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NACA 65(1)-212 a=0.6 (naca651212a06-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(1)-212 a=0.6 (naca651212a06-il)
Reynolds number: 500,000
Max Cl/Cd: 81.46 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca651212a06-il-500000.txt
Download as CSV file: xf-naca651212a06-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212 a=0.6                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5238   0.08557   0.08339  -0.0379   1.0000   0.0236
 -10.250  -0.5323   0.07867   0.07653  -0.0431   1.0000   0.0240
 -10.000  -0.5597   0.06833   0.06615  -0.0524   1.0000   0.0238
  -9.750  -0.5842   0.06240   0.06014  -0.0562   1.0000   0.0236
  -9.500  -0.6006   0.05748   0.05509  -0.0587   0.9760   0.0235
  -9.250  -0.5991   0.05343   0.05082  -0.0610   0.9496   0.0243
  -9.000  -0.6066   0.05032   0.04748  -0.0591   0.9293   0.0249
  -8.750  -0.6113   0.04721   0.04412  -0.0566   0.9148   0.0256
  -8.500  -0.6064   0.04681   0.04322  -0.0531   0.9021   0.0278
  -8.250  -0.6037   0.04418   0.04027  -0.0509   0.8923   0.0279
  -8.000  -0.6304   0.03042   0.02549  -0.0458   0.8830   0.0218
  -7.750  -0.6160   0.02749   0.02224  -0.0444   0.8755   0.0220
  -7.500  -0.5985   0.02537   0.01992  -0.0433   0.8697   0.0226
  -7.250  -0.5786   0.02290   0.01710  -0.0422   0.8632   0.0224
  -7.000  -0.5567   0.02121   0.01521  -0.0414   0.8574   0.0227
  -6.750  -0.5335   0.01990   0.01373  -0.0408   0.8523   0.0231
  -6.500  -0.5090   0.01884   0.01258  -0.0404   0.8466   0.0238
  -6.250  -0.4844   0.01797   0.01159  -0.0399   0.8415   0.0247
  -6.000  -0.4594   0.01719   0.01069  -0.0395   0.8368   0.0258
  -5.750  -0.4340   0.01627   0.00967  -0.0391   0.8313   0.0265
  -5.500  -0.4087   0.01555   0.00885  -0.0387   0.8266   0.0272
  -5.250  -0.3832   0.01501   0.00821  -0.0383   0.8224   0.0278
  -5.000  -0.3607   0.01372   0.00686  -0.0375   0.8174   0.0289
  -4.750  -0.3375   0.01298   0.00610  -0.0369   0.8128   0.0308
  -4.500  -0.3129   0.01254   0.00560  -0.0364   0.8087   0.0325
  -4.250  -0.2877   0.01209   0.00512  -0.0361   0.8040   0.0341
  -4.000  -0.2621   0.01171   0.00468  -0.0358   0.7995   0.0358
  -3.750  -0.2373   0.01124   0.00413  -0.0353   0.7956   0.0380
  -3.500  -0.2118   0.01085   0.00371  -0.0350   0.7919   0.0429
  -3.250  -0.1851   0.01059   0.00343  -0.0349   0.7874   0.0475
  -3.000  -0.1595   0.01015   0.00305  -0.0346   0.7832   0.0682
  -2.750  -0.1436   0.00840   0.00249  -0.0335   0.7794   0.3731
  -2.500  -0.1234   0.00759   0.00243  -0.0324   0.7756   0.5764
  -2.250  -0.0968   0.00747   0.00241  -0.0322   0.7715   0.6185
  -2.000  -0.0696   0.00742   0.00237  -0.0320   0.7676   0.6449
  -1.750  -0.0427   0.00741   0.00237  -0.0318   0.7642   0.6734
  -1.500  -0.0160   0.00740   0.00243  -0.0314   0.7606   0.6999
  -1.250   0.0106   0.00742   0.00253  -0.0311   0.7566   0.7239
  -1.000   0.0381   0.00748   0.00258  -0.0309   0.7529   0.7380
  -0.750   0.0662   0.00754   0.00258  -0.0309   0.7495   0.7481
  -0.500   0.0944   0.00756   0.00259  -0.0311   0.7462   0.7537
  -0.250   0.1228   0.00757   0.00260  -0.0313   0.7422   0.7604
   0.000   0.1511   0.00757   0.00258  -0.0315   0.7384   0.7664
   0.250   0.1794   0.00758   0.00257  -0.0316   0.7351   0.7730
   0.500   0.2077   0.00760   0.00256  -0.0318   0.7319   0.7797
   0.750   0.2358   0.00756   0.00257  -0.0319   0.7279   0.7865
   1.000   0.2639   0.00752   0.00255  -0.0321   0.7241   0.7938
   1.250   0.2919   0.00746   0.00251  -0.0322   0.7207   0.8014
   1.500   0.3198   0.00742   0.00250  -0.0323   0.7175   0.8097
   1.750   0.3474   0.00733   0.00252  -0.0323   0.7136   0.8193
   2.000   0.3740   0.00727   0.00262  -0.0321   0.7095   0.8302
   2.250   0.3988   0.00734   0.00282  -0.0311   0.7051   0.8421
   2.500   0.4220   0.00751   0.00309  -0.0297   0.6999   0.8547
   2.750   0.4509   0.00759   0.00313  -0.0301   0.6904   0.8965
   3.000   0.4763   0.00755   0.00308  -0.0294   0.6776   0.9073
   3.250   0.5008   0.00746   0.00300  -0.0286   0.6622   0.9167
   3.500   0.5246   0.00736   0.00289  -0.0275   0.6441   0.9253
   3.750   0.5484   0.00730   0.00285  -0.0265   0.6266   0.9339
   4.000   0.5725   0.00728   0.00285  -0.0256   0.6060   0.9421
   4.250   0.5971   0.00733   0.00286  -0.0248   0.5752   0.9497
   4.500   0.6189   0.00764   0.00294  -0.0237   0.5048   0.9577
   4.750   0.6299   0.00934   0.00364  -0.0217   0.2918   0.9677
   5.000   0.6462   0.01146   0.00468  -0.0214   0.0751   0.9758
   5.250   0.6750   0.01223   0.00530  -0.0223   0.0436   0.9820
   5.500   0.7073   0.01291   0.00596  -0.0238   0.0357   0.9864
   5.750   0.7397   0.01343   0.00653  -0.0253   0.0320   0.9909
   6.000   0.7673   0.01429   0.00741  -0.0261   0.0288   0.9970
   6.250   0.7875   0.01510   0.00827  -0.0252   0.0274   1.0000
   6.500   0.8005   0.01557   0.00879  -0.0227   0.0265   1.0000
   6.750   0.8126   0.01613   0.00940  -0.0201   0.0257   1.0000
   7.000   0.8262   0.01671   0.01002  -0.0178   0.0246   1.0000
   7.250   0.8412   0.01732   0.01064  -0.0158   0.0236   1.0000
   7.500   0.8563   0.01801   0.01134  -0.0140   0.0227   1.0000
   7.750   0.8696   0.01913   0.01248  -0.0119   0.0218   1.0000
   8.000   0.8905   0.02093   0.01434  -0.0112   0.0211   1.0000
   8.250   0.9118   0.02173   0.01522  -0.0103   0.0208   1.0000
   8.500   0.9349   0.02284   0.01642  -0.0098   0.0205   1.0000
   8.750   0.9576   0.02395   0.01764  -0.0092   0.0200   1.0000
   9.000   0.9815   0.02546   0.01929  -0.0089   0.0197   1.0000
   9.250   1.0025   0.02679   0.02077  -0.0081   0.0191   1.0000
   9.500   1.0216   0.02805   0.02216  -0.0072   0.0184   1.0000
   9.750   1.0408   0.03012   0.02445  -0.0063   0.0182   1.0000
  10.000   1.0565   0.03261   0.02720  -0.0049   0.0182   1.0000
  10.250   1.0652   0.03647   0.03147  -0.0028   0.0186   1.0000
  10.500   1.0651   0.04058   0.03597   0.0002   0.0193   1.0000
  10.750   1.0567   0.04533   0.04103   0.0035   0.0203   1.0000
  11.000   1.0116   0.05393   0.05041   0.0116   0.0252   1.0000
  11.250   0.9992   0.05628   0.05291   0.0145   0.0247   1.0000
  11.500   0.9832   0.05929   0.05609   0.0167   0.0243   1.0000
  11.750   0.9701   0.06214   0.05906   0.0181   0.0239   1.0000
  12.000   0.9476   0.06641   0.06351   0.0190   0.0239   1.0000
  12.250   0.9254   0.07099   0.06824   0.0188   0.0239   1.0000
  12.500   0.9080   0.07533   0.07269   0.0178   0.0235   1.0000
  12.750   0.8700   0.08351   0.08106   0.0145   0.0240   1.0000
  13.000   0.8328   0.09330   0.09100   0.0088   0.0247   1.0000
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