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BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
Reynolds number: 500,000
Max Cl/Cd: 99.52 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr7b-il-500000.txt
Download as CSV file: xf-vr7b-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-7 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5610   0.08643   0.08443   0.0079   0.8817   0.0212
  -8.250  -0.5641   0.08110   0.07911   0.0033   0.8711   0.0215
  -8.000  -0.5723   0.07352   0.07146  -0.0057   0.8599   0.0216
  -7.750  -0.5727   0.06774   0.06553  -0.0101   0.8496   0.0219
  -7.500  -0.5689   0.06221   0.05984  -0.0135   0.8378   0.0224
  -7.250  -0.5623   0.05640   0.05379  -0.0161   0.8266   0.0234
  -7.000  -0.5613   0.04620   0.04269  -0.0185   0.8174   0.0252
  -6.750  -0.5457   0.04260   0.03905  -0.0189   0.8058   0.0257
  -6.500  -0.5266   0.04037   0.03672  -0.0192   0.7946   0.0262
  -6.250  -0.5062   0.03824   0.03441  -0.0193   0.7843   0.0270
  -6.000  -0.4843   0.03575   0.03168  -0.0195   0.7739   0.0284
  -5.750  -0.4395   0.01729   0.01267  -0.0206   0.7486   0.0319
  -5.500  -0.4172   0.01540   0.01074  -0.0208   0.7408   0.0327
  -5.250  -0.3932   0.01400   0.00925  -0.0210   0.7325   0.0341
  -5.000  -0.3660   0.01335   0.00828  -0.0206   0.7247   0.0378
  -4.750  -0.3548   0.01998   0.01361  -0.0183   0.7308   0.0247
  -4.500  -0.3269   0.01799   0.01136  -0.0183   0.7229   0.0245
  -4.250  -0.2980   0.01684   0.01003  -0.0183   0.7144   0.0247
  -4.000  -0.2699   0.01542   0.00842  -0.0183   0.7072   0.0255
  -3.750  -0.2414   0.01436   0.00733  -0.0185   0.7001   0.0262
  -3.500  -0.2129   0.01367   0.00655  -0.0185   0.6940   0.0268
  -3.250  -0.1838   0.01307   0.00592  -0.0188   0.6876   0.0276
  -3.000  -0.1547   0.01257   0.00536  -0.0190   0.6813   0.0286
  -2.750  -0.1254   0.01215   0.00486  -0.0192   0.6754   0.0297
  -2.500  -0.0957   0.01189   0.00457  -0.0195   0.6693   0.0311
  -2.250  -0.0663   0.01125   0.00389  -0.0199   0.6639   0.0338
  -2.000  -0.0365   0.01097   0.00357  -0.0203   0.6583   0.0364
  -1.750  -0.0064   0.01067   0.00323  -0.0207   0.6522   0.0401
  -1.500   0.0234   0.01042   0.00293  -0.0210   0.6466   0.0494
  -1.250   0.0537   0.00916   0.00256  -0.0223   0.6409   0.2881
  -1.000   0.0830   0.00808   0.00248  -0.0234   0.6350   0.5849
  -0.750   0.1116   0.00776   0.00245  -0.0235   0.6295   0.6800
  -0.500   0.1397   0.00751   0.00250  -0.0233   0.6233   0.7698
  -0.250   0.1657   0.00735   0.00252  -0.0226   0.6174   0.8277
   0.000   0.1878   0.00729   0.00259  -0.0207   0.6119   0.8878
   0.250   0.2110   0.00727   0.00260  -0.0192   0.6056   0.9247
   0.500   0.2328   0.00719   0.00249  -0.0175   0.5999   0.9510
   0.750   0.2602   0.00709   0.00238  -0.0171   0.5937   0.9715
   1.000   0.2977   0.00704   0.00229  -0.0190   0.5869   0.9939
   1.250   0.3299   0.00709   0.00226  -0.0201   0.5806   1.0000
   1.500   0.3605   0.00713   0.00226  -0.0208   0.5735   1.0000
   1.750   0.3910   0.00721   0.00225  -0.0215   0.5672   1.0000
   2.000   0.4218   0.00725   0.00228  -0.0222   0.5595   1.0000
   2.500   0.4829   0.00739   0.00233  -0.0235   0.5429   1.0000
   2.750   0.5132   0.00749   0.00236  -0.0242   0.5347   1.0000
   3.000   0.5437   0.00757   0.00242  -0.0248   0.5266   1.0000
   3.250   0.5740   0.00768   0.00249  -0.0254   0.5188   1.0000
   3.500   0.6042   0.00778   0.00256  -0.0261   0.5095   1.0000
   3.750   0.6345   0.00789   0.00265  -0.0267   0.5001   1.0000
   4.000   0.6645   0.00803   0.00274  -0.0273   0.4913   1.0000
   4.250   0.6947   0.00813   0.00286  -0.0279   0.4818   1.0000
   4.500   0.7246   0.00827   0.00297  -0.0285   0.4715   1.0000
   5.000   0.7844   0.00856   0.00323  -0.0297   0.4497   1.0000
   5.250   0.8141   0.00872   0.00337  -0.0303   0.4393   1.0000
   5.500   0.8438   0.00890   0.00353  -0.0309   0.4287   1.0000
   5.750   0.8734   0.00907   0.00370  -0.0314   0.4164   1.0000
   6.000   0.9028   0.00926   0.00388  -0.0320   0.4041   1.0000
   6.250   0.9321   0.00947   0.00409  -0.0326   0.3921   1.0000
   6.500   0.9613   0.00971   0.00432  -0.0331   0.3794   1.0000
   6.750   0.9903   0.00997   0.00457  -0.0337   0.3674   1.0000
   7.000   1.0191   0.01024   0.00482  -0.0343   0.3509   1.0000
   7.250   1.0476   0.01058   0.00510  -0.0348   0.3260   1.0000
   7.500   1.0755   0.01102   0.00544  -0.0354   0.2965   1.0000
   7.750   1.1028   0.01157   0.00586  -0.0360   0.2641   1.0000
   8.000   1.1292   0.01225   0.00638  -0.0366   0.2262   1.0000
   8.250   1.1544   0.01309   0.00702  -0.0371   0.1897   1.0000
   8.500   1.1792   0.01389   0.00769  -0.0374   0.1618   1.0000
   8.750   1.2029   0.01476   0.00839  -0.0377   0.1294   1.0000
   9.000   1.2257   0.01568   0.00917  -0.0379   0.1016   1.0000
   9.250   1.2476   0.01661   0.00999  -0.0379   0.0826   1.0000
   9.500   1.2695   0.01746   0.01080  -0.0379   0.0707   1.0000
   9.750   1.2899   0.01838   0.01168  -0.0377   0.0604   1.0000
  10.000   1.3092   0.01934   0.01263  -0.0374   0.0511   1.0000
  10.250   1.3283   0.02023   0.01354  -0.0371   0.0436   1.0000
  10.500   1.3449   0.02130   0.01464  -0.0366   0.0380   1.0000
  10.750   1.3567   0.02266   0.01599  -0.0359   0.0339   1.0000
  11.000   1.3664   0.02386   0.01727  -0.0346   0.0318   1.0000
  11.250   1.3765   0.02516   0.01865  -0.0336   0.0299   1.0000
  11.500   1.3834   0.02685   0.02038  -0.0327   0.0283   1.0000
  11.750   1.3826   0.02937   0.02298  -0.0318   0.0267   1.0000
  12.000   1.3929   0.03094   0.02466  -0.0314   0.0259   1.0000
  12.250   1.4007   0.03280   0.02661  -0.0311   0.0249   1.0000
  12.500   1.4070   0.03488   0.02877  -0.0309   0.0239   1.0000
  12.750   1.4113   0.03719   0.03115  -0.0307   0.0231   1.0000
  13.000   1.4117   0.03997   0.03401  -0.0306   0.0223   1.0000
  13.250   1.4066   0.04334   0.03746  -0.0305   0.0217   1.0000
  13.500   1.4024   0.04663   0.04085  -0.0303   0.0211   1.0000
  13.750   1.4061   0.04912   0.04346  -0.0304   0.0207   1.0000
  14.000   1.4081   0.05183   0.04627  -0.0305   0.0202   1.0000
  14.250   1.4090   0.05470   0.04924  -0.0307   0.0196   1.0000
  14.500   1.4092   0.05772   0.05235  -0.0310   0.0191   1.0000
  14.750   1.4089   0.06088   0.05559  -0.0314   0.0185   1.0000
  15.000   1.4076   0.06423   0.05902  -0.0320   0.0181   1.0000
  15.250   1.4043   0.06785   0.06271  -0.0326   0.0177   1.0000
  15.500   1.3985   0.07175   0.06668  -0.0330   0.0172   1.0000
  15.750   1.3908   0.07573   0.07075  -0.0331   0.0168   1.0000
  16.000   1.3903   0.07928   0.07443  -0.0341   0.0166   1.0000
  16.250   1.3889   0.08301   0.07829  -0.0351   0.0163   1.0000
  16.500   1.3867   0.08686   0.08226  -0.0361   0.0160   1.0000
  16.750   1.3838   0.09087   0.08638  -0.0373   0.0156   1.0000
  17.000   1.3802   0.09503   0.09066  -0.0386   0.0153   1.0000
  17.250   1.3763   0.09934   0.09507  -0.0401   0.0150   1.0000
  17.500   1.3721   0.10373   0.09956  -0.0417   0.0147   1.0000
  17.750   1.3680   0.10819   0.10411  -0.0434   0.0144   1.0000
  18.000   1.3637   0.11266   0.10865  -0.0452   0.0141   1.0000
  18.250   1.3593   0.11711   0.11317  -0.0470   0.0138   1.0000
  18.500   1.3536   0.12172   0.11785  -0.0488   0.0135   1.0000
  19.000   1.3347   0.13249   0.12888  -0.0533   0.0131   1.0000
  19.250   1.3264   0.13828   0.13482  -0.0564   0.0129   1.0000
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