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NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(1)-212 (naca651212-il)
Reynolds number: 500,000
Max Cl/Cd: 76.26 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca651212-il-500000.txt
Download as CSV file: xf-naca651212-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5502   0.08809   0.08579  -0.0391   1.0000   0.0238
 -10.750  -0.5912   0.07182   0.06946  -0.0523   1.0000   0.0233
 -10.500  -0.6219   0.06465   0.06217  -0.0565   1.0000   0.0232
 -10.250  -0.6432   0.06031   0.05772  -0.0576   1.0000   0.0233
 -10.000  -0.6501   0.05823   0.05562  -0.0570   1.0000   0.0236
  -9.750  -0.6664   0.05571   0.05303  -0.0550   1.0000   0.0237
  -9.500  -0.6796   0.05285   0.05005  -0.0526   1.0000   0.0238
  -9.250  -0.6808   0.05116   0.04832  -0.0507   1.0000   0.0244
  -9.000  -0.6903   0.04927   0.04636  -0.0471   1.0000   0.0248
  -8.750  -0.6779   0.04582   0.04268  -0.0484   0.9930   0.0261
  -8.250  -0.6555   0.03084   0.02605  -0.0501   0.9751   0.0225
  -8.000  -0.6230   0.02969   0.02471  -0.0517   0.9706   0.0222
  -7.750  -0.6021   0.02602   0.02066  -0.0518   0.9612   0.0223
  -7.500  -0.5789   0.02281   0.01712  -0.0518   0.9530   0.0224
  -7.250  -0.5559   0.02015   0.01421  -0.0514   0.9442   0.0228
  -7.000  -0.5328   0.01855   0.01249  -0.0508   0.9350   0.0232
  -6.750  -0.5094   0.01748   0.01133  -0.0501   0.9270   0.0239
  -6.500  -0.4865   0.01667   0.01046  -0.0494   0.9176   0.0247
  -6.250  -0.4630   0.01606   0.00978  -0.0487   0.9095   0.0258
  -6.000  -0.4395   0.01539   0.00902  -0.0479   0.9011   0.0268
  -5.750  -0.4160   0.01467   0.00822  -0.0472   0.8934   0.0276
  -5.500  -0.3923   0.01409   0.00756  -0.0465   0.8857   0.0284
  -5.250  -0.3679   0.01366   0.00707  -0.0459   0.8783   0.0290
  -5.000  -0.3486   0.01248   0.00580  -0.0446   0.8705   0.0307
  -4.750  -0.3250   0.01199   0.00528  -0.0441   0.8632   0.0328
  -4.500  -0.3004   0.01160   0.00485  -0.0436   0.8562   0.0351
  -4.250  -0.2752   0.01126   0.00443  -0.0432   0.8498   0.0370
  -4.000  -0.2507   0.01076   0.00386  -0.0428   0.8428   0.0407
  -3.750  -0.2250   0.01044   0.00350  -0.0425   0.8369   0.0463
  -3.500  -0.1993   0.01007   0.00316  -0.0422   0.8299   0.0596
  -3.250  -0.1809   0.00853   0.00255  -0.0416   0.8238   0.2921
  -3.000  -0.1618   0.00723   0.00225  -0.0409   0.8171   0.5562
  -2.750  -0.1353   0.00709   0.00224  -0.0406   0.8114   0.6108
  -2.500  -0.1078   0.00707   0.00221  -0.0405   0.8060   0.6371
  -2.250  -0.0802   0.00707   0.00221  -0.0405   0.7998   0.6605
  -2.000  -0.0530   0.00710   0.00227  -0.0402   0.7946   0.6853
  -1.750  -0.0258   0.00720   0.00236  -0.0399   0.7892   0.7080
  -1.500   0.0018   0.00725   0.00241  -0.0398   0.7836   0.7216
  -1.250   0.0296   0.00727   0.00242  -0.0397   0.7787   0.7301
  -1.000   0.0581   0.00727   0.00239  -0.0399   0.7733   0.7358
  -0.750   0.0865   0.00725   0.00236  -0.0401   0.7680   0.7404
  -0.500   0.1148   0.00727   0.00234  -0.0402   0.7635   0.7452
  -0.250   0.1434   0.00727   0.00233  -0.0405   0.7581   0.7508
   0.000   0.1717   0.00726   0.00233  -0.0406   0.7530   0.7554
   0.250   0.2001   0.00730   0.00234  -0.0407   0.7487   0.7605
   0.500   0.2286   0.00731   0.00237  -0.0410   0.7436   0.7661
   0.750   0.2568   0.00731   0.00239  -0.0411   0.7386   0.7710
   1.000   0.2852   0.00735   0.00243  -0.0413   0.7343   0.7763
   1.250   0.3137   0.00739   0.00248  -0.0415   0.7295   0.7823
   1.500   0.3417   0.00739   0.00254  -0.0416   0.7245   0.7872
   1.750   0.3700   0.00744   0.00260  -0.0417   0.7199   0.7931
   2.000   0.3979   0.00745   0.00265  -0.0418   0.7126   0.7990
   2.250   0.4251   0.00745   0.00265  -0.0415   0.7026   0.8043
   2.500   0.4521   0.00743   0.00262  -0.0413   0.6888   0.8109
   2.750   0.4782   0.00737   0.00260  -0.0408   0.6690   0.8167
   3.000   0.5044   0.00737   0.00260  -0.0404   0.6485   0.8231
   3.250   0.5308   0.00742   0.00262  -0.0401   0.6286   0.8295
   3.500   0.5568   0.00747   0.00271  -0.0397   0.6056   0.8357
   3.750   0.5819   0.00763   0.00278  -0.0391   0.5686   0.8431
   4.000   0.6020   0.00807   0.00293  -0.0377   0.4797   0.8499
   4.250   0.6099   0.00977   0.00362  -0.0349   0.2608   0.8588
   4.500   0.6183   0.01146   0.00442  -0.0322   0.0731   0.8673
   4.750   0.6384   0.01209   0.00492  -0.0309   0.0445   0.8755
   5.000   0.6605   0.01249   0.00538  -0.0299   0.0385   0.8844
   5.250   0.6804   0.01299   0.00592  -0.0285   0.0342   0.8932
   5.500   0.6997   0.01355   0.00657  -0.0270   0.0319   0.9034
   5.750   0.7196   0.01393   0.00703  -0.0256   0.0300   0.9138
   6.000   0.7378   0.01434   0.00749  -0.0238   0.0282   0.9252
   6.250   0.7533   0.01485   0.00805  -0.0216   0.0266   0.9396
   6.500   0.7646   0.01584   0.00913  -0.0188   0.0253   0.9595
   6.750   0.7919   0.01676   0.01014  -0.0193   0.0246   0.9794
   7.000   0.8199   0.01750   0.01094  -0.0200   0.0239   1.0000
   7.250   0.8436   0.01834   0.01183  -0.0197   0.0231   1.0000
   7.500   0.8673   0.01922   0.01275  -0.0195   0.0223   1.0000
   7.750   0.8910   0.02002   0.01359  -0.0192   0.0214   1.0000
   8.000   0.9145   0.02093   0.01454  -0.0189   0.0207   1.0000
   8.250   0.9383   0.02206   0.01570  -0.0187   0.0202   1.0000
   8.500   0.9630   0.02361   0.01730  -0.0187   0.0197   1.0000
   8.750   0.9892   0.02610   0.01992  -0.0190   0.0193   1.0000
   9.000   1.0124   0.02906   0.02311  -0.0188   0.0191   1.0000
   9.250   1.0303   0.03259   0.02695  -0.0179   0.0190   1.0000
   9.500   1.0437   0.03345   0.02807  -0.0161   0.0186   1.0000
   9.750   1.0572   0.03500   0.02988  -0.0144   0.0182   1.0000
  10.000   1.0646   0.03812   0.03332  -0.0123   0.0182   1.0000
  10.250   1.0657   0.04200   0.03750  -0.0098   0.0184   1.0000
  12.000   0.8393   0.07510   0.07253   0.0076   0.0250   1.0000
  12.250   0.8293   0.07807   0.07560   0.0067   0.0252   1.0000
  12.500   0.8123   0.08235   0.08000   0.0048   0.0254   1.0000
  12.750   0.6791   0.11396   0.11206  -0.0173   0.0272   1.0000
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