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BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il)
Reynolds number: 500,000
Max Cl/Cd: 50.94 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr8b-il-500000-n5.txt
Download as CSV file: xf-vr8b-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-8 AIRFOIL WITH TAB             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.7029   0.09454   0.09264   0.0341   1.0000   0.0042
  -8.500  -0.7049   0.08874   0.08686   0.0297   1.0000   0.0042
  -8.250  -0.7086   0.08225   0.08040   0.0233   1.0000   0.0042
  -7.750  -0.7046   0.06542   0.06340   0.0048   1.0000   0.0042
  -7.500  -0.6998   0.05719   0.05496  -0.0005   1.0000   0.0042
  -7.250  -0.6883   0.05091   0.04845  -0.0036   1.0000   0.0044
  -7.000  -0.6721   0.04566   0.04295  -0.0055   1.0000   0.0046
  -6.750  -0.6532   0.04071   0.03772  -0.0069   1.0000   0.0048
  -6.250  -0.6091   0.03059   0.02681  -0.0085   0.9805   0.0055
  -6.000  -0.5879   0.02342   0.01885  -0.0077   0.9719   0.0065
  -5.750  -0.5658   0.01871   0.01338  -0.0065   0.9642   0.0071
  -5.500  -0.5407   0.01819   0.01276  -0.0062   0.9558   0.0074
  -5.250  -0.5148   0.01751   0.01196  -0.0060   0.9461   0.0080
  -5.000  -0.4881   0.01640   0.01062  -0.0057   0.9319   0.0091
  -4.750  -0.4646   0.01534   0.00919  -0.0043   0.9149   0.0105
  -4.500  -0.4424   0.01503   0.00886  -0.0032   0.8968   0.0113
  -4.250  -0.4181   0.01455   0.00821  -0.0023   0.8739   0.0128
  -4.000  -0.3932   0.01453   0.00779  -0.0012   0.8428   0.0140
  -3.750  -0.3700   0.01354   0.00655  -0.0002   0.7652   0.0150
  -3.500  -0.3414   0.01327   0.00580  -0.0006   0.6539   0.0166
  -3.250  -0.3110   0.01332   0.00537  -0.0014   0.5653   0.0178
  -3.000  -0.2812   0.01296   0.00477  -0.0020   0.5176   0.0182
  -2.750  -0.2515   0.01218   0.00384  -0.0029   0.4658   0.0193
  -2.500  -0.2168   0.01300   0.00346  -0.0057   0.0395   0.0196
  -2.250  -0.1873   0.01274   0.00310  -0.0061   0.0330   0.0196
  -2.000  -0.1578   0.01250   0.00279  -0.0066   0.0318   0.0197
  -1.750  -0.1282   0.01228   0.00251  -0.0071   0.0243   0.0199
  -1.500  -0.0984   0.01214   0.00226  -0.0076   0.0229   0.0203
  -1.250  -0.0689   0.01200   0.00206  -0.0081   0.0225   0.0207
  -1.000  -0.0394   0.01190   0.00191  -0.0086   0.0224   0.0212
  -0.750  -0.0099   0.01183   0.00180  -0.0090   0.0223   0.0216
  -0.500   0.0195   0.01179   0.00171  -0.0095   0.0221   0.0219
  -0.250   0.0490   0.01178   0.00165  -0.0099   0.0222   0.0228
   0.000   0.0784   0.01178   0.00162  -0.0103   0.0221   0.0237
   0.250   0.1078   0.01181   0.00161  -0.0108   0.0222   0.0239
   0.500   0.1371   0.01185   0.00162  -0.0112   0.0222   0.0241
   0.750   0.1663   0.01191   0.00161  -0.0116   0.0223   0.0254
   1.000   0.1958   0.01188   0.00168  -0.0121   0.0223   0.0260
   1.250   0.2251   0.01191   0.00180  -0.0126   0.0221   0.0316
   1.500   0.2544   0.01199   0.00192  -0.0130   0.0216   0.0320
   1.750   0.2838   0.01208   0.00205  -0.0135   0.0213   0.0329
   2.000   0.3131   0.01217   0.00218  -0.0140   0.0211   0.0378
   2.500   0.3751   0.01113   0.00257  -0.0167   0.0208   0.5488
   2.750   0.4049   0.01080   0.00285  -0.0176   0.0206   0.7154
   3.000   0.4329   0.01077   0.00311  -0.0178   0.0205   0.7894
   3.250   0.4571   0.01079   0.00340  -0.0169   0.0204   0.8643
   3.500   0.4743   0.01084   0.00363  -0.0142   0.0203   0.9348
   3.750   0.5002   0.01097   0.00380  -0.0137   0.0204   1.0000
   4.000   0.5296   0.01129   0.00411  -0.0143   0.0205   1.0000
   4.250   0.5588   0.01162   0.00445  -0.0149   0.0206   1.0000
   4.500   0.5878   0.01197   0.00481  -0.0154   0.0208   1.0000
   4.750   0.6168   0.01234   0.00522  -0.0159   0.0210   1.0000
   5.000   0.6455   0.01275   0.00565  -0.0164   0.0212   1.0000
   5.250   0.6740   0.01323   0.00615  -0.0169   0.0214   1.0000
   5.500   0.7022   0.01379   0.00674  -0.0174   0.0216   1.0000
   5.750   0.7299   0.01444   0.00744  -0.0178   0.0209   1.0000
   6.000   0.7532   0.01674   0.00940  -0.0180   0.0194   1.0000
   6.250   0.7820   0.01676   0.00974  -0.0184   0.0177   1.0000
   6.500   0.8074   0.01812   0.01101  -0.0185   0.0159   1.0000
   6.750   0.8350   0.01847   0.01158  -0.0188   0.0145   1.0000
   7.000   0.8604   0.01992   0.01282  -0.0190   0.0135   1.0000
   7.250   0.8886   0.01965   0.01307  -0.0193   0.0116   1.0000
   7.750   0.9427   0.02032   0.01413  -0.0198   0.0078   1.0000
   8.000   0.9687   0.02097   0.01488  -0.0199   0.0070   1.0000
   8.250   0.9937   0.02190   0.01595  -0.0200   0.0063   1.0000
   8.500   1.0191   0.02255   0.01672  -0.0201   0.0058   1.0000
   8.750   1.0445   0.02301   0.01725  -0.0203   0.0054   1.0000
   9.000   1.0687   0.02386   0.01822  -0.0204   0.0049   1.0000
   9.250   1.0886   0.02606   0.02071  -0.0200   0.0046   1.0000
   9.500   1.1061   0.02885   0.02390  -0.0194   0.0043   1.0000
   9.750   1.1217   0.03166   0.02711  -0.0188   0.0039   1.0000
  10.000   1.1361   0.03426   0.03002  -0.0183   0.0036   1.0000
  10.250   1.1462   0.03733   0.03344  -0.0176   0.0034   1.0000
  10.500   1.1498   0.04105   0.03753  -0.0168   0.0033   1.0000
  10.750   1.1463   0.04521   0.04204  -0.0159   0.0032   1.0000
  11.000   1.1299   0.04975   0.04689  -0.0149   0.0032   1.0000
  11.250   1.1070   0.05542   0.05282  -0.0163   0.0032   1.0000
  11.500   1.0760   0.06394   0.06162  -0.0214   0.0032   1.0000
  11.750   1.0424   0.07476   0.07267  -0.0293   0.0033   1.0000
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