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BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
Reynolds number: 200,000
Max Cl/Cd: 71.38 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr7b-il-200000-n5.txt
Download as CSV file: xf-vr7b-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3937   0.10154   0.09854  -0.0007   0.8824   0.0314
  -9.500  -0.5303   0.10110   0.09801   0.0019   0.9162   0.0268
  -9.250  -0.5319   0.09549   0.09241  -0.0019   0.9078   0.0268
  -8.750  -0.5368   0.08396   0.08089  -0.0060   0.8897   0.0214
  -8.500  -0.5377   0.07983   0.07676  -0.0086   0.8794   0.0211
  -8.250  -0.5431   0.07416   0.07104  -0.0144   0.8677   0.0208
  -8.000  -0.5455   0.06839   0.06515  -0.0186   0.8568   0.0203
  -7.750  -0.5472   0.06241   0.05898  -0.0218   0.8470   0.0198
  -7.500  -0.5459   0.05618   0.05247  -0.0242   0.8369   0.0194
  -7.250  -0.5407   0.04992   0.04585  -0.0257   0.8272   0.0190
  -7.000  -0.5317   0.04441   0.03990  -0.0260   0.8182   0.0189
  -6.750  -0.5171   0.03962   0.03465  -0.0263   0.8081   0.0190
  -6.500  -0.4995   0.03596   0.03055  -0.0260   0.7991   0.0195
  -6.250  -0.4793   0.03235   0.02637  -0.0256   0.7898   0.0206
  -6.000  -0.4568   0.02916   0.02263  -0.0252   0.7811   0.0209
  -5.750  -0.4327   0.02660   0.01955  -0.0247   0.7727   0.0212
  -5.500  -0.4066   0.02457   0.01705  -0.0244   0.7638   0.0215
  -5.250  -0.3810   0.02286   0.01508  -0.0242   0.7554   0.0220
  -5.000  -0.3540   0.02182   0.01393  -0.0243   0.7462   0.0227
  -4.750  -0.3271   0.02101   0.01295  -0.0242   0.7386   0.0239
  -4.500  -0.2991   0.01997   0.01172  -0.0242   0.7307   0.0248
  -4.000  -0.2435   0.01799   0.00939  -0.0238   0.7164   0.0260
  -3.750  -0.2159   0.01722   0.00846  -0.0236   0.7093   0.0266
  -3.500  -0.1880   0.01639   0.00759  -0.0237   0.7015   0.0274
  -3.250  -0.1603   0.01583   0.00699  -0.0237   0.6940   0.0289
  -3.000  -0.1317   0.01539   0.00649  -0.0239   0.6861   0.0309
  -2.750  -0.1032   0.01494   0.00595  -0.0240   0.6790   0.0327
  -2.500  -0.0744   0.01444   0.00538  -0.0243   0.6730   0.0345
  -2.250  -0.0451   0.01407   0.00496  -0.0246   0.6665   0.0375
  -2.000  -0.0161   0.01379   0.00457  -0.0248   0.6607   0.0423
  -1.750   0.0136   0.01346   0.00425  -0.0252   0.6544   0.0525
  -1.500   0.0431   0.01304   0.00393  -0.0257   0.6484   0.0837
  -1.250   0.0697   0.01124   0.00369  -0.0268   0.6435   0.4946
  -1.000   0.0969   0.01074   0.00369  -0.0267   0.6372   0.6325
  -0.750   0.1199   0.01038   0.00379  -0.0250   0.6311   0.7617
  -0.500   0.1401   0.01023   0.00382  -0.0225   0.6259   0.8377
  -0.250   0.1621   0.01018   0.00383  -0.0206   0.6195   0.8882
   0.000   0.1871   0.01017   0.00375  -0.0195   0.6135   0.9215
   0.250   0.2153   0.01015   0.00365  -0.0193   0.6074   0.9444
   0.500   0.2493   0.01011   0.00354  -0.0204   0.6004   0.9647
   1.000   0.3203   0.01012   0.00340  -0.0238   0.5866   1.0000
   1.250   0.3493   0.01020   0.00337  -0.0242   0.5803   1.0000
   1.500   0.3790   0.01027   0.00339  -0.0247   0.5731   1.0000
   1.750   0.4085   0.01036   0.00340  -0.0252   0.5662   1.0000
   2.000   0.4382   0.01045   0.00343  -0.0257   0.5593   1.0000
   2.250   0.4679   0.01054   0.00348  -0.0262   0.5519   1.0000
   2.500   0.4974   0.01065   0.00353  -0.0267   0.5452   1.0000
   2.750   0.5272   0.01076   0.00361  -0.0272   0.5374   1.0000
   3.000   0.5566   0.01088   0.00369  -0.0277   0.5304   1.0000
   3.250   0.5863   0.01100   0.00380  -0.0282   0.5219   1.0000
   3.500   0.6158   0.01114   0.00389  -0.0287   0.5130   1.0000
   3.750   0.6452   0.01127   0.00400  -0.0291   0.5032   1.0000
   4.000   0.6747   0.01142   0.00414  -0.0296   0.4938   1.0000
   4.250   0.7038   0.01159   0.00427  -0.0301   0.4856   1.0000
   4.500   0.7332   0.01175   0.00447  -0.0306   0.4761   1.0000
   4.750   0.7623   0.01193   0.00463  -0.0310   0.4668   1.0000
   5.000   0.7913   0.01213   0.00481  -0.0315   0.4556   1.0000
   5.250   0.8204   0.01232   0.00504  -0.0320   0.4445   1.0000
   5.500   0.8492   0.01253   0.00526  -0.0324   0.4337   1.0000
   5.750   0.8778   0.01276   0.00549  -0.0328   0.4211   1.0000
   6.000   0.9063   0.01301   0.00574  -0.0333   0.4077   1.0000
   6.250   0.9345   0.01328   0.00602  -0.0337   0.3941   1.0000
   6.500   0.9624   0.01361   0.00631  -0.0341   0.3779   1.0000
   6.750   0.9901   0.01393   0.00666  -0.0345   0.3631   1.0000
   7.000   1.0178   0.01426   0.00704  -0.0348   0.3488   1.0000
   7.250   1.0450   0.01464   0.00743  -0.0352   0.3314   1.0000
   7.500   1.0717   0.01506   0.00785  -0.0355   0.3107   1.0000
   7.750   1.0973   0.01560   0.00835  -0.0358   0.2856   1.0000
   8.000   1.1218   0.01628   0.00893  -0.0361   0.2536   1.0000
   8.250   1.1441   0.01719   0.00967  -0.0362   0.2145   1.0000
   8.500   1.1642   0.01832   0.01060  -0.0363   0.1810   1.0000
   8.750   1.1845   0.01933   0.01152  -0.0362   0.1529   1.0000
   9.000   1.2032   0.02042   0.01249  -0.0360   0.1274   1.0000
   9.250   1.2215   0.02146   0.01348  -0.0356   0.1071   1.0000
   9.500   1.2378   0.02261   0.01458  -0.0352   0.0903   1.0000
   9.750   1.2530   0.02377   0.01573  -0.0346   0.0795   1.0000
  10.000   1.2662   0.02502   0.01700  -0.0340   0.0717   1.0000
  10.250   1.2762   0.02625   0.01830  -0.0328   0.0655   1.0000
  10.500   1.2842   0.02773   0.01983  -0.0317   0.0604   1.0000
  10.750   1.2933   0.02922   0.02141  -0.0309   0.0555   1.0000
  11.000   1.2982   0.03117   0.02338  -0.0301   0.0512   1.0000
  11.250   1.3078   0.03275   0.02509  -0.0296   0.0472   1.0000
  11.500   1.3141   0.03471   0.02713  -0.0292   0.0437   1.0000
  11.750   1.3180   0.03698   0.02946  -0.0289   0.0411   1.0000
  12.000   1.3236   0.03913   0.03173  -0.0286   0.0388   1.0000
  12.250   1.3278   0.04147   0.03416  -0.0285   0.0367   1.0000
  12.500   1.3294   0.04412   0.03688  -0.0285   0.0349   1.0000
  12.750   1.3296   0.04696   0.03980  -0.0285   0.0335   1.0000
  13.000   1.3320   0.04958   0.04255  -0.0285   0.0321   1.0000
  13.250   1.3332   0.05237   0.04546  -0.0286   0.0308   1.0000
  13.500   1.3335   0.05530   0.04849  -0.0288   0.0298   1.0000
  13.750   1.3323   0.05845   0.05173  -0.0291   0.0288   1.0000
  14.000   1.3293   0.06191   0.05525  -0.0295   0.0279   1.0000
  14.250   1.3263   0.06539   0.05881  -0.0300   0.0271   1.0000
  14.500   1.3267   0.06856   0.06213  -0.0304   0.0263   1.0000
  14.750   1.3264   0.07190   0.06562  -0.0310   0.0255   1.0000
  15.000   1.3254   0.07538   0.06922  -0.0317   0.0247   1.0000
  15.250   1.3237   0.07902   0.07297  -0.0326   0.0240   1.0000
  15.500   1.3215   0.08283   0.07688  -0.0336   0.0233   1.0000
  15.750   1.3183   0.08683   0.08097  -0.0348   0.0227   1.0000
  16.000   1.3139   0.09099   0.08519  -0.0360   0.0221   1.0000
  16.250   1.3108   0.09502   0.08933  -0.0371   0.0216   1.0000
  16.500   1.3081   0.09914   0.09363  -0.0385   0.0211   1.0000
  16.750   1.3047   0.10344   0.09808  -0.0399   0.0205   1.0000
  17.000   1.3006   0.10788   0.10266  -0.0415   0.0200   1.0000
  17.250   1.2961   0.11248   0.10739  -0.0434   0.0195   1.0000
  17.500   1.2912   0.11722   0.11226  -0.0454   0.0191   1.0000
  17.750   1.2863   0.12208   0.11723  -0.0476   0.0187   1.0000
  18.000   1.2812   0.12702   0.12227  -0.0499   0.0183   1.0000
  18.250   1.2761   0.13198   0.12733  -0.0524   0.0179   1.0000
  18.500   1.2718   0.13671   0.13212  -0.0547   0.0175   1.0000
  18.750   1.2646   0.14236   0.13792  -0.0578   0.0172   1.0000
  19.000   1.2549   0.14886   0.14461  -0.0615   0.0169   1.0000
  19.250   1.2448   0.15563   0.15157  -0.0655   0.0166   1.0000
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