WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Reynolds number: 200,000 Max Cl/Cd: 31.29 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx71089a-il-200000.txt Download as CSV file: xf-fx71089a-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6366 0.09878 0.09464 0.0022 1.0000 0.1015
-9.750 -0.6349 0.09522 0.09109 0.0009 1.0000 0.1040
-9.500 -0.7646 0.08059 0.07637 -0.0192 1.0000 0.1096
-9.250 -0.7462 0.07465 0.07055 -0.0190 1.0000 0.1111
-9.000 -0.7178 0.07320 0.06916 -0.0171 1.0000 0.1122
-8.750 -0.7079 0.07094 0.06692 -0.0160 1.0000 0.1134
-8.500 -0.7046 0.06803 0.06399 -0.0159 1.0000 0.1151
-8.250 -0.7612 0.06341 0.05865 -0.0179 1.0000 0.1240
-8.000 -0.7986 0.04110 0.03519 -0.0175 1.0000 0.0834
-7.750 -0.7867 0.03739 0.03130 -0.0163 1.0000 0.0811
-7.500 -0.7860 0.03124 0.02413 -0.0132 1.0000 0.0756
-7.250 -0.7677 0.02938 0.02191 -0.0116 1.0000 0.0749
-7.000 -0.7477 0.02772 0.02002 -0.0103 1.0000 0.0747
-6.750 -0.7273 0.02595 0.01808 -0.0091 1.0000 0.0749
-6.500 -0.7060 0.02438 0.01639 -0.0081 1.0000 0.0755
-6.250 -0.6839 0.02309 0.01500 -0.0070 1.0000 0.0761
-6.000 -0.6614 0.02190 0.01370 -0.0059 1.0000 0.0765
-5.750 -0.6385 0.02082 0.01254 -0.0049 1.0000 0.0770
-5.500 -0.6153 0.01985 0.01151 -0.0038 1.0000 0.0775
-5.250 -0.5921 0.01898 0.01059 -0.0028 1.0000 0.0783
-5.000 -0.5689 0.01818 0.00975 -0.0017 1.0000 0.0792
-4.750 -0.5457 0.01744 0.00899 -0.0006 1.0000 0.0803
-4.500 -0.5227 0.01680 0.00832 0.0005 1.0000 0.0817
-4.250 -0.4999 0.01623 0.00773 0.0017 1.0000 0.0835
-4.000 -0.4771 0.01571 0.00719 0.0030 1.0000 0.0849
-3.750 -0.4561 0.01485 0.00643 0.0043 1.0000 0.0871
-3.500 -0.4346 0.01432 0.00597 0.0057 1.0000 0.0895
-3.250 -0.4131 0.01387 0.00557 0.0071 1.0000 0.0925
-3.000 -0.3916 0.01349 0.00519 0.0085 1.0000 0.0963
-2.750 -0.3714 0.01296 0.00478 0.0100 1.0000 0.1021
-2.500 -0.3506 0.01255 0.00445 0.0114 1.0000 0.1127
-2.250 -0.3311 0.01195 0.00408 0.0130 1.0000 0.1413
-2.000 -0.3134 0.01112 0.00382 0.0147 1.0000 0.2369
-1.750 -0.2959 0.01047 0.00372 0.0163 1.0000 0.3469
-1.500 -0.2795 0.00991 0.00373 0.0183 1.0000 0.4671
-0.750 -0.2151 0.00897 0.00428 0.0229 0.9943 0.8036
-0.500 -0.1586 0.00899 0.00459 0.0184 0.9884 0.9013
-0.250 -0.0779 0.00918 0.00483 0.0088 0.9830 0.9497
0.000 -0.0001 0.00926 0.00491 0.0000 0.9716 0.9715
0.250 0.0779 0.00918 0.00483 -0.0088 0.9493 0.9829
0.500 0.1591 0.00900 0.00459 -0.0185 0.9019 0.9887
0.750 0.2154 0.00897 0.00428 -0.0230 0.8027 0.9944
1.000 0.2489 0.00915 0.00397 -0.0235 0.6838 1.0000
1.250 0.2638 0.00947 0.00381 -0.0207 0.5794 1.0000
1.500 0.2793 0.00992 0.00373 -0.0183 0.4658 1.0000
1.750 0.2959 0.01046 0.00372 -0.0163 0.3482 1.0000
2.000 0.3135 0.01109 0.00382 -0.0147 0.2396 1.0000
2.250 0.3311 0.01194 0.00408 -0.0130 0.1417 1.0000
2.500 0.3506 0.01254 0.00445 -0.0114 0.1126 1.0000
2.750 0.3713 0.01295 0.00478 -0.0100 0.1021 1.0000
3.000 0.3915 0.01349 0.00519 -0.0085 0.0962 1.0000
3.250 0.4131 0.01387 0.00557 -0.0071 0.0925 1.0000
3.500 0.4346 0.01432 0.00597 -0.0057 0.0894 1.0000
3.750 0.4560 0.01485 0.00642 -0.0043 0.0870 1.0000
4.000 0.4770 0.01572 0.00719 -0.0030 0.0848 1.0000
4.250 0.4998 0.01622 0.00772 -0.0017 0.0834 1.0000
4.500 0.5227 0.01679 0.00831 -0.0005 0.0817 1.0000
4.750 0.5456 0.01744 0.00898 0.0006 0.0802 1.0000
5.000 0.5688 0.01818 0.00975 0.0017 0.0792 1.0000
5.250 0.5920 0.01898 0.01058 0.0028 0.0783 1.0000
5.500 0.6153 0.01985 0.01151 0.0038 0.0775 1.0000
5.750 0.6384 0.02082 0.01254 0.0049 0.0769 1.0000
6.000 0.6613 0.02189 0.01370 0.0059 0.0765 1.0000
6.250 0.6839 0.02308 0.01499 0.0070 0.0761 1.0000
6.500 0.7059 0.02438 0.01639 0.0081 0.0755 1.0000
6.750 0.7272 0.02597 0.01809 0.0091 0.0749 1.0000
7.000 0.7477 0.02773 0.02002 0.0103 0.0747 1.0000
7.250 0.7677 0.02937 0.02190 0.0116 0.0749 1.0000
7.500 0.7860 0.03125 0.02414 0.0132 0.0757 1.0000
7.750 0.7867 0.03738 0.03129 0.0163 0.0810 1.0000
8.000 0.7986 0.04109 0.03519 0.0175 0.0834 1.0000
8.250 0.7092 0.06422 0.06011 0.0164 0.1177 1.0000
8.500 0.7049 0.06805 0.06401 0.0158 0.1151 1.0000
8.750 0.7079 0.07101 0.06698 0.0159 0.1134 1.0000
9.000 0.7197 0.07310 0.06906 0.0171 0.1121 1.0000
9.250 0.7456 0.07474 0.07063 0.0189 0.1111 1.0000
9.500 0.7630 0.08065 0.07644 0.0190 0.1096 1.0000
9.750 0.6357 0.09524 0.09112 -0.0010 0.1039 1.0000
10.000 0.6376 0.09879 0.09465 -0.0023 0.1014 1.0000
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