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

Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il)
Reynolds number: 500,000
Max Cl/Cd: 92.31 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-apex16-il-500000-n5.txt
Download as CSV file: xf-apex16-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Apex 16 (normalized using XFOIL date021206)     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3345   0.08292   0.08050  -0.0783   0.9828   0.0120
  -9.750  -0.3343   0.07616   0.07375  -0.0848   0.9798   0.0119
  -9.500  -0.3364   0.06903   0.06657  -0.0936   0.9771   0.0118
  -9.250  -0.3436   0.06397   0.06144  -0.0992   0.9710   0.0116
  -9.000  -0.3461   0.05922   0.05657  -0.1049   0.9669   0.0114
  -8.750  -0.3502   0.05493   0.05213  -0.1067   0.9591   0.0115
  -8.500  -0.3409   0.05046   0.04746  -0.1099   0.9561   0.0114
  -8.250  -0.3378   0.04660   0.04341  -0.1097   0.9487   0.0116
  -8.000  -0.3239   0.04263   0.03920  -0.1109   0.9449   0.0117
  -7.750  -0.3141   0.03942   0.03577  -0.1099   0.9380   0.0119
  -7.500  -0.2982   0.03613   0.03224  -0.1098   0.9334   0.0120
  -7.000  -0.2692   0.02922   0.02474  -0.1074   0.9219   0.0127
  -6.750  -0.2488   0.02606   0.02127  -0.1071   0.9181   0.0126
  -6.500  -0.2349   0.02357   0.01851  -0.1052   0.9109   0.0127
  -6.250  -0.2137   0.02114   0.01580  -0.1047   0.9056   0.0128
  -6.000  -0.1922   0.01988   0.01437  -0.1041   0.8993   0.0132
  -5.750  -0.1687   0.01850   0.01282  -0.1035   0.8930   0.0134
  -5.500  -0.1419   0.01758   0.01177  -0.1038   0.8888   0.0138
  -5.250  -0.1196   0.01668   0.01076  -0.1029   0.8828   0.0141
  -5.000  -0.0940   0.01582   0.00980  -0.1027   0.8777   0.0145
  -4.750  -0.0675   0.01494   0.00880  -0.1027   0.8735   0.0148
  -4.500  -0.0440   0.01426   0.00806  -0.1020   0.8675   0.0152
  -4.250  -0.0182   0.01372   0.00745  -0.1018   0.8625   0.0160
  -4.000   0.0067   0.01308   0.00673  -0.1013   0.8577   0.0164
  -3.750   0.0296   0.01244   0.00603  -0.1005   0.8517   0.0166
  -3.500   0.0540   0.01187   0.00538  -0.1000   0.8466   0.0170
  -3.250   0.0771   0.01141   0.00487  -0.0992   0.8411   0.0173
  -3.000   0.1011   0.01104   0.00444  -0.0986   0.8355   0.0178
  -2.750   0.1267   0.01073   0.00406  -0.0983   0.8306   0.0182
  -2.500   0.1488   0.01028   0.00354  -0.0974   0.8246   0.0187
  -2.250   0.1729   0.00987   0.00305  -0.0968   0.8192   0.0198
  -2.000   0.1982   0.00962   0.00276  -0.0965   0.8140   0.0213
  -1.750   0.2236   0.00945   0.00256  -0.0961   0.8081   0.0229
  -1.500   0.2504   0.00931   0.00235  -0.0960   0.8030   0.0240
  -1.250   0.2759   0.00918   0.00219  -0.0956   0.7970   0.0256
  -1.000   0.3022   0.00909   0.00204  -0.0954   0.7910   0.0277
  -0.750   0.3284   0.00899   0.00193  -0.0952   0.7850   0.0375
  -0.500   0.3525   0.00869   0.00185  -0.0946   0.7781   0.1318
  -0.250   0.3701   0.00769   0.00167  -0.0933   0.7714   0.4425
   0.250   0.4180   0.00737   0.00170  -0.0920   0.7565   0.5589
   0.500   0.4427   0.00731   0.00173  -0.0915   0.7483   0.5891
   0.750   0.4680   0.00730   0.00175  -0.0910   0.7404   0.6094
   1.000   0.4936   0.00731   0.00176  -0.0906   0.7316   0.6200
   1.250   0.5189   0.00733   0.00179  -0.0901   0.7226   0.6313
   1.500   0.5442   0.00736   0.00182  -0.0897   0.7136   0.6425
   1.750   0.5692   0.00738   0.00186  -0.0892   0.7035   0.6540
   2.000   0.5940   0.00742   0.00191  -0.0886   0.6930   0.6658
   2.250   0.6183   0.00747   0.00197  -0.0879   0.6816   0.6768
   2.500   0.6423   0.00753   0.00204  -0.0872   0.6693   0.6881
   2.750   0.6657   0.00761   0.00211  -0.0863   0.6556   0.7000
   3.000   0.6882   0.00770   0.00219  -0.0853   0.6389   0.7123
   3.250   0.7080   0.00786   0.00229  -0.0836   0.6146   0.7242
   3.500   0.7269   0.00805   0.00242  -0.0819   0.5884   0.7360
   3.750   0.7465   0.00822   0.00255  -0.0802   0.5673   0.7489
   4.000   0.7677   0.00835   0.00270  -0.0789   0.5504   0.7627
   4.250   0.7865   0.00852   0.00287  -0.0772   0.5270   0.7785
   4.500   0.8009   0.00880   0.00306  -0.0745   0.4908   0.7960
   4.750   0.8117   0.00916   0.00330  -0.0711   0.4487   0.8163
   5.000   0.8211   0.00957   0.00357  -0.0675   0.4047   0.8367
   5.250   0.8330   0.00997   0.00385  -0.0644   0.3659   0.8577
   5.500   0.8466   0.01035   0.00415  -0.0618   0.3322   0.8792
   5.750   0.8649   0.01075   0.00449  -0.0602   0.2941   0.9102
   6.000   0.9050   0.01173   0.00517  -0.0642   0.2185   1.0000
   6.250   0.9175   0.01234   0.00558  -0.0617   0.1786   1.0000
   6.500   0.9293   0.01302   0.00603  -0.0590   0.1387   1.0000
   6.750   0.9430   0.01362   0.00648  -0.0568   0.1098   1.0000
   7.000   0.9581   0.01416   0.00691  -0.0548   0.0881   1.0000
   7.250   0.9706   0.01486   0.00746  -0.0525   0.0576   1.0000
   7.500   0.9826   0.01560   0.00806  -0.0501   0.0349   1.0000
   7.750   0.9983   0.01615   0.00859  -0.0483   0.0278   1.0000
   8.000   1.0150   0.01665   0.00911  -0.0466   0.0247   1.0000
   8.250   1.0322   0.01713   0.00963  -0.0451   0.0232   1.0000
   8.500   1.0485   0.01766   0.01020  -0.0436   0.0217   1.0000
   8.750   1.0638   0.01827   0.01085  -0.0419   0.0201   1.0000
   9.000   1.0778   0.01896   0.01159  -0.0400   0.0188   1.0000
   9.250   1.0930   0.01958   0.01227  -0.0384   0.0179   1.0000
   9.500   1.1086   0.02018   0.01293  -0.0369   0.0172   1.0000
   9.750   1.1233   0.02085   0.01366  -0.0353   0.0164   1.0000
  10.000   1.1374   0.02156   0.01443  -0.0337   0.0156   1.0000
  10.250   1.1505   0.02236   0.01527  -0.0320   0.0147   1.0000
  10.500   1.1625   0.02323   0.01620  -0.0303   0.0138   1.0000
  10.750   1.1697   0.02446   0.01750  -0.0280   0.0129   1.0000
  11.000   1.1841   0.02520   0.01832  -0.0267   0.0125   1.0000
  11.250   1.1960   0.02613   0.01933  -0.0251   0.0120   1.0000
  11.500   1.2073   0.02713   0.02041  -0.0235   0.0115   1.0000
  11.750   1.2180   0.02820   0.02155  -0.0220   0.0109   1.0000
  12.000   1.2280   0.02933   0.02276  -0.0205   0.0105   1.0000
  12.250   1.2380   0.03048   0.02398  -0.0191   0.0100   1.0000
  12.500   1.2483   0.03164   0.02520  -0.0178   0.0094   1.0000
  12.750   1.2543   0.03318   0.02680  -0.0163   0.0090   1.0000
  13.000   1.2576   0.03497   0.02868  -0.0146   0.0085   1.0000
  13.250   1.2657   0.03641   0.03025  -0.0134   0.0083   1.0000
  13.500   1.2753   0.03775   0.03168  -0.0125   0.0078   1.0000
  13.750   1.2799   0.03958   0.03363  -0.0112   0.0076   1.0000
  14.000   1.2844   0.04146   0.03561  -0.0102   0.0073   1.0000
  14.250   1.2886   0.04343   0.03769  -0.0092   0.0071   1.0000
  14.500   1.2923   0.04552   0.03988  -0.0084   0.0069   1.0000
  14.750   1.2967   0.04760   0.04206  -0.0078   0.0066   1.0000
  15.000   1.2983   0.05003   0.04460  -0.0073   0.0064   1.0000
  15.250   1.2997   0.05257   0.04725  -0.0069   0.0064   1.0000
  15.500   1.3013   0.05517   0.04994  -0.0067   0.0061   1.0000
  15.750   1.3005   0.05815   0.05302  -0.0067   0.0059   1.0000
  16.000   1.2957   0.06173   0.05672  -0.0069   0.0057   1.0000
  16.250   1.2901   0.06553   0.06066  -0.0072   0.0057   1.0000
  16.500   1.2833   0.06964   0.06490  -0.0079   0.0056   1.0000
  16.750   1.2756   0.07404   0.06945  -0.0088   0.0055   1.0000
  17.000   1.2676   0.07862   0.07418  -0.0100   0.0055   1.0000
  17.250   1.2611   0.08315   0.07886  -0.0114   0.0054   1.0000
  17.500   1.2508   0.08841   0.08430  -0.0133   0.0054   1.0000
  17.750   1.2410   0.09381   0.08985  -0.0154   0.0054   1.0000
  18.000   1.2304   0.09952   0.09571  -0.0179   0.0053   1.0000
  18.250   1.2184   0.10561   0.10196  -0.0206   0.0053   1.0000
  18.500   1.2051   0.11216   0.10866  -0.0238   0.0052   1.0000
  18.750   1.1915   0.11896   0.11562  -0.0273   0.0052   1.0000
  19.000   1.1778   0.12600   0.12281  -0.0312   0.0051   1.0000
<< Back to Apex 16 (normalized using XFOIL date021206) (apex16-il)

Polar data table (+)

Polar graphs


<< Back to Apex 16 (normalized using XFOIL date021206) (apex16-il)