WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Reynolds number: 100,000 Max Cl/Cd: 26.91 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx71089a-il-100000-n5.txt Download as CSV file: xf-fx71089a-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7214 0.08523 0.07924 -0.0104 1.0000 0.0623
-10.250 -0.7865 0.06812 0.06201 -0.0245 1.0000 0.0611
-10.000 -0.8272 0.06145 0.05514 -0.0257 1.0000 0.0607
-9.750 -0.8500 0.05623 0.04964 -0.0252 1.0000 0.0606
-9.500 -0.8612 0.05173 0.04481 -0.0241 1.0000 0.0606
-9.250 -0.8642 0.04785 0.04056 -0.0228 1.0000 0.0609
-9.000 -0.8612 0.04447 0.03682 -0.0214 1.0000 0.0612
-8.750 -0.8540 0.04158 0.03355 -0.0200 1.0000 0.0619
-8.500 -0.8437 0.03896 0.03054 -0.0186 1.0000 0.0627
-8.250 -0.8306 0.03664 0.02782 -0.0172 1.0000 0.0634
-8.000 -0.8149 0.03457 0.02538 -0.0159 1.0000 0.0639
-7.750 -0.7973 0.03273 0.02321 -0.0146 1.0000 0.0643
-7.500 -0.7776 0.03105 0.02134 -0.0136 1.0000 0.0647
-7.250 -0.7568 0.02958 0.01978 -0.0127 1.0000 0.0653
-7.000 -0.7353 0.02829 0.01838 -0.0117 1.0000 0.0659
-6.750 -0.7135 0.02713 0.01714 -0.0108 1.0000 0.0667
-6.500 -0.6914 0.02611 0.01604 -0.0099 1.0000 0.0679
-6.250 -0.6690 0.02513 0.01497 -0.0089 1.0000 0.0693
-6.000 -0.6464 0.02416 0.01390 -0.0079 1.0000 0.0706
-5.750 -0.6235 0.02323 0.01286 -0.0069 1.0000 0.0719
-5.500 -0.6006 0.02234 0.01189 -0.0059 1.0000 0.0729
-5.250 -0.5776 0.02153 0.01100 -0.0048 1.0000 0.0740
-5.000 -0.5557 0.02066 0.01020 -0.0037 1.0000 0.0752
-4.750 -0.5338 0.01994 0.00954 -0.0025 1.0000 0.0768
-4.500 -0.5120 0.01931 0.00894 -0.0014 1.0000 0.0789
-4.250 -0.4900 0.01873 0.00837 -0.0001 1.0000 0.0818
-4.000 -0.4681 0.01818 0.00782 0.0011 1.0000 0.0850
-3.750 -0.4470 0.01760 0.00732 0.0024 1.0000 0.0886
-3.500 -0.4254 0.01710 0.00686 0.0037 1.0000 0.0932
-3.250 -0.4040 0.01659 0.00641 0.0050 1.0000 0.0991
-3.000 -0.3826 0.01612 0.00600 0.0063 1.0000 0.1087
-2.750 -0.3614 0.01564 0.00563 0.0076 1.0000 0.1238
-2.500 -0.3407 0.01511 0.00533 0.0089 1.0000 0.1496
-2.250 -0.3201 0.01461 0.00510 0.0102 1.0000 0.1903
-2.000 -0.2998 0.01412 0.00491 0.0115 1.0000 0.2447
-1.750 -0.2798 0.01364 0.00478 0.0129 1.0000 0.3111
-1.500 -0.2611 0.01306 0.00473 0.0145 1.0000 0.4104
-1.250 -0.2430 0.01249 0.00479 0.0164 1.0000 0.5362
-1.000 -0.2246 0.01203 0.00499 0.0188 1.0000 0.6737
-0.750 -0.1962 0.01184 0.00531 0.0199 0.9979 0.8050
-0.500 -0.1358 0.01194 0.00561 0.0145 0.9893 0.8911
-0.250 -0.0677 0.01207 0.00577 0.0073 0.9784 0.9353
0.000 0.0001 0.01213 0.00584 0.0000 0.9647 0.9648
0.250 0.0676 0.01207 0.00577 -0.0073 0.9355 0.9784
0.500 0.1359 0.01194 0.00561 -0.0145 0.8907 0.9892
0.750 0.1961 0.01184 0.00531 -0.0199 0.8051 0.9979
1.000 0.2246 0.01203 0.00498 -0.0188 0.6729 1.0000
1.250 0.2429 0.01249 0.00478 -0.0164 0.5354 1.0000
1.500 0.2610 0.01306 0.00473 -0.0145 0.4096 1.0000
1.750 0.2798 0.01363 0.00478 -0.0129 0.3117 1.0000
2.000 0.2997 0.01412 0.00491 -0.0115 0.2456 1.0000
2.250 0.3201 0.01461 0.00509 -0.0102 0.1905 1.0000
2.500 0.3407 0.01511 0.00533 -0.0089 0.1496 1.0000
2.750 0.3613 0.01564 0.00563 -0.0076 0.1240 1.0000
3.000 0.3825 0.01612 0.00600 -0.0063 0.1087 1.0000
3.250 0.4040 0.01658 0.00641 -0.0050 0.0991 1.0000
3.500 0.4253 0.01710 0.00686 -0.0037 0.0931 1.0000
3.750 0.4469 0.01759 0.00732 -0.0024 0.0885 1.0000
4.250 0.4900 0.01873 0.00837 0.0001 0.0817 1.0000
4.500 0.5119 0.01930 0.00893 0.0014 0.0788 1.0000
4.750 0.5338 0.01994 0.00954 0.0026 0.0768 1.0000
5.000 0.5557 0.02065 0.01020 0.0037 0.0752 1.0000
5.250 0.5776 0.02152 0.01099 0.0048 0.0739 1.0000
5.500 0.6005 0.02233 0.01189 0.0059 0.0729 1.0000
5.750 0.6235 0.02322 0.01286 0.0069 0.0718 1.0000
6.000 0.6464 0.02416 0.01390 0.0079 0.0706 1.0000
6.250 0.6690 0.02513 0.01496 0.0089 0.0693 1.0000
6.500 0.6914 0.02611 0.01604 0.0099 0.0679 1.0000
6.750 0.7135 0.02713 0.01714 0.0108 0.0667 1.0000
7.000 0.7353 0.02829 0.01838 0.0117 0.0659 1.0000
7.250 0.7568 0.02958 0.01977 0.0127 0.0653 1.0000
7.500 0.7777 0.03105 0.02134 0.0136 0.0647 1.0000
7.750 0.7973 0.03273 0.02321 0.0146 0.0642 1.0000
8.000 0.8150 0.03457 0.02538 0.0158 0.0639 1.0000
8.250 0.8307 0.03664 0.02782 0.0172 0.0634 1.0000
8.500 0.8437 0.03897 0.03055 0.0186 0.0627 1.0000
8.750 0.8541 0.04158 0.03355 0.0200 0.0619 1.0000
9.000 0.8614 0.04447 0.03682 0.0214 0.0612 1.0000
9.250 0.8644 0.04786 0.04057 0.0228 0.0609 1.0000
9.500 0.8613 0.05176 0.04483 0.0241 0.0606 1.0000
9.750 0.8501 0.05627 0.04968 0.0251 0.0606 1.0000
10.000 0.8272 0.06151 0.05520 0.0257 0.0607 1.0000
10.250 0.7864 0.06822 0.06211 0.0243 0.0611 1.0000
10.500 0.7219 0.08531 0.07931 0.0102 0.0623 1.0000
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Polar data table (+)
Polar graphs
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