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WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
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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