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BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il)
Reynolds number: 50,000
Max Cl/Cd: 30.59 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr1-il-50000.txt
Download as CSV file: xf-vr1-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4929   0.13614   0.12834  -0.0145   1.0000   0.2347
 -11.250  -0.4612   0.12998   0.12210  -0.0132   1.0000   0.2423
 -11.000  -0.4832   0.12946   0.12172  -0.0152   1.0000   0.2502
 -10.750  -0.4526   0.12371   0.11589  -0.0140   1.0000   0.2589
 -10.500  -0.4623   0.12155   0.11384  -0.0150   1.0000   0.2672
 -10.250  -0.4535   0.11849   0.11078  -0.0147   1.0000   0.2795
 -10.000  -0.4394   0.11439   0.10670  -0.0143   1.0000   0.2884
  -9.750  -0.4504   0.11242   0.10483  -0.0148   1.0000   0.2995
  -9.500  -0.4459   0.10979   0.10224  -0.0144   1.0000   0.3132
  -9.250  -0.3259   0.09847   0.09148  -0.0191   1.0000   0.3258
  -9.000  -0.3280   0.09525   0.08832  -0.0189   1.0000   0.3346
  -8.750  -0.4373   0.10067   0.09329  -0.0131   1.0000   0.3484
  -8.500  -0.4158   0.09656   0.08918  -0.0124   1.0000   0.3588
  -8.250  -0.4121   0.09342   0.08610  -0.0118   1.0000   0.3696
  -8.000  -0.4160   0.09093   0.08370  -0.0109   1.0000   0.3828
  -7.750  -0.4072   0.08768   0.08050  -0.0104   1.0000   0.3902
  -7.500  -0.4145   0.08500   0.07793  -0.0095   1.0000   0.3992
  -7.250  -0.6106   0.06466   0.05729  -0.0333   1.0000   0.1704
  -7.000  -0.6072   0.05939   0.05197  -0.0321   1.0000   0.1574
  -6.750  -0.6064   0.05564   0.04800  -0.0301   1.0000   0.1489
  -6.500  -0.6160   0.05137   0.04305  -0.0275   1.0000   0.1381
  -6.250  -0.6082   0.04819   0.03972  -0.0254   1.0000   0.1349
  -6.000  -0.6025   0.04491   0.03606  -0.0231   1.0000   0.1304
  -5.750  -0.5968   0.04205   0.03226  -0.0201   1.0000   0.1248
  -5.500  -0.5823   0.03964   0.02956  -0.0183   1.0000   0.1235
  -5.250  -0.5666   0.03733   0.02698  -0.0165   1.0000   0.1228
  -5.000  -0.5495   0.03527   0.02459  -0.0148   1.0000   0.1228
  -4.750  -0.5313   0.03362   0.02252  -0.0130   1.0000   0.1241
  -4.500  -0.5118   0.03172   0.02059  -0.0119   1.0000   0.1273
  -4.250  -0.4913   0.03032   0.01910  -0.0106   1.0000   0.1313
  -4.000  -0.4690   0.02902   0.01763  -0.0093   1.0000   0.1352
  -3.750  -0.4457   0.02785   0.01626  -0.0080   1.0000   0.1402
  -3.500  -0.4234   0.02670   0.01524  -0.0068   1.0000   0.1491
  -3.250  -0.4019   0.02569   0.01429  -0.0054   1.0000   0.1642
  -3.000  -0.3803   0.02438   0.01318  -0.0043   1.0000   0.1949
  -2.750  -0.0974   0.02387   0.01520  -0.0328   1.0000   1.0000
  -2.500  -0.1109   0.02346   0.01473  -0.0287   1.0000   1.0000
  -2.250  -0.1230   0.02309   0.01428  -0.0244   1.0000   1.0000
  -2.000  -0.1332   0.02276   0.01387  -0.0202   1.0000   1.0000
  -1.750  -0.1409   0.02249   0.01348  -0.0161   1.0000   1.0000
  -1.500  -0.1452   0.02229   0.01315  -0.0123   1.0000   1.0000
  -1.250  -0.1456   0.02216   0.01288  -0.0089   1.0000   1.0000
  -1.000  -0.1421   0.02213   0.01269  -0.0061   1.0000   1.0000
  -0.750  -0.1354   0.02218   0.01258  -0.0036   1.0000   1.0000
  -0.500  -0.1265   0.02230   0.01254  -0.0015   1.0000   1.0000
  -0.250  -0.1156   0.02249   0.01256   0.0004   1.0000   1.0000
   0.000  -0.1032   0.02273   0.01266   0.0020   1.0000   1.0000
   0.250  -0.0896   0.02302   0.01283   0.0034   1.0000   1.0000
   0.500  -0.0751   0.02336   0.01305   0.0046   1.0000   1.0000
   0.750  -0.0600   0.02374   0.01333   0.0057   1.0000   1.0000
   1.000  -0.0444   0.02416   0.01366   0.0067   1.0000   1.0000
   1.250  -0.0285   0.02462   0.01404   0.0075   1.0000   1.0000
   1.500  -0.0124   0.02512   0.01449   0.0083   1.0000   1.0000
   1.750   0.0040   0.02567   0.01498   0.0090   1.0000   1.0000
   2.000   0.0204   0.02625   0.01553   0.0096   1.0000   1.0000
   2.250   0.0368   0.02688   0.01613   0.0102   1.0000   1.0000
   2.500   0.0532   0.02756   0.01679   0.0107   1.0000   1.0000
   2.750   0.0882   0.02883   0.01809   0.0074   0.9918   1.0000
   3.000   0.1314   0.03034   0.01966   0.0027   0.9778   1.0000
   3.250   0.1723   0.03176   0.02116  -0.0014   0.9631   1.0000
   3.500   0.2123   0.03313   0.02264  -0.0052   0.9472   1.0000
   3.750   0.2520   0.03447   0.02410  -0.0088   0.9303   1.0000
   4.000   0.2964   0.03584   0.02564  -0.0129   0.9113   1.0000
   4.250   0.3470   0.03677   0.02680  -0.0171   0.8807   1.0000
   4.500   0.4877   0.03419   0.02486  -0.0283   0.7990   1.0000
   4.750   0.6131   0.02867   0.02017  -0.0338   0.7392   1.0000
   5.000   0.6692   0.02188   0.01358  -0.0240   0.5629   1.0000
   5.250   0.6624   0.02387   0.01311  -0.0153   0.3019   1.0000
   5.500   0.6739   0.02594   0.01448  -0.0125   0.2480   1.0000
   5.750   0.7023   0.02777   0.01602  -0.0121   0.2138   1.0000
   6.000   0.7404   0.02969   0.01769  -0.0132   0.1906   1.0000
   6.250   0.7751   0.03162   0.01954  -0.0138   0.1750   1.0000
   6.500   0.8060   0.03369   0.02181  -0.0138   0.1660   1.0000
   6.750   0.8360   0.03615   0.02412  -0.0141   0.1574   1.0000
   7.000   0.8555   0.03809   0.02655  -0.0124   0.1529   1.0000
   7.250   0.8762   0.04054   0.02936  -0.0111   0.1503   1.0000
   7.500   0.8945   0.04308   0.03223  -0.0096   0.1476   1.0000
   7.750   0.9140   0.04579   0.03503  -0.0086   0.1441   1.0000
   8.000   0.9306   0.04923   0.03861  -0.0075   0.1422   1.0000
   8.250   0.9426   0.05248   0.04225  -0.0056   0.1425   1.0000
   8.500   0.9346   0.05539   0.04599  -0.0014   0.1459   1.0000
   8.750   0.9265   0.05950   0.05064   0.0016   0.1497   1.0000
   9.000   0.9208   0.06374   0.05519   0.0039   0.1529   1.0000
   9.250   0.9199   0.06813   0.05977   0.0054   0.1555   1.0000
   9.500   0.8761   0.07310   0.06518   0.0086   0.1630   1.0000
   9.750   0.8450   0.07839   0.07058   0.0102   0.1690   1.0000
  10.000   0.7708   0.08779   0.08006   0.0062   0.1804   1.0000
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