0000
2.500 0.3254 0.01840 0.00759 -0.0046 0.3573 1.0000
2.750 0.3422 0.01945 0.00795 -0.0028 0.2598 1.0000
3.000 0.3614 0.02040 0.00846 -0.0014 0.2035 1.0000
3.250 0.3830 0.02129 0.00909 -0.0004 0.1712 1.0000
3.500 0.4053 0.02215 0.00981 0.0006 0.1519 1.0000
3.750 0.4276 0.02302 0.01056 0.0017 0.1397 1.0000
4.000 0.4508 0.02384 0.01140 0.0028 0.1297 1.0000
4.250 0.4735 0.02473 0.01219 0.0038 0.1225 1.0000
4.500 0.4973 0.02562 0.01316 0.0048 0.1165 1.0000
4.750 0.5208 0.02661 0.01412 0.0058 0.1125 1.0000
5.000 0.5444 0.02776 0.01518 0.0067 0.1096 1.0000
5.250 0.5687 0.02896 0.01658 0.0076 0.1069 1.0000
5.500 0.5921 0.03023 0.01802 0.0086 0.1040 1.0000
5.750 0.6147 0.03149 0.01941 0.0095 0.1010 1.0000
6.000 0.6368 0.03277 0.02073 0.0104 0.0985 1.0000
6.250 0.6587 0.03427 0.02224 0.0112 0.0967 1.0000
6.500 0.6793 0.03616 0.02447 0.0122 0.0956 1.0000
6.750 0.6984 0.03825 0.02692 0.0133 0.0946 1.0000
7.000 0.7157 0.04058 0.02961 0.0143 0.0938 1.0000
7.250 0.7309 0.04312 0.03252 0.0154 0.0929 1.0000
7.500 0.7439 0.04582 0.03558 0.0165 0.0917 1.0000
7.750 0.7548 0.04864 0.03874 0.0175 0.0904 1.0000
8.000 0.7638 0.05158 0.04197 0.0184 0.0892 1.0000
8.250 0.7693 0.05495 0.04564 0.0192 0.0885 1.0000
8.500 0.7687 0.05901 0.05001 0.0197 0.0885 1.0000
8.750 0.7614 0.06370 0.05498 0.0198 0.0887 1.0000
9.000 0.7448 0.06919 0.06071 0.0190 0.0892 1.0000
9.250 0.7172 0.07555 0.06721 0.0171 0.0901 1.0000
9.500 0.6881 0.08349 0.07517 0.0119 0.0913 1.0000
9.750 0.6727 0.09108 0.08273 0.0064 0.0925 1.0000
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