WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Reynolds number: 100,000 Max Cl/Cd: 25.63 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx71089a-il-100000.txt Download as CSV file: xf-fx71089a-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6028 0.08946 0.08383 0.0046 1.0000 0.1924
-8.250 -0.6034 0.08629 0.08070 0.0036 1.0000 0.1989
-8.000 -0.6407 0.08077 0.07531 -0.0014 1.0000 0.2057
-7.750 -0.6117 0.07877 0.07329 0.0015 1.0000 0.2097
-7.500 -0.6569 0.07310 0.06765 -0.0043 1.0000 0.2215
-7.250 -0.7286 0.04727 0.04000 -0.0154 1.0000 0.1232
-7.000 -0.7133 0.04375 0.03639 -0.0146 1.0000 0.1215
-6.750 -0.7001 0.04021 0.03260 -0.0135 1.0000 0.1187
-6.500 -0.6875 0.03640 0.02831 -0.0120 1.0000 0.1149
-6.250 -0.6741 0.03305 0.02421 -0.0100 1.0000 0.1118
-6.000 -0.6544 0.03102 0.02183 -0.0086 1.0000 0.1111
-5.750 -0.6335 0.02915 0.01974 -0.0074 1.0000 0.1113
-5.500 -0.6118 0.02753 0.01800 -0.0064 1.0000 0.1126
-5.250 -0.5895 0.02618 0.01657 -0.0053 1.0000 0.1144
-5.000 -0.5667 0.02489 0.01516 -0.0043 1.0000 0.1159
-4.750 -0.5434 0.02364 0.01378 -0.0031 1.0000 0.1173
-4.500 -0.5197 0.02249 0.01251 -0.0021 1.0000 0.1191
-4.250 -0.4957 0.02145 0.01137 -0.0010 1.0000 0.1213
-4.000 -0.4717 0.02058 0.01037 0.0001 1.0000 0.1240
-3.750 -0.4485 0.01939 0.00937 0.0011 1.0000 0.1287
-3.500 -0.4255 0.01863 0.00867 0.0023 1.0000 0.1348
-3.250 -0.4030 0.01775 0.00787 0.0035 1.0000 0.1418
-3.000 -0.3813 0.01697 0.00722 0.0049 1.0000 0.1523
-2.750 -0.3608 0.01612 0.00654 0.0066 1.0000 0.1707
-2.500 -0.3430 0.01498 0.00589 0.0085 1.0000 0.2195
-2.250 -0.3295 0.01342 0.00541 0.0109 1.0000 0.3747
-2.000 -0.3165 0.01236 0.00537 0.0141 1.0000 0.5703
-1.750 -0.2981 0.01189 0.00553 0.0172 1.0000 0.7179
-1.500 -0.2707 0.01184 0.00583 0.0192 1.0000 0.8352
-1.250 -0.1979 0.01237 0.00642 0.0132 1.0000 0.9356
-1.000 -0.0866 0.01288 0.00673 -0.0012 1.0000 0.9821
-0.750 -0.0134 0.01268 0.00641 -0.0102 1.0000 1.0000
-0.500 -0.0075 0.01247 0.00621 -0.0072 1.0000 1.0000
-0.250 -0.0031 0.01235 0.00609 -0.0037 1.0000 1.0000
0.000 0.0000 0.01230 0.00606 0.0000 1.0000 1.0000
0.250 0.0030 0.01235 0.00609 0.0037 1.0000 1.0000
0.500 0.0075 0.01247 0.00621 0.0072 1.0000 1.0000
0.750 0.0134 0.01268 0.00641 0.0102 1.0000 1.0000
1.000 0.0865 0.01288 0.00673 0.0012 0.9821 1.0000
1.250 0.1981 0.01236 0.00641 -0.0132 0.9352 1.0000
1.500 0.2706 0.01183 0.00583 -0.0192 0.8349 1.0000
1.750 0.2980 0.01189 0.00553 -0.0172 0.7184 1.0000
2.000 0.3165 0.01235 0.00537 -0.0141 0.5721 1.0000
2.250 0.3295 0.01342 0.00541 -0.0109 0.3754 1.0000
2.500 0.3430 0.01498 0.00589 -0.0084 0.2196 1.0000
2.750 0.3608 0.01612 0.00655 -0.0065 0.1708 1.0000
3.000 0.3813 0.01697 0.00722 -0.0049 0.1523 1.0000
3.250 0.4029 0.01775 0.00786 -0.0035 0.1418 1.0000
3.500 0.4255 0.01862 0.00867 -0.0022 0.1347 1.0000
3.750 0.4484 0.01939 0.00936 -0.0011 0.1286 1.0000
4.000 0.4716 0.02057 0.01037 -0.0001 0.1240 1.0000
4.250 0.4956 0.02145 0.01136 0.0010 0.1213 1.0000
4.500 0.5196 0.02248 0.01250 0.0021 0.1191 1.0000
4.750 0.5433 0.02364 0.01378 0.0032 0.1173 1.0000
5.000 0.5666 0.02489 0.01516 0.0043 0.1159 1.0000
5.250 0.5894 0.02618 0.01656 0.0053 0.1144 1.0000
5.500 0.6118 0.02753 0.01800 0.0064 0.1127 1.0000
5.750 0.6334 0.02915 0.01973 0.0074 0.1113 1.0000
6.000 0.6544 0.03102 0.02183 0.0086 0.1111 1.0000
6.250 0.6741 0.03304 0.02420 0.0100 0.1118 1.0000
6.500 0.6875 0.03639 0.02830 0.0120 0.1149 1.0000
6.750 0.7001 0.04021 0.03260 0.0135 0.1187 1.0000
7.000 0.7134 0.04374 0.03639 0.0146 0.1215 1.0000
7.250 0.7289 0.04729 0.04000 0.0153 0.1233 1.0000
7.500 0.6570 0.07312 0.06767 0.0042 0.2215 1.0000
7.750 0.6133 0.07869 0.07322 -0.0014 0.2095 1.0000
8.000 0.6418 0.08074 0.07528 0.0014 0.2057 1.0000
8.250 0.6031 0.08631 0.08072 -0.0038 0.1986 1.0000
8.500 0.6036 0.08947 0.08384 -0.0047 0.1923 1.0000
8.750 0.6258 0.09210 0.08648 -0.0026 0.1891 1.0000
9.000 0.6892 0.09541 0.08988 0.0045 0.1870 1.0000
9.250 0.6001 0.10036 0.09461 -0.0085 0.1776 1.0000
9.500 0.6143 0.10328 0.09754 -0.0077 0.1738 1.0000
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Polar data table (+)
Polar graphs
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