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GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GRUMMAN K-2 AIRFOIL (k2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 60.36 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k2-il-1000000.txt
Download as CSV file: xf-k2-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GRUMMAN K-2 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.9859   0.05546   0.05249  -0.0571   1.0000   0.0127
 -12.750  -1.0036   0.05097   0.04783  -0.0578   1.0000   0.0126
 -12.500  -1.0182   0.04739   0.04411  -0.0574   1.0000   0.0126
 -12.250  -1.0322   0.04426   0.04083  -0.0562   1.0000   0.0126
 -12.000  -1.0436   0.04170   0.03812  -0.0542   1.0000   0.0125
 -11.750  -1.0557   0.03933   0.03561  -0.0516   1.0000   0.0125
 -11.500  -1.0673   0.03725   0.03339  -0.0483   1.0000   0.0125
 -11.250  -1.0794   0.03545   0.03146  -0.0443   1.0000   0.0125
 -11.000  -1.0938   0.03406   0.02995  -0.0393   1.0000   0.0125
 -10.750  -1.1030   0.03244   0.02819  -0.0351   1.0000   0.0125
 -10.500  -1.1064   0.03013   0.02568  -0.0323   1.0000   0.0125
 -10.250  -1.1049   0.02785   0.02318  -0.0298   1.0000   0.0126
 -10.000  -1.0987   0.02584   0.02099  -0.0276   1.0000   0.0127
  -9.750  -1.0873   0.02436   0.01938  -0.0259   1.0000   0.0128
  -9.500  -1.0727   0.02320   0.01813  -0.0245   1.0000   0.0129
  -9.250  -1.0560   0.02225   0.01710  -0.0234   1.0000   0.0131
  -9.000  -1.0378   0.02140   0.01619  -0.0224   1.0000   0.0132
  -8.750  -1.0184   0.02064   0.01536  -0.0215   1.0000   0.0134
  -8.500  -0.9926   0.01986   0.01452  -0.0219   0.9995   0.0136
  -8.250  -0.9646   0.01909   0.01368  -0.0227   0.9988   0.0138
  -8.000  -0.9357   0.01836   0.01287  -0.0236   0.9979   0.0141
  -7.750  -0.9064   0.01766   0.01211  -0.0246   0.9970   0.0143
  -7.500  -0.8765   0.01699   0.01139  -0.0256   0.9962   0.0146
  -7.250  -0.8461   0.01639   0.01073  -0.0267   0.9954   0.0148
  -7.000  -0.8157   0.01583   0.01012  -0.0277   0.9948   0.0150
  -6.750  -0.7852   0.01537   0.00962  -0.0287   0.9943   0.0152
  -6.500  -0.7552   0.01453   0.00873  -0.0299   0.9939   0.0156
  -6.250  -0.7277   0.01388   0.00805  -0.0304   0.9929   0.0160
  -6.000  -0.6988   0.01346   0.00763  -0.0310   0.9919   0.0165
  -5.750  -0.6688   0.01309   0.00725  -0.0318   0.9908   0.0170
  -5.500  -0.6379   0.01275   0.00690  -0.0328   0.9898   0.0177
  -5.250  -0.6065   0.01245   0.00658  -0.0338   0.9889   0.0183
  -5.000  -0.5748   0.01196   0.00607  -0.0351   0.9882   0.0193
  -4.750  -0.5430   0.01168   0.00581  -0.0362   0.9875   0.0204
  -4.500  -0.5109   0.01146   0.00559  -0.0373   0.9869   0.0217
  -4.250  -0.4778   0.01113   0.00528  -0.0387   0.9863   0.0236
  -4.000  -0.4444   0.01093   0.00510  -0.0401   0.9857   0.0256
  -3.750  -0.4104   0.01065   0.00484  -0.0416   0.9852   0.0283
  -3.500  -0.3766   0.01047   0.00468  -0.0431   0.9847   0.0312
  -3.250  -0.3426   0.01025   0.00450  -0.0446   0.9843   0.0358
  -3.000  -0.3082   0.01005   0.00435  -0.0462   0.9839   0.0427
  -2.750  -0.2774   0.00976   0.00416  -0.0471   0.9827   0.0563
  -2.500  -0.2460   0.00935   0.00395  -0.0482   0.9815   0.0962
  -2.250  -0.2059   0.00860   0.00372  -0.0518   0.9824   0.2152
  -2.000  -0.1623   0.00784   0.00352  -0.0561   0.9838   0.3552
  -1.750  -0.1191   0.00687   0.00324  -0.0606   0.9847   0.5326
  -1.500  -0.0755   0.00639   0.00315  -0.0644   0.9846   0.6411
  -1.250  -0.0366   0.00617   0.00304  -0.0666   0.9805   0.6792
  -1.000   0.0087   0.00587   0.00279  -0.0699   0.9750   0.7022
  -0.750   0.0566   0.00567   0.00267  -0.0738   0.9723   0.7283
  -0.500   0.0879   0.00550   0.00251  -0.0741   0.9651   0.7372
  -0.250   0.1280   0.00530   0.00233  -0.0764   0.9613   0.7420
   0.000   0.1616   0.00521   0.00225  -0.0773   0.9577   0.7469
   0.250   0.1896   0.00513   0.00216  -0.0771   0.9496   0.7508
   0.500   0.2202   0.00502   0.00209  -0.0773   0.9419   0.7543
   0.750   0.2516   0.00496   0.00204  -0.0777   0.9289   0.7581
   1.000   0.2863   0.00493   0.00194  -0.0786   0.8908   0.7631
   1.250   0.3116   0.00541   0.00193  -0.0775   0.7692   0.7674
   1.500   0.3252   0.00643   0.00217  -0.0744   0.5761   0.7706
   1.750   0.3459   0.00717   0.00239  -0.0729   0.4377   0.7729
   2.000   0.3692   0.00778   0.00258  -0.0721   0.3307   0.7750
   2.250   0.3940   0.00829   0.00275  -0.0715   0.2390   0.7772
   2.500   0.4198   0.00875   0.00291  -0.0712   0.1699   0.7793
   2.750   0.4467   0.00909   0.00306  -0.0710   0.1296   0.7815
   3.000   0.4748   0.00931   0.00319  -0.0710   0.1098   0.7834
   3.250   0.5030   0.00953   0.00333  -0.0711   0.0952   0.7850
   3.500   0.5304   0.00970   0.00345  -0.0709   0.0822   0.7870
   3.750   0.5573   0.00994   0.00361  -0.0707   0.0666   0.7885
   4.000   0.5830   0.01036   0.00386  -0.0702   0.0346   0.7900
   4.250   0.6091   0.01077   0.00420  -0.0698   0.0208   0.7916
   4.500   0.6358   0.01110   0.00449  -0.0694   0.0167   0.7932
   4.750   0.6630   0.01140   0.00481  -0.0692   0.0150   0.7949
   5.000   0.6900   0.01172   0.00513  -0.0689   0.0138   0.7966
   5.250   0.7168   0.01214   0.00556  -0.0686   0.0129   0.7984
   5.500   0.7441   0.01247   0.00591  -0.0684   0.0123   0.8001
   5.750   0.7712   0.01284   0.00629  -0.0682   0.0117   0.8014
   6.000   0.7979   0.01322   0.00668  -0.0680   0.0113   0.8029
   6.250   0.8234   0.01370   0.00720  -0.0674   0.0109   0.8044
   6.500   0.8474   0.01441   0.00797  -0.0666   0.0106   0.8058
   6.750   0.8710   0.01520   0.00882  -0.0657   0.0105   0.8071
   7.000   0.8964   0.01566   0.00934  -0.0652   0.0103   0.8084
   7.250   0.9216   0.01617   0.00990  -0.0646   0.0102   0.8098
   7.500   0.9465   0.01674   0.01053  -0.0640   0.0101   0.8114
   7.750   0.9711   0.01738   0.01123  -0.0634   0.0099   0.8130
   8.000   0.9952   0.01812   0.01205  -0.0627   0.0098   0.8145
   8.250   1.0190   0.01895   0.01295  -0.0620   0.0098   0.8160
   8.500   1.0425   0.01984   0.01393  -0.0612   0.0097   0.8173
   8.750   1.0655   0.02082   0.01501  -0.0604   0.0097   0.8185
   9.000   1.0878   0.02185   0.01616  -0.0594   0.0097   0.8199
   9.250   1.1087   0.02299   0.01745  -0.0583   0.0096   0.8214
   9.500   1.1288   0.02420   0.01882  -0.0570   0.0096   0.8227
   9.750   1.1475   0.02562   0.02042  -0.0555   0.0096   0.8239
  10.000   1.1646   0.02721   0.02222  -0.0539   0.0096   0.8252
  10.250   1.1800   0.02896   0.02419  -0.0520   0.0096   0.8265
  10.500   1.1924   0.03107   0.02656  -0.0499   0.0096   0.8279
  10.750   1.2021   0.03337   0.02912  -0.0474   0.0096   0.8294
  11.000   1.2071   0.03608   0.03213  -0.0445   0.0096   0.8311
  11.250   1.2055   0.03931   0.03569  -0.0411   0.0096   0.8327
  11.500   1.1976   0.04284   0.03953  -0.0372   0.0096   0.8342
  11.750   1.1756   0.04666   0.04365  -0.0317   0.0097   0.8355
  12.000   1.1485   0.05074   0.04800  -0.0270   0.0098   0.8373
  12.250   1.1187   0.05564   0.05315  -0.0243   0.0098   0.8388
  12.500   1.0889   0.06177   0.05951  -0.0250   0.0099   0.8401
  12.750   1.0541   0.07260   0.07057  -0.0338   0.0100   0.8415
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