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BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.08 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr7b-il-1000000.txt
Download as CSV file: xf-vr7b-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5951   0.08754   0.08588   0.0157   0.8382   0.0133
  -8.500  -0.5991   0.08184   0.08015   0.0110   0.8253   0.0134
  -8.250  -0.6123   0.07205   0.07028  -0.0015   0.8110   0.0133
  -8.000  -0.6131   0.06540   0.06347  -0.0069   0.7984   0.0135
  -7.750  -0.6094   0.05966   0.05756  -0.0103   0.7861   0.0137
  -7.500  -0.6018   0.05429   0.05198  -0.0127   0.7739   0.0140
  -7.250  -0.5917   0.04830   0.04573  -0.0144   0.7623   0.0149
  -7.000  -0.5821   0.03829   0.03493  -0.0148   0.7529   0.0159
  -6.500  -0.5517   0.02770   0.02363  -0.0154   0.7300   0.0152
  -6.250  -0.5323   0.02086   0.01598  -0.0150   0.7208   0.0142
  -6.000  -0.5061   0.01828   0.01300  -0.0149   0.7112   0.0144
  -5.750  -0.4782   0.01713   0.01163  -0.0150   0.7024   0.0151
  -5.500  -0.4498   0.01624   0.01053  -0.0151   0.6942   0.0156
  -5.250  -0.4211   0.01552   0.00964  -0.0152   0.6873   0.0158
  -5.000  -0.3929   0.01434   0.00828  -0.0153   0.6805   0.0161
  -4.750  -0.3650   0.01305   0.00690  -0.0154   0.6746   0.0165
  -4.500  -0.3363   0.01243   0.00623  -0.0157   0.6687   0.0170
  -4.250  -0.3073   0.01199   0.00573  -0.0159   0.6629   0.0174
  -4.000  -0.2781   0.01158   0.00529  -0.0162   0.6577   0.0180
  -3.750  -0.2487   0.01124   0.00491  -0.0165   0.6522   0.0188
  -3.500  -0.2192   0.01094   0.00455  -0.0168   0.6471   0.0195
  -3.250  -0.1897   0.01063   0.00420  -0.0171   0.6426   0.0199
  -3.000  -0.1601   0.01006   0.00357  -0.0175   0.6377   0.0207
  -2.750  -0.1303   0.00974   0.00320  -0.0179   0.6326   0.0216
  -2.500  -0.1004   0.00952   0.00297  -0.0183   0.6277   0.0227
  -2.250  -0.0705   0.00932   0.00275  -0.0186   0.6225   0.0241
  -2.000  -0.0404   0.00913   0.00251  -0.0190   0.6173   0.0257
  -1.750  -0.0104   0.00894   0.00230  -0.0195   0.6122   0.0287
  -1.500   0.0197   0.00877   0.00213  -0.0198   0.6067   0.0329
  -1.250   0.0498   0.00857   0.00196  -0.0203   0.6010   0.0474
  -1.000   0.0802   0.00797   0.00179  -0.0212   0.5958   0.1823
  -0.750   0.1107   0.00693   0.00164  -0.0225   0.5899   0.4524
  -0.500   0.1408   0.00661   0.00162  -0.0231   0.5840   0.5616
  -0.250   0.1708   0.00642   0.00160  -0.0236   0.5783   0.6206
   0.000   0.2007   0.00622   0.00158  -0.0241   0.5720   0.6847
   0.250   0.2298   0.00599   0.00163  -0.0243   0.5659   0.7835
   0.500   0.2582   0.00586   0.00165  -0.0242   0.5593   0.8280
   0.750   0.2857   0.00582   0.00169  -0.0239   0.5529   0.8705
   1.000   0.3122   0.00580   0.00174  -0.0234   0.5462   0.9025
   1.250   0.3402   0.00585   0.00176  -0.0233   0.5384   0.9200
   1.500   0.3683   0.00587   0.00177  -0.0232   0.5304   0.9335
   1.750   0.3948   0.00588   0.00175  -0.0228   0.5221   0.9476
   2.000   0.4202   0.00582   0.00171  -0.0220   0.5150   0.9627
   2.250   0.4487   0.00582   0.00167  -0.0221   0.5075   0.9780
   2.500   0.4816   0.00582   0.00166  -0.0232   0.4992   1.0000
   2.750   0.5125   0.00593   0.00171  -0.0240   0.4903   1.0000
   3.000   0.5432   0.00600   0.00176  -0.0247   0.4816   1.0000
   3.250   0.5739   0.00611   0.00182  -0.0254   0.4736   1.0000
   3.500   0.6045   0.00621   0.00189  -0.0261   0.4647   1.0000
   3.750   0.6349   0.00633   0.00197  -0.0268   0.4536   1.0000
   4.000   0.6654   0.00646   0.00205  -0.0274   0.4419   1.0000
   4.500   0.7259   0.00671   0.00224  -0.0288   0.4198   1.0000
   4.750   0.7561   0.00686   0.00235  -0.0294   0.4094   1.0000
   5.000   0.7862   0.00702   0.00248  -0.0301   0.3983   1.0000
   5.250   0.8162   0.00719   0.00261  -0.0307   0.3871   1.0000
   5.500   0.8461   0.00736   0.00275  -0.0314   0.3757   1.0000
   5.750   0.8759   0.00754   0.00291  -0.0320   0.3650   1.0000
   6.000   0.9056   0.00774   0.00308  -0.0326   0.3537   1.0000
   6.250   0.9352   0.00792   0.00324  -0.0332   0.3411   1.0000
   6.500   0.9646   0.00818   0.00344  -0.0339   0.3215   1.0000
   6.750   0.9937   0.00857   0.00369  -0.0346   0.2916   1.0000
   7.000   1.0224   0.00903   0.00400  -0.0353   0.2580   1.0000
   7.250   1.0506   0.00958   0.00438  -0.0361   0.2231   1.0000
   7.500   1.0784   0.01020   0.00482  -0.0368   0.1891   1.0000
   7.750   1.1060   0.01074   0.00525  -0.0374   0.1658   1.0000
   8.000   1.1330   0.01134   0.00570  -0.0379   0.1377   1.0000
   8.250   1.1597   0.01193   0.00618  -0.0384   0.1146   1.0000
   8.500   1.1854   0.01267   0.00675  -0.0389   0.0882   1.0000
   8.750   1.2110   0.01330   0.00729  -0.0392   0.0730   1.0000
   9.000   1.2368   0.01384   0.00780  -0.0395   0.0638   1.0000
   9.250   1.2625   0.01432   0.00828  -0.0398   0.0567   1.0000
   9.500   1.2874   0.01489   0.00882  -0.0399   0.0494   1.0000
   9.750   1.3114   0.01552   0.00941  -0.0401   0.0404   1.0000
  10.000   1.3343   0.01624   0.01007  -0.0401   0.0321   1.0000
  10.250   1.3559   0.01705   0.01086  -0.0399   0.0267   1.0000
  10.500   1.3786   0.01765   0.01150  -0.0399   0.0247   1.0000
  10.750   1.3989   0.01846   0.01232  -0.0396   0.0224   1.0000
  11.000   1.4183   0.01928   0.01319  -0.0392   0.0208   1.0000
  11.250   1.4380   0.02002   0.01399  -0.0390   0.0199   1.0000
  11.500   1.4550   0.02092   0.01493  -0.0386   0.0190   1.0000
  11.750   1.4655   0.02202   0.01608  -0.0374   0.0181   1.0000
  12.000   1.4713   0.02357   0.01771  -0.0359   0.0171   1.0000
  12.250   1.4820   0.02486   0.01907  -0.0351   0.0165   1.0000
  12.500   1.4940   0.02611   0.02039  -0.0346   0.0161   1.0000
  12.750   1.5044   0.02755   0.02190  -0.0341   0.0156   1.0000
  13.000   1.5136   0.02917   0.02359  -0.0336   0.0150   1.0000
  13.250   1.5211   0.03100   0.02549  -0.0333   0.0146   1.0000
  13.500   1.5258   0.03319   0.02774  -0.0330   0.0141   1.0000
  13.750   1.5253   0.03599   0.03063  -0.0328   0.0136   1.0000
  14.000   1.5184   0.03957   0.03432  -0.0327   0.0131   1.0000
  14.250   1.5252   0.04165   0.03649  -0.0327   0.0129   1.0000
  14.500   1.5303   0.04393   0.03886  -0.0328   0.0127   1.0000
  14.750   1.5331   0.04650   0.04151  -0.0329   0.0124   1.0000
  15.000   1.5346   0.04922   0.04431  -0.0330   0.0120   1.0000
  15.250   1.5351   0.05213   0.04730  -0.0333   0.0117   1.0000
  15.500   1.5343   0.05525   0.05050  -0.0337   0.0114   1.0000
  15.750   1.5325   0.05858   0.05392  -0.0342   0.0112   1.0000
  16.000   1.5284   0.06231   0.05773  -0.0349   0.0110   1.0000
  16.250   1.5216   0.06648   0.06199  -0.0358   0.0107   1.0000
  16.500   1.5116   0.07118   0.06678  -0.0368   0.0105   1.0000
  16.750   1.4967   0.07671   0.07242  -0.0383   0.0103   1.0000
  17.000   1.4828   0.08216   0.07799  -0.0397   0.0101   1.0000
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