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GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GRUMMAN K-2 AIRFOIL (k2-il)
Reynolds number: 200,000
Max Cl/Cd: 35.06 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k2-il-200000-n5.txt
Download as CSV file: xf-k2-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.8299   0.06246   0.05741  -0.0515   1.0000   0.0185
 -10.750  -0.8516   0.05800   0.05278  -0.0517   1.0000   0.0185
 -10.500  -0.8729   0.05418   0.04876  -0.0505   1.0000   0.0185
 -10.250  -0.8929   0.05100   0.04539  -0.0480   1.0000   0.0185
 -10.000  -0.9131   0.04838   0.04258  -0.0443   1.0000   0.0185
  -9.750  -0.9308   0.04598   0.03997  -0.0402   1.0000   0.0185
  -9.500  -0.9378   0.04343   0.03722  -0.0376   1.0000   0.0186
  -9.250  -0.9384   0.04123   0.03482  -0.0352   1.0000   0.0186
  -9.000  -0.9348   0.03920   0.03261  -0.0331   1.0000   0.0188
  -8.750  -0.9275   0.03740   0.03064  -0.0313   1.0000   0.0189
  -8.500  -0.9172   0.03586   0.02896  -0.0297   1.0000   0.0192
  -8.250  -0.9049   0.03443   0.02737  -0.0282   1.0000   0.0195
  -8.000  -0.8910   0.03301   0.02579  -0.0269   1.0000   0.0199
  -7.750  -0.8760   0.03149   0.02406  -0.0256   1.0000   0.0204
  -7.500  -0.8597   0.02987   0.02220  -0.0244   1.0000   0.0209
  -7.250  -0.8420   0.02826   0.02033  -0.0232   1.0000   0.0214
  -7.000  -0.8229   0.02678   0.01861  -0.0221   1.0000   0.0217
  -6.750  -0.8029   0.02548   0.01709  -0.0210   1.0000   0.0221
  -6.500  -0.7826   0.02435   0.01593  -0.0201   1.0000   0.0225
  -6.250  -0.7616   0.02344   0.01499  -0.0193   1.0000   0.0229
  -6.000  -0.7401   0.02260   0.01410  -0.0186   1.0000   0.0235
  -5.750  -0.7181   0.02178   0.01322  -0.0179   1.0000   0.0242
  -5.500  -0.6955   0.02097   0.01235  -0.0172   1.0000   0.0250
  -5.250  -0.6723   0.02022   0.01151  -0.0167   1.0000   0.0260
  -5.000  -0.6487   0.01953   0.01084  -0.0164   1.0000   0.0271
  -4.750  -0.6244   0.01898   0.01030  -0.0162   1.0000   0.0287
  -4.500  -0.5994   0.01841   0.00967  -0.0160   1.0000   0.0305
  -4.250  -0.5738   0.01775   0.00904  -0.0161   1.0000   0.0320
  -4.000  -0.5475   0.01721   0.00850  -0.0163   1.0000   0.0340
  -3.750  -0.5206   0.01672   0.00799  -0.0166   1.0000   0.0368
  -3.500  -0.4934   0.01628   0.00758  -0.0169   1.0000   0.0405
  -3.250  -0.4653   0.01582   0.00712  -0.0174   1.0000   0.0448
  -3.000  -0.4370   0.01542   0.00675  -0.0179   1.0000   0.0510
  -2.750  -0.4080   0.01501   0.00640  -0.0186   1.0000   0.0610
  -2.500  -0.3779   0.01454   0.00607  -0.0196   1.0000   0.0822
  -2.250  -0.3432   0.01370   0.00570  -0.0220   1.0000   0.1681
  -2.000  -0.2987   0.01239   0.00529  -0.0272   1.0000   0.3573
  -1.750  -0.2555   0.01131   0.00542  -0.0312   1.0000   0.5955
  -1.500  -0.2363   0.01155   0.00594  -0.0288   1.0000   0.6669
  -1.250  -0.2170   0.01194   0.00643  -0.0264   1.0000   0.7069
  -1.000  -0.1905   0.01255   0.00708  -0.0253   0.9970   0.7393
  -0.750  -0.1604   0.01302   0.00754  -0.0253   0.9945   0.7544
  -0.500  -0.1306   0.01328   0.00778  -0.0254   0.9912   0.7606
  -0.250  -0.0946   0.01342   0.00787  -0.0271   0.9880   0.7688
   0.000  -0.0646   0.01382   0.00830  -0.0269   0.9842   0.7741
   0.250  -0.0321   0.01400   0.00847  -0.0276   0.9786   0.7823
   0.500   0.0104   0.01405   0.00853  -0.0304   0.9723   0.7866
   0.750   0.0487   0.01391   0.00840  -0.0320   0.9609   0.7886
   1.000   0.0845   0.01371   0.00823  -0.0331   0.9494   0.7908
   1.250   0.1241   0.01336   0.00790  -0.0349   0.9341   0.7930
   1.500   0.1614   0.01292   0.00749  -0.0361   0.9145   0.7955
   1.750   0.1914   0.01269   0.00730  -0.0363   0.8964   0.7991
   2.000   0.2266   0.01242   0.00705  -0.0376   0.8740   0.8024
   2.250   0.2867   0.01197   0.00655  -0.0433   0.8160   0.8029
   2.500   0.3392   0.01261   0.00615  -0.0472   0.5797   0.8034
   2.750   0.3545   0.01341   0.00639  -0.0445   0.4492   0.8053
   3.000   0.3737   0.01408   0.00661  -0.0428   0.3450   0.8073
   3.250   0.3964   0.01459   0.00682  -0.0419   0.2748   0.8097
   3.500   0.4208   0.01510   0.00704  -0.0415   0.2117   0.8123
   3.750   0.4475   0.01553   0.00725  -0.0416   0.1660   0.8150
   4.000   0.4766   0.01590   0.00746  -0.0422   0.1340   0.8179
   4.250   0.5030   0.01626   0.00770  -0.0421   0.1092   0.8200
   4.500   0.5270   0.01660   0.00796  -0.0413   0.0892   0.8215
   4.750   0.5520   0.01694   0.00823  -0.0408   0.0693   0.8231
   5.000   0.5770   0.01740   0.00856  -0.0403   0.0453   0.8249
   5.250   0.6017   0.01799   0.00904  -0.0398   0.0330   0.8270
   5.500   0.6275   0.01857   0.00962  -0.0395   0.0278   0.8294
   5.750   0.6545   0.01915   0.01024  -0.0394   0.0248   0.8317
   6.000   0.6819   0.01980   0.01091  -0.0396   0.0229   0.8338
   6.250   0.7095   0.02038   0.01158  -0.0398   0.0211   0.8359
   6.500   0.7324   0.02095   0.01217  -0.0388   0.0197   0.8374
   6.750   0.7556   0.02157   0.01288  -0.0380   0.0184   0.8390
   7.000   0.7794   0.02223   0.01363  -0.0373   0.0174   0.8407
   7.250   0.8032   0.02298   0.01444  -0.0367   0.0167   0.8424
   7.500   0.8270   0.02384   0.01533  -0.0362   0.0162   0.8441
   7.750   0.8509   0.02485   0.01645  -0.0357   0.0158   0.8462
   8.000   0.8755   0.02596   0.01772  -0.0353   0.0154   0.8484
   8.250   0.9005   0.02722   0.01915  -0.0351   0.0150   0.8506
   8.500   0.9229   0.02851   0.02064  -0.0344   0.0147   0.8521
   8.750   0.9430   0.02988   0.02221  -0.0332   0.0144   0.8534
   9.000   0.9622   0.03138   0.02394  -0.0319   0.0142   0.8548
   9.250   0.9803   0.03302   0.02583  -0.0306   0.0140   0.8564
   9.500   0.9969   0.03486   0.02796  -0.0292   0.0139   0.8584
   9.750   1.0117   0.03690   0.03029  -0.0277   0.0138   0.8605
  10.000   1.0242   0.03923   0.03295  -0.0261   0.0137   0.8626
  10.250   1.0333   0.04195   0.03603  -0.0244   0.0136   0.8645
  10.500   1.0376   0.04512   0.03960  -0.0224   0.0136   0.8664
  10.750   1.0322   0.04866   0.04356  -0.0193   0.0136   0.8679
  11.000   1.0108   0.05316   0.04855  -0.0150   0.0137   0.8698
  11.250   0.9743   0.05937   0.05525  -0.0116   0.0139   0.8723
  11.500   0.9162   0.07040   0.06681  -0.0143   0.0142   0.8748
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