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FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 84-W-097 (fx84w097-il)
Reynolds number: 50,000
Max Cl/Cd: 36.14 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx84w097-il-50000.txt
Download as CSV file: xf-fx84w097-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-097                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4281   0.11573   0.10900  -0.0125   1.0000   0.2033
  -9.250  -0.4106   0.11078   0.10402  -0.0120   1.0000   0.2120
  -9.000  -0.4272   0.11013   0.10351  -0.0150   1.0000   0.2188
  -8.750  -0.4116   0.10563   0.09902  -0.0143   1.0000   0.2324
  -8.500  -0.3980   0.10146   0.09488  -0.0138   1.0000   0.2441
  -8.250  -0.3928   0.09810   0.09158  -0.0142   1.0000   0.2549
  -8.000  -0.3970   0.09562   0.08920  -0.0152   1.0000   0.2657
  -7.750  -0.4074   0.09420   0.08792  -0.0162   1.0000   0.2778
  -7.500  -0.3992   0.09071   0.08449  -0.0156   1.0000   0.2922
  -7.250  -0.3965   0.08778   0.08165  -0.0150   1.0000   0.3070
  -7.000  -0.3996   0.08533   0.07931  -0.0142   1.0000   0.3221
  -6.750  -0.3704   0.08062   0.07456  -0.0120   1.0000   0.3460
  -6.500  -0.3824   0.07916   0.07327  -0.0101   1.0000   0.3653
  -6.250  -0.3770   0.07659   0.07076  -0.0070   1.0000   0.3945
  -6.000  -0.3681   0.07382   0.06806  -0.0039   1.0000   0.4224
  -5.750  -0.3646   0.07141   0.06574  -0.0002   1.0000   0.4493
  -5.500  -0.4005   0.07190   0.06644   0.0063   1.0000   0.4701
  -4.500  -0.4124   0.04612   0.03885  -0.0330   1.0000   0.1587
  -4.250  -0.3917   0.04179   0.03368  -0.0340   1.0000   0.1456
  -4.000  -0.3732   0.03872   0.03037  -0.0336   1.0000   0.1432
  -3.750  -0.3520   0.03606   0.02714  -0.0335   1.0000   0.1438
  -3.500  -0.3312   0.03390   0.02466  -0.0332   1.0000   0.1492
  -3.250  -0.3085   0.03198   0.02239  -0.0328   1.0000   0.1534
  -3.000  -0.2842   0.03033   0.02016  -0.0324   1.0000   0.1599
  -2.750  -0.2629   0.02905   0.01877  -0.0319   1.0000   0.1731
  -2.500  -0.2405   0.02776   0.01734  -0.0313   1.0000   0.1851
  -2.250  -0.2184   0.02676   0.01623  -0.0307   1.0000   0.2072
  -2.000  -0.1964   0.02583   0.01527  -0.0298   1.0000   0.2345
  -1.750  -0.1735   0.02487   0.01456  -0.0294   1.0000   0.2848
  -1.500  -0.1498   0.02292   0.01378  -0.0288   1.0000   0.4418
  -1.250  -0.1246   0.02116   0.01332  -0.0262   1.0000   1.0000
  -1.000  -0.0972   0.02174   0.01336  -0.0275   0.9965   1.0000
  -0.750  -0.0540   0.02266   0.01380  -0.0317   0.9862   1.0000
  -0.500  -0.0143   0.02354   0.01430  -0.0352   0.9759   1.0000
  -0.250   0.0244   0.02443   0.01486  -0.0385   0.9655   1.0000
   0.000   0.0643   0.02537   0.01554  -0.0419   0.9551   1.0000
   0.250   0.1007   0.02624   0.01619  -0.0447   0.9444   1.0000
   0.500   0.1316   0.02704   0.01681  -0.0465   0.9334   1.0000
   0.750   0.1642   0.02791   0.01752  -0.0485   0.9226   1.0000
   1.000   0.1996   0.02884   0.01833  -0.0509   0.9121   1.0000
   1.250   0.2336   0.02975   0.01912  -0.0530   0.9011   1.0000
   1.500   0.2574   0.03058   0.01988  -0.0535   0.8900   1.0000
   1.750   0.2853   0.03149   0.02073  -0.0546   0.8790   1.0000
   2.000   0.3169   0.03246   0.02166  -0.0562   0.8683   1.0000
   2.250   0.3509   0.03343   0.02259  -0.0581   0.8573   1.0000
   2.500   0.3706   0.03437   0.02351  -0.0578   0.8456   1.0000
   2.750   0.3939   0.03536   0.02451  -0.0581   0.8340   1.0000
   3.000   0.4205   0.03639   0.02556  -0.0588   0.8225   1.0000
   3.250   0.4517   0.03740   0.02661  -0.0600   0.8109   1.0000
   3.500   0.4822   0.03840   0.02766  -0.0611   0.7992   1.0000
   3.750   0.5007   0.03949   0.02882  -0.0606   0.7865   1.0000
   4.000   0.5202   0.04063   0.03002  -0.0603   0.7740   1.0000
   4.250   0.5422   0.04178   0.03124  -0.0603   0.7613   1.0000
   4.500   0.5660   0.04292   0.03246  -0.0604   0.7483   1.0000
   4.750   0.5906   0.04403   0.03367  -0.0605   0.7351   1.0000
   5.000   0.6151   0.04512   0.03492  -0.0605   0.7211   1.0000
   5.250   0.6391   0.04619   0.03612  -0.0603   0.7064   1.0000
   5.500   0.6622   0.04727   0.03734  -0.0600   0.6913   1.0000
   5.750   0.6852   0.04836   0.03858  -0.0596   0.6761   1.0000
   6.000   0.7091   0.04936   0.03978  -0.0592   0.6600   1.0000
   6.250   0.7366   0.05014   0.04077  -0.0588   0.6434   1.0000
   6.500   0.7758   0.05016   0.04107  -0.0586   0.6262   1.0000
   6.750   0.8022   0.05061   0.04180  -0.0575   0.6073   1.0000
   7.000   0.8290   0.05069   0.04214  -0.0559   0.5861   1.0000
   7.250   0.9589   0.03817   0.03045  -0.0506   0.5520   1.0000
   7.500   1.0095   0.03213   0.02466  -0.0448   0.5073   1.0000
   7.750   1.0324   0.02904   0.02167  -0.0392   0.4458   1.0000
   8.000   1.0301   0.02850   0.02042  -0.0321   0.3294   1.0000
   8.250   1.0178   0.03127   0.02201  -0.0269   0.2339   1.0000
   8.500   1.0213   0.03416   0.02421  -0.0239   0.1844   1.0000
   8.750   1.0397   0.03676   0.02649  -0.0223   0.1519   1.0000
   9.000   1.0728   0.03951   0.02905  -0.0220   0.1300   1.0000
   9.250   1.1066   0.04264   0.03210  -0.0221   0.1155   1.0000
   9.500   1.1299   0.04595   0.03587  -0.0211   0.1090   1.0000
   9.750   1.1570   0.04973   0.03961  -0.0212   0.1013   1.0000
  10.000   1.1642   0.05299   0.04351  -0.0191   0.0989   1.0000
  10.250   1.1708   0.05694   0.04797  -0.0173   0.0978   1.0000
  10.500   1.1718   0.06107   0.05256  -0.0155   0.0976   1.0000
  10.750   1.1671   0.06527   0.05716  -0.0137   0.0977   1.0000
  11.000   1.1567   0.06946   0.06170  -0.0119   0.0979   1.0000
  11.250   1.1409   0.07353   0.06604  -0.0100   0.0984   1.0000
  11.500   1.1214   0.07780   0.07052  -0.0088   0.0991   1.0000
  11.750   1.1015   0.08253   0.07543  -0.0086   0.0998   1.0000
  12.000   1.0831   0.08789   0.08092  -0.0093   0.1006   1.0000
  12.250   1.0711   0.09371   0.08683  -0.0104   0.1014   1.0000
  12.500   0.9535   0.11041   0.10371  -0.0257   0.1106   1.0000
  12.750   0.9391   0.11916   0.11245  -0.0300   0.1132   1.0000
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