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K3311 (original) (k3311-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: K3311 (original) (k3311-il)
Reynolds number: 200,000
Max Cl/Cd: 77.42 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3311-il-200000.txt
Download as CSV file: xf-k3311-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: K3311  (original)                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3947   0.08678   0.08344  -0.0469   1.0000   0.0548
  -8.500  -0.4132   0.08319   0.07995  -0.0487   1.0000   0.0549
  -8.250  -0.4350   0.07948   0.07626  -0.0505   1.0000   0.0550
  -8.000  -0.4536   0.07693   0.07367  -0.0494   1.0000   0.0551
  -7.750  -0.4557   0.07217   0.06908  -0.0463   1.0000   0.0563
  -7.500  -0.4519   0.07155   0.06855  -0.0413   1.0000   0.0574
  -7.250  -0.4600   0.07008   0.06713  -0.0383   1.0000   0.0583
  -7.000  -0.4450   0.06626   0.06325  -0.0422   0.9963   0.0609
  -6.750  -0.4212   0.05515   0.05145  -0.0600   0.9847   0.0687
  -6.500  -0.3931   0.05221   0.04869  -0.0613   0.9806   0.0711
  -6.250  -0.3637   0.04763   0.04336  -0.0687   0.9716   0.0822
  -6.000  -0.3363   0.04402   0.04005  -0.0701   0.9666   0.0855
  -5.750  -0.3063   0.04040   0.03592  -0.0743   0.9590   0.0976
  -5.500  -0.2706   0.03738   0.03297  -0.0774   0.9562   0.1028
  -5.250  -0.2448   0.03452   0.02982  -0.0790   0.9467   0.1147
  -5.000  -0.2085   0.03194   0.02702  -0.0822   0.9431   0.1292
  -4.750  -0.1718   0.02304   0.01624  -0.0804   0.9350   0.0575
  -4.500  -0.1322   0.02175   0.01463  -0.0819   0.9301   0.0547
  -4.250  -0.0962   0.01963   0.01229  -0.0834   0.9249   0.0538
  -4.000  -0.0634   0.01865   0.01111  -0.0841   0.9165   0.0548
  -3.750  -0.0275   0.01735   0.00968  -0.0853   0.9108   0.0549
  -3.500   0.0021   0.01632   0.00857  -0.0854   0.9011   0.0550
  -3.250   0.0315   0.01527   0.00751  -0.0854   0.8921   0.0557
  -3.000   0.0608   0.01432   0.00655  -0.0855   0.8835   0.0571
  -2.750   0.0861   0.01376   0.00598  -0.0848   0.8721   0.0591
  -2.500   0.1132   0.01336   0.00554  -0.0845   0.8622   0.0631
  -2.250   0.1416   0.01303   0.00510  -0.0842   0.8529   0.0675
  -2.000   0.1663   0.01264   0.00469  -0.0834   0.8413   0.0760
  -1.750   0.1884   0.01166   0.00430  -0.0825   0.8306   0.2269
  -1.500   0.2061   0.01054   0.00429  -0.0806   0.8210   0.5492
  -1.250   0.2267   0.01019   0.00430  -0.0787   0.8101   0.6638
  -1.000   0.2472   0.00990   0.00433  -0.0764   0.7994   0.7631
  -0.750   0.2741   0.00967   0.00426  -0.0753   0.7900   0.8477
  -0.500   0.3331   0.00951   0.00412  -0.0810   0.7803   0.9372
  -0.250   0.4064   0.00947   0.00393  -0.0902   0.7684   0.9984
   0.000   0.4295   0.00952   0.00382  -0.0895   0.7559   1.0000
   0.250   0.4522   0.00961   0.00376  -0.0885   0.7446   1.0000
   0.500   0.4758   0.00971   0.00372  -0.0877   0.7338   1.0000
   0.750   0.4989   0.00982   0.00374  -0.0867   0.7222   1.0000
   1.000   0.5228   0.00994   0.00377  -0.0859   0.7114   1.0000
   1.250   0.5476   0.01006   0.00378  -0.0852   0.7017   1.0000
   1.500   0.5721   0.01020   0.00383  -0.0845   0.6914   1.0000
   1.750   0.5965   0.01035   0.00392  -0.0837   0.6811   1.0000
   2.000   0.6219   0.01053   0.00400  -0.0832   0.6719   1.0000
   2.250   0.6468   0.01070   0.00413  -0.0825   0.6619   1.0000
   2.500   0.6712   0.01088   0.00427  -0.0818   0.6514   1.0000
   2.750   0.6962   0.01106   0.00439  -0.0812   0.6413   1.0000
   3.000   0.7212   0.01121   0.00451  -0.0805   0.6308   1.0000
   3.250   0.7454   0.01135   0.00467  -0.0798   0.6201   1.0000
   3.500   0.7704   0.01150   0.00480  -0.0791   0.6106   1.0000
   3.750   0.7956   0.01164   0.00491  -0.0785   0.6012   1.0000
   4.000   0.8200   0.01177   0.00509  -0.0778   0.5905   1.0000
   4.250   0.8450   0.01192   0.00525  -0.0772   0.5807   1.0000
   4.500   0.8705   0.01209   0.00536  -0.0766   0.5709   1.0000
   4.750   0.8944   0.01224   0.00555  -0.0758   0.5586   1.0000
   5.000   0.9183   0.01241   0.00574  -0.0750   0.5454   1.0000
   5.250   0.9420   0.01260   0.00594  -0.0741   0.5316   1.0000
   5.500   0.9653   0.01280   0.00613  -0.0732   0.5168   1.0000
   5.750   0.9884   0.01300   0.00637  -0.0722   0.5020   1.0000
   6.000   1.0116   0.01324   0.00663  -0.0713   0.4880   1.0000
   6.250   1.0348   0.01349   0.00692  -0.0704   0.4740   1.0000
   6.500   1.0572   0.01373   0.00720  -0.0693   0.4585   1.0000
   6.750   1.0778   0.01396   0.00742  -0.0679   0.4381   1.0000
   7.000   1.0963   0.01416   0.00762  -0.0662   0.4100   1.0000
   7.250   1.1139   0.01448   0.00787  -0.0643   0.3793   1.0000
   7.500   1.1307   0.01492   0.00823  -0.0624   0.3471   1.0000
   7.750   1.1465   0.01549   0.00870  -0.0604   0.3148   1.0000
   8.000   1.1605   0.01617   0.00928  -0.0582   0.2786   1.0000
   8.250   1.1715   0.01703   0.00994  -0.0557   0.2318   1.0000
   8.500   1.1756   0.01834   0.01087  -0.0522   0.1670   1.0000
   8.750   1.1658   0.02049   0.01238  -0.0469   0.0861   1.0000
   9.000   1.1592   0.02233   0.01389  -0.0419   0.0516   1.0000
   9.250   1.1623   0.02363   0.01520  -0.0384   0.0438   1.0000
   9.500   1.1618   0.02519   0.01680  -0.0348   0.0395   1.0000
   9.750   1.1663   0.02652   0.01825  -0.0321   0.0370   1.0000
  10.000   1.1696   0.02801   0.01985  -0.0295   0.0354   1.0000
  10.250   1.1710   0.02975   0.02165  -0.0271   0.0338   1.0000
  10.500   1.1694   0.03188   0.02382  -0.0247   0.0324   1.0000
  10.750   1.1703   0.03407   0.02606  -0.0225   0.0313   1.0000
  11.000   1.1788   0.03563   0.02774  -0.0210   0.0302   1.0000
  11.250   1.1870   0.03729   0.02950  -0.0197   0.0289   1.0000
  11.500   1.1956   0.03909   0.03137  -0.0183   0.0277   1.0000
  11.750   1.2059   0.04088   0.03324  -0.0171   0.0268   1.0000
  12.000   1.2192   0.04267   0.03509  -0.0159   0.0262   1.0000
  12.250   1.2353   0.04459   0.03706  -0.0148   0.0256   1.0000
  12.500   1.2588   0.04702   0.03959  -0.0140   0.0249   1.0000
  12.750   1.2796   0.05083   0.04364  -0.0135   0.0243   1.0000
  13.000   1.2774   0.05315   0.04619  -0.0120   0.0241   1.0000
  13.250   1.2732   0.05561   0.04889  -0.0108   0.0237   1.0000
  13.500   1.2692   0.05862   0.05218  -0.0098   0.0235   1.0000
  13.750   1.2631   0.06207   0.05588  -0.0092   0.0233   1.0000
  14.000   1.2566   0.06604   0.06010  -0.0088   0.0234   1.0000
  14.250   1.2466   0.07034   0.06463  -0.0088   0.0235   1.0000
  14.500   1.2334   0.07494   0.06947  -0.0093   0.0235   1.0000
  14.750   1.2189   0.07997   0.07473  -0.0103   0.0237   1.0000
  15.000   1.2041   0.08548   0.08044  -0.0116   0.0239   1.0000
  15.250   1.1849   0.09155   0.08672  -0.0137   0.0240   1.0000
  15.500   1.1678   0.09801   0.09336  -0.0161   0.0242   1.0000
  15.750   1.1581   0.10357   0.09908  -0.0181   0.0245   1.0000
  16.000   1.1436   0.10911   0.10479  -0.0214   0.0247   1.0000
  16.250   1.1241   0.11619   0.11207  -0.0260   0.0249   1.0000
  16.500   1.0925   0.12663   0.12279  -0.0334   0.0255   1.0000
  16.750   0.9680   0.17020   0.16672  -0.0611   0.0331   1.0000
  17.000   0.9722   0.17356   0.17010  -0.0626   0.0325   1.0000
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