Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il)
Reynolds number: 1,000,000
Max Cl/Cd: 75.6 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr1-il-1000000-n5.txt
Download as CSV file: xf-vr1-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-1 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8604   0.06219   0.05976  -0.0538   1.0000   0.0115
 -13.750  -0.8955   0.05162   0.04895  -0.0627   1.0000   0.0115
 -13.500  -0.9200   0.04502   0.04213  -0.0671   1.0000   0.0115
 -13.250  -0.9414   0.04016   0.03706  -0.0687   1.0000   0.0115
 -13.000  -0.9547   0.03693   0.03365  -0.0682   1.0000   0.0116
 -12.750  -0.9658   0.03437   0.03091  -0.0663   1.0000   0.0116
 -12.500  -0.9783   0.03208   0.02841  -0.0630   1.0000   0.0117
 -12.250  -0.9853   0.03058   0.02678  -0.0589   1.0000   0.0117
 -12.000  -0.9870   0.02912   0.02516  -0.0553   1.0000   0.0117
 -11.750  -0.9837   0.02772   0.02360  -0.0523   1.0000   0.0118
 -11.500  -0.9773   0.02653   0.02228  -0.0496   1.0000   0.0119
 -11.250  -0.9699   0.02545   0.02107  -0.0468   1.0000   0.0119
 -11.000  -0.9500   0.02349   0.01892  -0.0471   0.9965   0.0120
 -10.750  -0.9284   0.02221   0.01752  -0.0471   0.9903   0.0121
 -10.500  -0.9021   0.02136   0.01660  -0.0477   0.9857   0.0123
 -10.250  -0.8739   0.02075   0.01594  -0.0486   0.9816   0.0124
 -10.000  -0.8455   0.01999   0.01511  -0.0494   0.9768   0.0125
  -9.750  -0.8151   0.01918   0.01421  -0.0507   0.9726   0.0127
  -9.500  -0.7849   0.01837   0.01332  -0.0519   0.9673   0.0128
  -9.250  -0.7548   0.01755   0.01240  -0.0530   0.9604   0.0129
  -9.000  -0.7242   0.01687   0.01164  -0.0541   0.9533   0.0131
  -8.750  -0.6968   0.01611   0.01079  -0.0545   0.9431   0.0132
  -8.500  -0.6710   0.01557   0.01016  -0.0544   0.9328   0.0134
  -8.250  -0.6465   0.01501   0.00951  -0.0540   0.9223   0.0136
  -8.000  -0.6232   0.01450   0.00891  -0.0533   0.9112   0.0137
  -7.750  -0.5998   0.01403   0.00836  -0.0525   0.9011   0.0139
  -7.250  -0.5531   0.01314   0.00732  -0.0510   0.8824   0.0142
  -7.000  -0.5297   0.01274   0.00684  -0.0502   0.8735   0.0143
  -6.750  -0.5056   0.01237   0.00642  -0.0495   0.8649   0.0145
  -6.500  -0.4815   0.01204   0.00602  -0.0488   0.8571   0.0146
  -6.250  -0.4567   0.01173   0.00567  -0.0482   0.8494   0.0147
  -6.000  -0.4342   0.01122   0.00510  -0.0473   0.8414   0.0150
  -5.750  -0.4096   0.01088   0.00474  -0.0467   0.8342   0.0152
  -5.500  -0.3847   0.01060   0.00442  -0.0461   0.8270   0.0155
  -5.250  -0.3592   0.01038   0.00418  -0.0457   0.8204   0.0158
  -5.000  -0.3337   0.01014   0.00391  -0.0452   0.8131   0.0161
  -4.750  -0.3083   0.00992   0.00364  -0.0447   0.8066   0.0164
  -4.500  -0.2824   0.00968   0.00339  -0.0443   0.8002   0.0167
  -4.250  -0.2566   0.00948   0.00315  -0.0439   0.7934   0.0170
  -4.000  -0.2304   0.00930   0.00294  -0.0435   0.7873   0.0173
  -3.750  -0.2041   0.00912   0.00274  -0.0431   0.7807   0.0176
  -3.250  -0.1518   0.00874   0.00231  -0.0423   0.7683   0.0184
  -3.000  -0.1255   0.00857   0.00213  -0.0420   0.7617   0.0189
  -2.750  -0.0989   0.00844   0.00198  -0.0417   0.7558   0.0195
  -2.500  -0.0720   0.00831   0.00185  -0.0414   0.7495   0.0203
  -2.250  -0.0452   0.00822   0.00174  -0.0411   0.7432   0.0210
  -2.000  -0.0181   0.00812   0.00163  -0.0409   0.7374   0.0216
  -1.750   0.0089   0.00801   0.00152  -0.0406   0.7310   0.0229
  -1.500   0.0357   0.00793   0.00143  -0.0403   0.7249   0.0243
  -1.250   0.0629   0.00783   0.00135  -0.0401   0.7188   0.0287
  -1.000   0.0864   0.00732   0.00121  -0.0394   0.7123   0.1407
  -0.750   0.1097   0.00684   0.00111  -0.0387   0.7061   0.2601
  -0.500   0.1352   0.00661   0.00106  -0.0382   0.6983   0.3224
  -0.250   0.1597   0.00638   0.00102  -0.0376   0.6858   0.3886
   0.000   0.1842   0.00616   0.00099  -0.0369   0.6737   0.4599
   0.500   0.2319   0.00576   0.00098  -0.0353   0.6437   0.6076
   0.750   0.2551   0.00560   0.00100  -0.0343   0.6258   0.6790
   1.000   0.2788   0.00556   0.00104  -0.0333   0.6006   0.7261
   1.250   0.3023   0.00558   0.00109  -0.0323   0.5721   0.7645
   1.500   0.3241   0.00581   0.00117  -0.0310   0.5143   0.7925
   1.750   0.3445   0.00620   0.00131  -0.0295   0.4349   0.8128
   2.000   0.3646   0.00668   0.00151  -0.0280   0.3508   0.8306
   2.250   0.3840   0.00725   0.00174  -0.0265   0.2552   0.8452
   2.500   0.4041   0.00778   0.00197  -0.0251   0.1724   0.8598
   2.750   0.4263   0.00816   0.00216  -0.0240   0.1207   0.8735
   3.000   0.4507   0.00834   0.00231  -0.0233   0.1026   0.8872
   3.250   0.4756   0.00851   0.00246  -0.0227   0.0901   0.9018
   3.500   0.5010   0.00867   0.00260  -0.0221   0.0805   0.9160
   3.750   0.5271   0.00883   0.00276  -0.0218   0.0724   0.9302
   4.000   0.5548   0.00902   0.00292  -0.0217   0.0642   0.9454
   4.250   0.5854   0.00923   0.00311  -0.0224   0.0567   0.9589
   4.500   0.6181   0.00946   0.00330  -0.0236   0.0502   0.9686
   4.750   0.6510   0.00972   0.00351  -0.0248   0.0439   0.9741
   5.000   0.6841   0.00998   0.00373  -0.0261   0.0389   0.9791
   5.250   0.7150   0.01021   0.00394  -0.0269   0.0359   0.9840
   5.500   0.7477   0.01049   0.00419  -0.0282   0.0328   0.9865
   5.750   0.7785   0.01073   0.00442  -0.0290   0.0310   0.9893
   6.000   0.8081   0.01100   0.00467  -0.0296   0.0293   0.9926
   6.250   0.8372   0.01131   0.00496  -0.0301   0.0277   0.9960
   6.500   0.8676   0.01157   0.00523  -0.0309   0.0269   0.9987
   6.750   0.8950   0.01184   0.00550  -0.0311   0.0259   1.0000
   7.000   0.9140   0.01209   0.00575  -0.0294   0.0250   1.0000
   7.250   0.9333   0.01236   0.00602  -0.0278   0.0243   1.0000
   7.500   0.9524   0.01268   0.00633  -0.0262   0.0236   1.0000
   7.750   0.9717   0.01299   0.00667  -0.0246   0.0231   1.0000
   8.000   0.9916   0.01328   0.00697  -0.0232   0.0228   1.0000
   8.250   1.0114   0.01358   0.00730  -0.0217   0.0224   1.0000
   8.500   1.0310   0.01390   0.00764  -0.0203   0.0220   1.0000
   8.750   1.0505   0.01423   0.00799  -0.0189   0.0216   1.0000
   9.000   1.0698   0.01458   0.00836  -0.0174   0.0212   1.0000
   9.250   1.0887   0.01494   0.00874  -0.0159   0.0209   1.0000
   9.500   1.1073   0.01533   0.00915  -0.0144   0.0205   1.0000
   9.750   1.1254   0.01573   0.00957  -0.0129   0.0201   1.0000
  10.000   1.1408   0.01619   0.01005  -0.0108   0.0197   1.0000
  10.250   1.1540   0.01672   0.01062  -0.0084   0.0193   1.0000
  10.500   1.1694   0.01714   0.01108  -0.0064   0.0192   1.0000
  10.750   1.1849   0.01759   0.01157  -0.0044   0.0190   1.0000
  11.000   1.2002   0.01806   0.01209  -0.0026   0.0188   1.0000
  11.250   1.2154   0.01857   0.01265  -0.0008   0.0187   1.0000
  11.500   1.2302   0.01911   0.01324   0.0010   0.0185   1.0000
  11.750   1.2450   0.01967   0.01385   0.0027   0.0183   1.0000
  12.000   1.2590   0.02029   0.01453   0.0044   0.0180   1.0000
  12.250   1.2728   0.02095   0.01524   0.0061   0.0178   1.0000
  12.500   1.2865   0.02162   0.01597   0.0077   0.0177   1.0000
  12.750   1.2995   0.02236   0.01676   0.0093   0.0175   1.0000
  13.000   1.3121   0.02314   0.01760   0.0109   0.0173   1.0000
  13.250   1.3246   0.02394   0.01845   0.0123   0.0171   1.0000
  13.500   1.3365   0.02481   0.01937   0.0138   0.0169   1.0000
  13.750   1.3470   0.02579   0.02042   0.0153   0.0168   1.0000
  14.000   1.3570   0.02685   0.02154   0.0167   0.0166   1.0000
  14.250   1.3666   0.02795   0.02270   0.0180   0.0164   1.0000
  14.500   1.3729   0.02937   0.02418   0.0194   0.0162   1.0000
  14.750   1.3777   0.03093   0.02582   0.0208   0.0160   1.0000
  15.000   1.3835   0.03248   0.02746   0.0219   0.0159   1.0000
  15.250   1.3912   0.03390   0.02897   0.0229   0.0158   1.0000
  15.500   1.3976   0.03547   0.03063   0.0237   0.0157   1.0000
  15.750   1.4026   0.03722   0.03248   0.0245   0.0156   1.0000
  16.000   1.4069   0.03909   0.03444   0.0251   0.0156   1.0000
  16.250   1.4102   0.04111   0.03655   0.0256   0.0155   1.0000
  16.500   1.4110   0.04345   0.03900   0.0260   0.0154   1.0000
  16.750   1.4133   0.04574   0.04139   0.0262   0.0152   1.0000
  17.000   1.4138   0.04828   0.04404   0.0261   0.0152   1.0000
  17.250   1.4108   0.05134   0.04721   0.0259   0.0151   1.0000
  17.500   1.4075   0.05458   0.05056   0.0253   0.0150   1.0000
  17.750   1.4070   0.05761   0.05369   0.0246   0.0148   1.0000
  18.000   1.4014   0.06141   0.05760   0.0235   0.0147   1.0000
  18.250   1.3932   0.06575   0.06207   0.0221   0.0147   1.0000
  18.500   1.3845   0.07038   0.06681   0.0202   0.0146   1.0000
  18.750   1.3691   0.07620   0.07278   0.0176   0.0146   1.0000
  19.000   1.3540   0.08229   0.07900   0.0147   0.0146   1.0000
  19.250   1.3406   0.08837   0.08521   0.0115   0.0144   1.0000
<< Back to BOEING-VERTOL VR-1 AIRFOIL (vr1-il)

Polar data table (+)

Polar graphs


<< Back to BOEING-VERTOL VR-1 AIRFOIL (vr1-il)