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WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
Reynolds number: 50,000
Max Cl/Cd: 4.91 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66a175-il-50000.txt
Download as CSV file: xf-fx66a175-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 66-17A-175 AIRFOIL                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2615   0.14247   0.13660  -0.0391   1.0000   0.2153
 -11.750  -0.2352   0.13636   0.13056  -0.0386   1.0000   0.2224
 -11.500  -0.2539   0.13675   0.13112  -0.0402   1.0000   0.2298
 -11.250  -0.2257   0.13079   0.12524  -0.0396   1.0000   0.2388
 -11.000  -0.2334   0.12914   0.12378  -0.0404   1.0000   0.2462
 -10.750  -0.2290   0.12697   0.12178  -0.0401   1.0000   0.2577
 -10.500  -0.2315   0.12537   0.12050  -0.0387   1.0000   0.2626
 -10.250  -0.2378   0.12566   0.12096  -0.0404   0.9847   0.2720
 -10.000  -0.2126   0.12073   0.11600  -0.0463   0.9672   0.2865
  -9.750  -0.1781   0.11458   0.10979  -0.0520   0.9537   0.2953
  -9.500  -0.1602   0.10998   0.10512  -0.0582   0.9433   0.3051
  -9.250  -0.1297   0.10424   0.09930  -0.0644   0.9327   0.3091
  -9.000  -0.1012   0.06936   0.06455  -0.1012   0.8909   0.1341
  -8.750  -0.1337   0.06078   0.05597  -0.1075   0.8843   0.1251
  -8.500  -0.1648   0.05453   0.04968  -0.1117   0.8754   0.1204
  -8.250  -0.2767   0.06361   0.05831  -0.1139   0.8857   0.1120
  -8.000  -0.2799   0.05962   0.05406  -0.1158   0.8746   0.1097
  -7.750  -0.2883   0.05645   0.05052  -0.1160   0.8633   0.1066
  -7.500  -0.2895   0.05339   0.04700  -0.1161   0.8537   0.1050
  -7.250  -0.2803   0.05017   0.04317  -0.1165   0.8454   0.1035
  -7.000  -0.2759   0.04829   0.04080  -0.1149   0.8359   0.1027
  -6.750  -0.2486   0.04519   0.03713  -0.1158   0.8298   0.1025
  -6.500  -0.2406   0.04400   0.03573  -0.1136   0.8209   0.1031
  -6.250  -0.2056   0.04152   0.03304  -0.1144   0.8154   0.1075
  -6.000  -0.1990   0.04113   0.03245  -0.1118   0.8073   0.1120
  -5.750  -0.1672   0.03937   0.03063  -0.1117   0.8019   0.1221
  -5.500  -0.1578   0.03918   0.03027  -0.1088   0.7952   0.1288
  -5.250  -0.1399   0.03835   0.02951  -0.1070   0.7895   0.1438
  -5.000  -0.1246   0.03730   0.02871  -0.1053   0.7848   0.1713
  -4.750  -0.1339   0.03750   0.02918  -0.1013   0.7790   0.1905
  -4.500  -0.1390   0.03608   0.02965  -0.0975   0.7752   0.3338
  -4.250  -0.1358   0.04299   0.03675  -0.0831   0.7717   0.5580
  -4.000  -0.1563   0.04456   0.03833  -0.0769   0.7682   0.5725
  -3.750  -0.1714   0.04610   0.03985  -0.0703   0.7653   0.5939
  -3.500  -0.1800   0.04771   0.04144  -0.0630   0.7631   0.6232
  -3.250  -0.1887   0.04906   0.04278  -0.0558   0.7622   0.6527
  -3.000  -0.4400   0.04512   0.03637  -0.0472   1.0000   0.1208
  -2.750  -0.4209   0.04470   0.03585  -0.0460   1.0000   0.1301
  -2.500  -0.4015   0.04404   0.03535  -0.0455   1.0000   0.1496
  -2.250  -0.3762   0.04255   0.03445  -0.0468   1.0000   0.2143
  -2.000  -0.3816   0.04518   0.03907  -0.0361   1.0000   0.5775
  -1.750  -0.3824   0.04665   0.04058  -0.0284   1.0000   0.6266
  -1.500  -0.3805   0.04752   0.04140  -0.0222   1.0000   0.6676
  -1.250  -0.3860   0.04800   0.04196  -0.0137   1.0000   0.7141
  -1.000  -0.3848   0.04869   0.04263  -0.0063   0.9957   0.7624
  -0.750  -0.3740   0.04918   0.04294  -0.0028   0.9905   0.7960
  -0.500  -0.3472   0.05045   0.04393  -0.0037   0.9835   0.8145
  -0.250  -0.3190   0.05117   0.04432  -0.0060   0.9737   0.8264
   0.000  -0.2909   0.05205   0.04492  -0.0082   0.9640   0.8361
   0.250  -0.2604   0.05320   0.04580  -0.0112   0.9554   0.8440
   0.500  -0.2247   0.05486   0.04718  -0.0151   0.9458   0.8525
   0.750  -0.1975   0.05562   0.04771  -0.0173   0.9335   0.8599
   1.000  -0.1691   0.05665   0.04854  -0.0199   0.9215   0.8672
   1.250  -0.1400   0.05787   0.04959  -0.0225   0.9110   0.8745
   1.500  -0.1012   0.06011   0.05162  -0.0270   0.9021   0.8834
   1.750  -0.0774   0.06070   0.05210  -0.0286   0.8900   0.8913
   2.000  -0.0515   0.06177   0.05306  -0.0308   0.8789   0.9006
   2.250  -0.0190   0.06347   0.05467  -0.0343   0.8698   0.9130
   2.500   0.0254   0.06585   0.05696  -0.0400   0.8591   0.9307
   2.750   0.0573   0.06700   0.05807  -0.0439   0.8458   0.9643
   3.000   0.0778   0.06797   0.05892  -0.0456   0.8345   1.0000
   3.250   0.1084   0.07014   0.06093  -0.0492   0.8272   1.0000
   3.500   0.1399   0.07211   0.06273  -0.0527   0.8167   1.0000
   3.750   0.1599   0.07334   0.06386  -0.0543   0.8056   1.0000
   4.000   0.1926   0.07597   0.06633  -0.0580   0.7991   1.0000
   4.250   0.2170   0.07754   0.06779  -0.0602   0.7883   1.0000
   4.500   0.2348   0.07896   0.06911  -0.0614   0.7784   1.0000
   4.750   0.2742   0.08229   0.07231  -0.0657   0.7719   1.0000
   5.000   0.2851   0.08304   0.07298  -0.0658   0.7608   1.0000
   5.250   0.3067   0.08517   0.07501  -0.0675   0.7536   1.0000
   5.500   0.3334   0.08739   0.07715  -0.0696   0.7445   1.0000
   5.750   0.3457   0.08878   0.07847  -0.0698   0.7352   1.0000
   6.000   0.3790   0.09192   0.08153  -0.0727   0.7289   1.0000
   6.250   0.3851   0.09283   0.08239  -0.0721   0.7191   1.0000
   6.500   0.4200   0.09643   0.08591  -0.0750   0.7139   1.0000
   6.750   0.4233   0.09703   0.08649  -0.0740   0.7031   1.0000
   7.000   0.4480   0.10006   0.08949  -0.0756   0.6979   1.0000
   7.250   0.4580   0.10129   0.09070  -0.0754   0.6880   1.0000
   7.500   0.4728   0.10355   0.09294  -0.0759   0.6816   1.0000
   7.750   0.4917   0.10569   0.09508  -0.0766   0.6728   1.0000
   8.000   0.5009   0.10755   0.09696  -0.0765   0.6655   1.0000
   8.250   0.5233   0.11018   0.09960  -0.0776   0.6577   1.0000
   8.500   0.5291   0.11182   0.10126  -0.0772   0.6497   1.0000
   8.750   0.5533   0.11477   0.10423  -0.0784   0.6428   1.0000
   9.000   0.5567   0.11627   0.10577  -0.0779   0.6347   1.0000
   9.250   0.5822   0.11951   0.10909  -0.0793   0.6280   1.0000
   9.500   0.5830   0.12086   0.11048  -0.0787   0.6198   1.0000
   9.750   0.6083   0.12424   0.11392  -0.0800   0.6135   1.0000
  10.000   0.6082   0.12556   0.11530  -0.0794   0.6049   1.0000
  10.250   0.6345   0.12923   0.11905  -0.0808   0.5988   1.0000
  10.500   0.6324   0.13041   0.12031  -0.0803   0.5902   1.0000
  10.750   0.6594   0.13431   0.12432  -0.0817   0.5842   1.0000
  11.000   0.6560   0.13535   0.12542  -0.0812   0.5752   1.0000
  11.250   0.6840   0.13962   0.12982  -0.0826   0.5694   1.0000
  11.500   0.6788   0.14042   0.13068  -0.0822   0.5603   1.0000
  11.750   0.7079   0.14512   0.13555  -0.0837   0.5547   1.0000
  12.000   0.7009   0.14564   0.13614  -0.0833   0.5452   1.0000
  12.250   0.7323   0.15097   0.14163  -0.0850   0.5400   1.0000
  12.500   0.7223   0.15099   0.14171  -0.0846   0.5304   1.0000
  12.750   0.7466   0.15576   0.14664  -0.0859   0.5251   1.0000
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