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P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il)
Reynolds number: 100,000
Max Cl/Cd: 35.45 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51dtip-il-100000-n5.txt
Download as CSV file: xf-p51dtip-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: P-51D TIP (BL215) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5127   0.09605   0.09161  -0.0349   1.0000   0.0238
 -10.250  -0.5148   0.09054   0.08614  -0.0389   0.9596   0.0237
 -10.000  -0.5153   0.08292   0.07849  -0.0465   0.9356   0.0236
  -9.750  -0.5212   0.07599   0.07147  -0.0529   0.9198   0.0233
  -9.500  -0.5332   0.07028   0.06563  -0.0570   0.9071   0.0232
  -9.250  -0.5461   0.06588   0.06110  -0.0587   0.8967   0.0230
  -8.750  -0.5711   0.05815   0.05294  -0.0580   0.8806   0.0232
  -8.500  -0.5773   0.05412   0.04859  -0.0571   0.8748   0.0234
  -8.250  -0.5790   0.05000   0.04410  -0.0560   0.8696   0.0236
  -8.000  -0.5764   0.04598   0.03965  -0.0548   0.8650   0.0238
  -7.750  -0.5704   0.04202   0.03514  -0.0532   0.8612   0.0243
  -7.500  -0.5598   0.03834   0.03080  -0.0517   0.8576   0.0249
  -7.250  -0.5447   0.03533   0.02744  -0.0509   0.8539   0.0260
  -7.000  -0.5253   0.03402   0.02600  -0.0506   0.8505   0.0286
  -6.750  -0.5055   0.03192   0.02333  -0.0496   0.8475   0.0321
  -6.500  -0.4835   0.02956   0.02056  -0.0489   0.8448   0.0342
  -6.250  -0.4595   0.02811   0.01896  -0.0488   0.8417   0.0370
  -6.000  -0.4350   0.02708   0.01758  -0.0484   0.8389   0.0424
  -5.750  -0.4097   0.02536   0.01580  -0.0483   0.8366   0.0449
  -5.500  -0.3838   0.02414   0.01444  -0.0480   0.8345   0.0477
  -5.250  -0.3586   0.02313   0.01320  -0.0475   0.8326   0.0508
  -5.000  -0.3336   0.02236   0.01227  -0.0472   0.8301   0.0534
  -4.750  -0.3109   0.02157   0.01156  -0.0469   0.8274   0.0587
  -4.500  -0.2873   0.02105   0.01094  -0.0465   0.8247   0.0638
  -4.250  -0.2643   0.02050   0.01027  -0.0458   0.8224   0.0660
  -4.000  -0.2418   0.01993   0.00966  -0.0451   0.8204   0.0698
  -3.750  -0.2182   0.01953   0.00916  -0.0445   0.8187   0.0763
  -3.500  -0.1951   0.01907   0.00870  -0.0441   0.8166   0.0918
  -3.250  -0.1773   0.01809   0.00834  -0.0432   0.8142   0.2019
  -3.000  -0.1752   0.01669   0.00900  -0.0383   0.8115   0.6154
  -2.750  -0.1535   0.01713   0.00929  -0.0368   0.8093   0.7059
  -2.500  -0.1348   0.01805   0.01024  -0.0331   0.8074   0.7562
  -2.250  -0.1193   0.01910   0.01131  -0.0276   0.8058   0.8020
  -2.000  -0.0974   0.01954   0.01169  -0.0248   0.8045   0.8232
  -1.750  -0.0741   0.01961   0.01165  -0.0244   0.8023   0.8301
  -1.500  -0.0497   0.01963   0.01156  -0.0244   0.8003   0.8338
  -1.250  -0.0242   0.01965   0.01147  -0.0245   0.7984   0.8362
  -1.000   0.0012   0.01966   0.01139  -0.0247   0.7966   0.8382
  -0.750   0.0267   0.01967   0.01132  -0.0249   0.7948   0.8402
  -0.500   0.0526   0.01967   0.01124  -0.0251   0.7932   0.8420
  -0.250   0.0787   0.01970   0.01120  -0.0254   0.7918   0.8437
   0.000   0.1046   0.01976   0.01121  -0.0258   0.7905   0.8456
   0.250   0.1282   0.01995   0.01141  -0.0259   0.7883   0.8475
   0.500   0.1521   0.02014   0.01161  -0.0260   0.7863   0.8494
   0.750   0.1764   0.02032   0.01180  -0.0261   0.7843   0.8512
   1.000   0.2014   0.02048   0.01198  -0.0263   0.7824   0.8531
   1.250   0.2268   0.02065   0.01217  -0.0265   0.7807   0.8551
   1.500   0.2524   0.02085   0.01240  -0.0268   0.7795   0.8573
   1.750   0.2783   0.02106   0.01265  -0.0272   0.7783   0.8598
   2.000   0.3047   0.02127   0.01293  -0.0274   0.7773   0.8618
   2.250   0.3243   0.02171   0.01348  -0.0271   0.7743   0.8646
   2.500   0.3449   0.02213   0.01400  -0.0268   0.7716   0.8674
   2.750   0.3676   0.02247   0.01444  -0.0267   0.7691   0.8702
   3.000   0.3942   0.02265   0.01472  -0.0269   0.7663   0.8728
   3.250   0.4244   0.02268   0.01489  -0.0273   0.7638   0.8749
   3.500   0.4412   0.02308   0.01544  -0.0263   0.7571   0.8786
   3.750   0.4783   0.02244   0.01494  -0.0265   0.7500   0.8806
   4.000   0.5105   0.02148   0.01411  -0.0255   0.7358   0.8833
   4.250   0.5369   0.02057   0.01340  -0.0239   0.7174   0.8867
   4.500   0.5666   0.01878   0.01172  -0.0215   0.6873   0.8893
   4.750   0.5882   0.01764   0.01074  -0.0191   0.6450   0.8933
   5.000   0.6040   0.01761   0.01091  -0.0173   0.5936   0.8991
   5.250   0.6169   0.01740   0.00907  -0.0121   0.3133   0.9034
   5.500   0.6215   0.01878   0.00987  -0.0093   0.1981   0.9110
   5.750   0.6345   0.01988   0.01054  -0.0076   0.1175   0.9189
   6.000   0.6530   0.02085   0.01141  -0.0066   0.0838   0.9280
   6.250   0.6762   0.02172   0.01228  -0.0064   0.0673   0.9383
   6.500   0.7014   0.02272   0.01334  -0.0068   0.0572   0.9525
   6.750   0.7261   0.02392   0.01456  -0.0074   0.0479   1.0000
   7.000   0.7452   0.02492   0.01558  -0.0068   0.0399   1.0000
   7.250   0.7652   0.02636   0.01710  -0.0061   0.0353   1.0000
   7.500   0.7866   0.02776   0.01847  -0.0058   0.0301   1.0000
   7.750   0.8119   0.02924   0.02011  -0.0057   0.0264   1.0000
   8.000   0.8382   0.03125   0.02214  -0.0059   0.0242   1.0000
   8.250   0.8679   0.03388   0.02506  -0.0062   0.0228   1.0000
   8.500   0.8922   0.03653   0.02819  -0.0057   0.0209   1.0000
   8.750   0.9106   0.03907   0.03115  -0.0048   0.0190   1.0000
   9.000   0.9247   0.04181   0.03426  -0.0036   0.0178   1.0000
   9.250   0.9343   0.04501   0.03801  -0.0020   0.0173   1.0000
   9.500   0.9388   0.04832   0.04170  -0.0001   0.0170   1.0000
   9.750   0.9382   0.05171   0.04544   0.0021   0.0168   1.0000
  10.000   0.9312   0.05502   0.04906   0.0047   0.0167   1.0000
  10.250   0.9197   0.05849   0.05280   0.0072   0.0167   1.0000
  10.500   0.9051   0.06222   0.05678   0.0090   0.0167   1.0000
  10.750   0.8879   0.06644   0.06124   0.0101   0.0169   1.0000
  11.000   0.8686   0.07110   0.06610   0.0103   0.0169   1.0000
  11.250   0.8472   0.07647   0.07165   0.0094   0.0172   1.0000
  11.500   0.8237   0.08279   0.07813   0.0072   0.0174   1.0000
  11.750   0.7997   0.09041   0.08587   0.0033   0.0177   1.0000
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