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

WORTMANN FX 69-274 (fx69274-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 69-274 (fx69274-il)
Reynolds number: 100,000
Max Cl/Cd: 1.7 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx69274-il-100000.txt
Download as CSV file: xf-fx69274-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 69-274                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.2845   0.17735   0.17225  -0.0521   1.0000   0.1743
 -17.000  -0.2637   0.17504   0.17002  -0.0496   0.9989   0.1755
 -16.750  -0.7027   0.08504   0.07908  -0.0893   1.0000   0.1248
 -16.500  -0.7123   0.08644   0.08061  -0.0850   1.0000   0.1260
 -16.250  -0.7173   0.08153   0.07560  -0.0887   0.9948   0.1283
 -16.000  -0.7840   0.07062   0.06421  -0.0943   0.9892   0.1286
 -15.750  -0.7956   0.06543   0.05875  -0.0982   0.9832   0.1310
 -15.500  -0.8142   0.05987   0.05280  -0.1021   0.9785   0.1333
 -15.250  -0.8361   0.05527   0.04776  -0.1043   0.9702   0.1352
 -15.000  -0.7712   0.05486   0.04767  -0.1082   0.9661   0.1410
 -14.750  -0.7698   0.05182   0.04440  -0.1103   0.9578   0.1448
 -14.500  -0.7618   0.04911   0.04147  -0.1120   0.9499   0.1488
 -14.250  -0.7272   0.04846   0.04098  -0.1133   0.9410   0.1544
 -14.000  -0.7285   0.04621   0.03848  -0.1133   0.9320   0.1588
 -13.750  -0.7073   0.04534   0.03770  -0.1131   0.9219   0.1642
 -13.500  -0.6956   0.04422   0.03654  -0.1125   0.9136   0.1701
 -13.250  -0.7039   0.04260   0.03469  -0.1106   0.9021   0.1749
 -13.000  -0.6765   0.04224   0.03455  -0.1100   0.8947   0.1822
 -12.750  -0.6816   0.04090   0.03300  -0.1082   0.8839   0.1881
 -12.500  -0.6600   0.04036   0.03264  -0.1073   0.8766   0.1959
 -12.250  -0.6619   0.03926   0.03139  -0.1055   0.8678   0.2032
 -12.000  -0.6441   0.03872   0.03101  -0.1046   0.8599   0.2119
 -11.750  -0.6481   0.03761   0.02970  -0.1017   0.8534   0.2202
 -11.500  -0.6294   0.03728   0.02959  -0.1013   0.8444   0.2301
 -11.250  -0.6273   0.03640   0.02864  -0.0990   0.8367   0.2399
 -11.000  -0.6189   0.03582   0.02810  -0.0966   0.8313   0.2506
 -10.750  -0.6117   0.03551   0.02789  -0.0953   0.8221   0.2614
 -10.500  -0.6172   0.03485   0.02709  -0.0919   0.8148   0.2726
 -10.250  -0.6030   0.03447   0.02686  -0.0899   0.8099   0.2857
 -10.000  -0.6052   0.03454   0.02699  -0.0867   0.8007   0.2968
  -9.750  -0.6130   0.03446   0.02687  -0.0820   0.7931   0.3083
  -9.500  -0.6010   0.03428   0.02679  -0.0794   0.7883   0.3223
  -9.250  -0.6055   0.03455   0.02705  -0.0753   0.7808   0.3340
  -9.000  -0.6094   0.03494   0.02746  -0.0712   0.7724   0.3458
  -8.750  -0.5922   0.03486   0.02746  -0.0693   0.7677   0.3602
  -8.500  -0.5768   0.03458   0.02713  -0.0671   0.7640   0.3750
  -8.250  -0.5889   0.03560   0.02821  -0.0622   0.7531   0.3840
  -8.000  -0.5768   0.03572   0.02834  -0.0598   0.7472   0.3966
  -7.750  -0.5676   0.03545   0.02791  -0.0569   0.7434   0.4112
  -7.500  -0.5264   0.03553   0.02811  -0.0580   0.7410   0.4257
  -7.250  -0.5699   0.03695   0.02948  -0.0494   0.7275   0.4312
  -7.000  -0.5329   0.03721   0.02989  -0.0501   0.7234   0.4440
  -6.750  -0.5053   0.03699   0.02960  -0.0495   0.7204   0.4580
  -6.500  -0.4740   0.03685   0.02938  -0.0493   0.7182   0.4725
  -6.250  -0.5371   0.03902   0.03157  -0.0389   0.7036   0.4750
  -6.000  -0.4921   0.03951   0.03222  -0.0403   0.7001   0.4866
  -5.750  -0.4585   0.03922   0.03184  -0.0405   0.6976   0.5001
  -5.500  -0.4965   0.04118   0.03389  -0.0328   0.6873   0.5040
  -5.250  -0.5012   0.04175   0.03440  -0.0288   0.6806   0.5138
  -5.000  -0.4618   0.04187   0.03452  -0.0298   0.6773   0.5248
  -4.750  -0.4245   0.04145   0.03396  -0.0307   0.6750   0.5391
  -4.500  -0.4696   0.04347   0.03604  -0.0226   0.6645   0.5428
  -4.250  -0.4522   0.04443   0.03710  -0.0211   0.6589   0.5510
  -4.000  -0.4250   0.04433   0.03689  -0.0209   0.6555   0.5645
  -3.750  -0.3784   0.04483   0.03746  -0.0219   0.6532   0.5746
  -3.500  -0.4034   0.04617   0.03868  -0.0173   0.6464   0.5849
  -3.250  -0.4071   0.04790   0.04054  -0.0141   0.6394   0.5901
  -3.000  -0.3806   0.04835   0.04098  -0.0136   0.6353   0.5994
  -2.750  -0.3452   0.04800   0.04052  -0.0143   0.6324   0.6107
  -2.500  -0.2995   0.04803   0.04056  -0.0151   0.6305   0.6190
  -2.250  -0.3538   0.05128   0.04385  -0.0090   0.6208   0.6258
  -2.000  -0.3427   0.05216   0.04471  -0.0078   0.6166   0.6343
  -1.750  -0.3178   0.05289   0.04546  -0.0071   0.6134   0.6423
  -1.500  -0.2818   0.05264   0.04508  -0.0080   0.6108   0.6550
  -1.250  -0.2361   0.05269   0.04515  -0.0083   0.6089   0.6624
  -1.000  -0.2955   0.05653   0.04910  -0.0025   0.5997   0.6682
  -0.750  -0.2876   0.05765   0.05016  -0.0019   0.5967   0.6787
  -0.500  -0.3633   0.06471   0.05748   0.0015   0.6387   0.6810
  -0.250  -0.3592   0.06666   0.05949   0.0029   0.6437   0.6881
   0.000  -0.3444   0.06739   0.06012   0.0027   0.6389   0.7003
   0.250  -0.3260   0.06859   0.06139   0.0040   0.6356   0.7067
   0.500  -0.2866   0.07000   0.06274   0.0028   0.6318   0.7171
   0.750  -0.2569   0.06771   0.06034   0.0050   0.5948   0.7275
   1.000  -0.2334   0.06874   0.06138   0.0057   0.5918   0.7359
   1.250  -0.2108   0.06995   0.06252   0.0050   0.5903   0.7479
   1.500  -0.1916   0.07145   0.06407   0.0062   0.5892   0.7551
   1.750  -0.1664   0.07306   0.06563   0.0059   0.5883   0.7662
   2.000  -0.1412   0.07490   0.06747   0.0060   0.5874   0.7753
   2.250  -0.2242   0.07779   0.07057   0.0119   0.6010   0.7798
   2.500  -0.2044   0.07865   0.07137   0.0118   0.5943   0.7915
   2.750  -0.1789   0.07992   0.07265   0.0125   0.5910   0.8001
   3.000  -0.1433   0.08186   0.07454   0.0114   0.5888   0.8117
   3.250  -0.1012   0.08466   0.07731   0.0102   0.5875   0.8213
   3.500  -0.1621   0.08340   0.07615   0.0167   0.5770   0.8285
   3.750  -0.1389   0.08444   0.07716   0.0167   0.5722   0.8392
   4.000  -0.1098   0.08594   0.07864   0.0170   0.5694   0.8500
   4.250  -0.0728   0.08827   0.08094   0.0161   0.5678   0.8613
   4.500  -0.1155   0.08822   0.08096   0.0207   0.5604   0.8701
   4.750  -0.1030   0.08905   0.08180   0.0218   0.5546   0.8811
   5.000  -0.0794   0.09024   0.08295   0.0220   0.5510   0.8940
   5.250  -0.0494   0.09193   0.08462   0.0220   0.5488   0.9070
   5.500  -0.0104   0.09471   0.08737   0.0210   0.5474   0.9201
   5.750  -0.0601   0.09392   0.08668   0.0255   0.5376   0.9304
   6.000  -0.0368   0.09532   0.08807   0.0247   0.5330   0.9436
   6.250   0.0008   0.09745   0.09019   0.0220   0.5299   0.9559
   6.500   0.0542   0.10096   0.09368   0.0171   0.5280   0.9661
   6.750   0.0313   0.10216   0.09496   0.0168   0.5196   0.9726
   7.000   0.0658   0.10449   0.09729   0.0126   0.5137   0.9807
   7.250   0.1162   0.10758   0.10037   0.0068   0.5103   0.9856
   7.500   0.1760   0.11176   0.10454   0.0003   0.5084   0.9920
   7.750   0.1508   0.11324   0.10610  -0.0006   0.4993   0.9984
   8.000   0.1528   0.11288   0.10568   0.0013   0.4945   1.0000
   8.250   0.1636   0.11296   0.10568   0.0028   0.4915   1.0000
   8.500   0.1959   0.11522   0.10788   0.0012   0.4897   1.0000
<< Back to WORTMANN FX 69-274 (fx69274-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 69-274 (fx69274-il)