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NACA 66 (p51hroot-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 66 (p51hroot-il)
Reynolds number: 200,000
Max Cl/Cd: 42.36 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-p51hroot-il-200000.txt
Download as CSV file: xf-p51hroot-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.2820   0.09434   0.09085  -0.0833   0.9426   0.0786
 -12.000  -0.2903   0.08921   0.08572  -0.0858   0.9395   0.0818
 -11.750  -0.3364   0.07747   0.07401  -0.0947   0.9374   0.0843
 -11.500  -0.4440   0.07499   0.07136  -0.1005   0.9575   0.0776
 -11.250  -0.4672   0.06960   0.06587  -0.1035   0.9494   0.0781
 -11.000  -0.4889   0.06566   0.06180  -0.1040   0.9419   0.0791
 -10.750  -0.5122   0.06263   0.05863  -0.1026   0.9339   0.0807
 -10.500  -0.5331   0.06020   0.05604  -0.1001   0.9265   0.0814
 -10.250  -0.5684   0.05939   0.05497  -0.0939   0.9177   0.0838
 -10.000  -0.6112   0.06213   0.05721  -0.0855   0.9094   0.0856
  -9.000  -0.6171   0.03896   0.03222  -0.0732   0.8957   0.0500
  -8.750  -0.6034   0.03630   0.02931  -0.0718   0.8928   0.0491
  -8.500  -0.5876   0.03416   0.02687  -0.0703   0.8902   0.0488
  -8.250  -0.5676   0.03205   0.02447  -0.0693   0.8881   0.0485
  -8.000  -0.5439   0.03023   0.02238  -0.0687   0.8863   0.0485
  -7.750  -0.5187   0.02882   0.02073  -0.0684   0.8847   0.0493
  -7.500  -0.4970   0.02813   0.01983  -0.0677   0.8824   0.0506
  -7.250  -0.4705   0.02711   0.01866  -0.0679   0.8804   0.0514
  -7.000  -0.4246   0.02495   0.01653  -0.0716   0.8799   0.0531
  -6.750  -0.3948   0.02412   0.01573  -0.0725   0.8784   0.0553
  -6.500  -0.3682   0.02354   0.01514  -0.0728   0.8766   0.0578
  -6.250  -0.3424   0.02295   0.01452  -0.0729   0.8750   0.0596
  -6.000  -0.3220   0.02257   0.01409  -0.0719   0.8733   0.0614
  -5.750  -0.3085   0.02189   0.01346  -0.0699   0.8714   0.0637
  -5.500  -0.2966   0.02157   0.01316  -0.0673   0.8695   0.0671
  -5.250  -0.2841   0.02146   0.01300  -0.0649   0.8678   0.0713
  -5.000  -0.2903   0.02192   0.01345  -0.0597   0.8642   0.0737
  -4.750  -0.2994   0.02223   0.01378  -0.0537   0.8606   0.0768
  -4.500  -0.2977   0.02229   0.01383  -0.0494   0.8577   0.0827
  -4.250  -0.2954   0.02223   0.01381  -0.0451   0.8557   0.0950
  -4.000  -0.3031   0.02138   0.01359  -0.0394   0.8537   0.2011
  -3.750  -0.3233   0.01955   0.01318  -0.0314   0.8516   0.4861
  -3.500  -0.3580   0.02100   0.01417  -0.0206   0.8468   0.4052
  -3.250  -0.3801   0.02038   0.01478  -0.0114   0.8443   0.6310
  -3.000  -0.3705   0.02099   0.01553  -0.0072   0.8419   0.7301
  -2.750  -0.3521   0.02169   0.01623  -0.0047   0.8401   0.7589
  -2.500  -0.3307   0.02233   0.01681  -0.0030   0.8384   0.7815
  -2.250  -0.3022   0.02347   0.01800  -0.0012   0.8369   0.8035
  -2.000  -0.2696   0.02503   0.01958   0.0007   0.8357   0.8283
  -1.750  -0.2828   0.02579   0.02036   0.0084   0.8313   0.8393
  -1.500  -0.2767   0.02656   0.02112   0.0132   0.8279   0.8534
  -1.250  -0.2567   0.02734   0.02187   0.0157   0.8251   0.8676
  -1.000  -0.2119   0.02821   0.02268   0.0134   0.8232   0.8746
  -0.750  -0.1966   0.02795   0.02234   0.0151   0.8207   0.8818
  -0.500  -0.1521   0.02817   0.02249   0.0119   0.8193   0.8832
  -0.250  -0.1615   0.02835   0.02267   0.0179   0.8123   0.8884
   0.000  -0.1459   0.02830   0.02258   0.0195   0.8082   0.8928
   0.250  -0.1259   0.02807   0.02228   0.0204   0.8050   0.8981
   0.500  -0.0852   0.02815   0.02233   0.0178   0.8032   0.8990
   0.750  -0.0421   0.02827   0.02240   0.0147   0.8016   0.8996
   1.000  -0.0615   0.02825   0.02240   0.0220   0.7911   0.9051
   1.250  -0.0271   0.02823   0.02236   0.0205   0.7884   0.9069
   1.500   0.0127   0.02823   0.02233   0.0181   0.7865   0.9080
   1.750  -0.0016   0.02804   0.02214   0.0244   0.7760   0.9144
   2.000   0.0335   0.02806   0.02216   0.0228   0.7729   0.9159
   2.250   0.0800   0.02791   0.02201   0.0196   0.7706   0.9165
   2.500   0.0902   0.02787   0.02199   0.0221   0.7598   0.9201
   2.750   0.1527   0.02694   0.02106   0.0172   0.7554   0.9192
   3.000   0.1985   0.02662   0.02077   0.0141   0.7539   0.9198
   3.250   0.2009   0.02654   0.02071   0.0180   0.7419   0.9254
   3.500   0.2529   0.02577   0.01999   0.0145   0.7394   0.9257
   3.750   0.2761   0.02544   0.01969   0.0153   0.7340   0.9295
   4.000   0.3695   0.02387   0.01822   0.0055   0.7363   0.9245
   4.250   0.3591   0.02399   0.01838   0.0115   0.7239   0.9315
   4.500   0.4257   0.02235   0.01682   0.0063   0.7230   0.9303
   4.750   0.4821   0.02066   0.01522   0.0028   0.7165   0.9300
   5.000   0.6023   0.01715   0.01178  -0.0104   0.7035   0.9223
   5.250   0.6017   0.01639   0.01106  -0.0046   0.6864   0.9288
   5.500   0.6001   0.01611   0.01088   0.0008   0.6645   0.9343
   5.750   0.5965   0.01591   0.01074   0.0066   0.6426   0.9425
   6.000   0.6253   0.01476   0.00872   0.0085   0.4828   0.9453
   6.250   0.6083   0.01608   0.00941   0.0152   0.3710   0.9543
   6.500   0.5894   0.01822   0.01073   0.0205   0.2244   0.9640
   6.750   0.5838   0.02042   0.01209   0.0233   0.0856   0.9724
   7.000   0.6060   0.02176   0.01325   0.0223   0.0605   0.9757
   7.250   0.6317   0.02273   0.01426   0.0211   0.0555   0.9795
   7.500   0.6558   0.02369   0.01525   0.0201   0.0527   0.9840
   7.750   0.6799   0.02496   0.01650   0.0187   0.0503   0.9873
   8.000   0.7071   0.02592   0.01751   0.0173   0.0486   0.9913
   8.250   0.7351   0.02688   0.01851   0.0160   0.0474   0.9955
   8.500   0.7659   0.02785   0.01949   0.0144   0.0461   0.9993
   8.750   0.7659   0.02809   0.01973   0.0183   0.0454   1.0000
   9.000   0.7616   0.02819   0.01982   0.0231   0.0446   1.0000
   9.250   0.7818   0.02887   0.02041   0.0241   0.0433   1.0000
   9.500   0.8269   0.03010   0.02160   0.0221   0.0424   1.0000
   9.750   0.8529   0.03100   0.02263   0.0223   0.0417   1.0000
  10.000   0.8808   0.03209   0.02387   0.0221   0.0408   1.0000
  10.250   0.9120   0.03353   0.02547   0.0215   0.0399   1.0000
  10.500   0.9463   0.03547   0.02762   0.0204   0.0397   1.0000
  10.750   0.9781   0.03796   0.03040   0.0196   0.0399   1.0000
  11.000   1.0040   0.04088   0.03362   0.0193   0.0405   1.0000
  11.250   1.0289   0.04462   0.03763   0.0189   0.0416   1.0000
  11.500   1.0585   0.04786   0.04107   0.0179   0.0434   1.0000
  11.750   0.9794   0.04582   0.04004   0.0279   0.0498   1.0000
  12.000   0.9309   0.06902   0.06462   0.0377   0.0905   1.0000
  12.250   0.8955   0.07155   0.06735   0.0412   0.0889   1.0000
  12.500   0.8666   0.07552   0.07147   0.0428   0.0886   1.0000
  12.750   0.8347   0.07996   0.07606   0.0434   0.0877   1.0000
  13.000   0.7987   0.08583   0.08206   0.0426   0.0876   1.0000
  13.250   0.7553   0.09386   0.09020   0.0395   0.0880   1.0000
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