Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 83-W-227 (fx83w227-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 83-W-227 (fx83w227-il)
Reynolds number: 50,000
Max Cl/Cd: 2.25 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx83w227-il-50000.txt
Download as CSV file: xf-fx83w227-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 83-W-227                                     
  
 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  -0.6661   0.10069   0.09424  -0.0324   1.0000   0.2337
  -9.250  -0.7032   0.09443   0.08796  -0.0316   1.0000   0.2319
  -9.000  -0.7606   0.08794   0.08145  -0.0286   1.0000   0.2292
  -8.750  -0.8516   0.08091   0.07428  -0.0210   1.0000   0.2242
  -8.500  -0.9209   0.07420   0.06723  -0.0143   1.0000   0.2214
  -8.250  -0.9448   0.07052   0.06331  -0.0101   1.0000   0.2226
  -8.000  -0.9614   0.06721   0.05975  -0.0063   1.0000   0.2244
  -7.750  -0.9739   0.06412   0.05636  -0.0028   1.0000   0.2267
  -7.500  -0.9843   0.06108   0.05294   0.0008   1.0000   0.2294
  -7.250  -0.9925   0.05820   0.04957   0.0043   1.0000   0.2322
  -7.000  -0.9866   0.05627   0.04753   0.0064   1.0000   0.2362
  -6.750  -0.9751   0.05513   0.04642   0.0079   1.0000   0.2414
  -6.500  -0.9701   0.05345   0.04446   0.0103   1.0000   0.2469
  -6.250  -0.9673   0.05156   0.04210   0.0129   1.0000   0.2521
  -6.000  -0.9521   0.05062   0.04132   0.0140   1.0000   0.2584
  -5.750  -0.9422   0.04949   0.04001   0.0158   1.0000   0.2660
  -5.500  -0.9312   0.04829   0.03866   0.0175   1.0000   0.2734
  -5.250  -0.9178   0.04755   0.03792   0.0189   1.0000   0.2822
  -5.000  -0.9060   0.04658   0.03680   0.0205   1.0000   0.2919
  -4.750  -0.8921   0.04595   0.03619   0.0218   1.0000   0.3029
  -4.500  -0.8783   0.04530   0.03557   0.0232   1.0000   0.3147
  -4.250  -0.8655   0.04468   0.03486   0.0247   1.0000   0.3290
  -4.000  -0.8516   0.04422   0.03443   0.0261   1.0000   0.3448
  -3.750  -0.8374   0.04384   0.03418   0.0275   1.0000   0.3627
  -3.500  -0.8240   0.04346   0.03388   0.0290   1.0000   0.3843
  -3.250  -0.8082   0.04334   0.03404   0.0303   0.9994   0.4095
  -3.000  -0.7836   0.04414   0.03511   0.0301   0.9942   0.4468
  -2.750  -0.7636   0.04481   0.03616   0.0311   0.9897   0.4896
  -2.500  -0.7418   0.04609   0.03776   0.0321   0.9834   0.5430
  -2.250  -0.7249   0.04726   0.03924   0.0345   0.9781   0.5922
  -2.000  -0.7025   0.04926   0.04140   0.0362   0.9704   0.6443
  -1.750  -0.6892   0.05017   0.04240   0.0393   0.9643   0.6848
  -1.500  -0.6649   0.05234   0.04461   0.0409   0.9570   0.7265
  -1.250  -0.6506   0.05317   0.04545   0.0437   0.9509   0.7602
  -1.000  -0.6166   0.05567   0.04791   0.0435   0.9427   0.7959
  -0.750  -0.5962   0.05672   0.04891   0.0448   0.9363   0.8269
  -0.500  -0.5334   0.06060   0.05270   0.0388   0.9279   0.8551
  -0.250  -0.4716   0.06418   0.05613   0.0320   0.9221   0.8782
   0.000  -0.3762   0.06939   0.06114   0.0187   0.9117   0.8996
   0.250  -0.3059   0.07311   0.06470   0.0090   0.9056   0.9196
   0.500  -0.2301   0.07658   0.06802  -0.0022   0.8950   0.9392
   0.750  -0.1680   0.07938   0.07069  -0.0116   0.8875   0.9561
   1.000  -0.0993   0.08211   0.07330  -0.0225   0.8772   0.9725
   1.250  -0.0450   0.08451   0.07560  -0.0313   0.8708   0.9874
   1.500   0.0113   0.08651   0.07750  -0.0405   0.8594   1.0000
   1.750   0.0170   0.08727   0.07816  -0.0399   0.8543   1.0000
   2.000   0.0117   0.08649   0.07733  -0.0372   0.8434   1.0000
   2.250   0.0324   0.08832   0.07903  -0.0387   0.8374   1.0000
   2.500   0.0125   0.08666   0.07734  -0.0337   0.8275   1.0000
   2.750   0.0270   0.08768   0.07825  -0.0339   0.8200   1.0000
   3.000   0.0145   0.08713   0.07764  -0.0301   0.8133   1.0000
   3.250   0.0162   0.08707   0.07750  -0.0281   0.8040   1.0000
   3.500   0.0343   0.08923   0.07954  -0.0286   0.7991   1.0000
   3.750   0.0058   0.08671   0.07699  -0.0220   0.7889   1.0000
   4.000   0.0172   0.08771   0.07787  -0.0211   0.7817   1.0000
   4.250   0.0032   0.08709   0.07716  -0.0166   0.7757   1.0000
   4.500   0.0053   0.08717   0.07713  -0.0143   0.7663   1.0000
   4.750   0.0309   0.08999   0.07980  -0.0154   0.7612   1.0000
   5.000   0.0147   0.08861   0.07835  -0.0109   0.7520   1.0000
   5.250   0.0358   0.09048   0.08010  -0.0113   0.7443   1.0000
   5.500   0.0485   0.09249   0.08201  -0.0108   0.7403   1.0000
   5.750   0.0459   0.09216   0.08162  -0.0083   0.7300   1.0000
   6.000   0.0733   0.09495   0.08432  -0.0095   0.7240   1.0000
   6.250   0.0688   0.09513   0.08445  -0.0070   0.7170   1.0000
   6.500   0.0841   0.09657   0.08582  -0.0068   0.7083   1.0000
   6.750   0.1151   0.10025   0.08942  -0.0086   0.7040   1.0000
   7.000   0.1020   0.09940   0.08855  -0.0052   0.6958   1.0000
   7.250   0.1228   0.10147   0.09056  -0.0057   0.6880   1.0000
   7.500   0.1508   0.10529   0.09432  -0.0073   0.6841   1.0000
   7.750   0.1381   0.10414   0.09316  -0.0041   0.6743   1.0000
   8.000   0.1619   0.10674   0.09572  -0.0050   0.6682   1.0000
   8.250   0.1742   0.10909   0.09804  -0.0049   0.6639   1.0000
   8.500   0.1755   0.10929   0.09823  -0.0034   0.6536   1.0000
   8.750   0.2032   0.11259   0.10150  -0.0048   0.6484   1.0000
   9.000   0.2019   0.11353   0.10243  -0.0035   0.6432   1.0000
   9.250   0.2122   0.11477   0.10367  -0.0031   0.6338   1.0000
   9.500   0.2430   0.11871   0.10759  -0.0048   0.6290   1.0000
   9.750   0.2331   0.11854   0.10743  -0.0028   0.6219   1.0000
  10.000   0.2489   0.12052   0.10940  -0.0030   0.6141   1.0000
  10.250   0.2816   0.12510   0.11398  -0.0050   0.6099   1.0000
<< Back to FX 83-W-227 (fx83w227-il)

Polar data table (+)

Polar graphs


<< Back to FX 83-W-227 (fx83w227-il)