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BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
Reynolds number: 100,000
Max Cl/Cd: 53.43 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr7b-il-100000-n5.txt
Download as CSV file: xf-vr7b-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4703   0.09874   0.09454  -0.0070   1.0000   0.0573
  -8.750  -0.4668   0.09391   0.08975  -0.0111   1.0000   0.0576
  -8.500  -0.4954   0.07501   0.07065  -0.0341   0.9736   0.0332
  -8.250  -0.4914   0.07029   0.06581  -0.0375   0.9567   0.0330
  -8.000  -0.4916   0.06575   0.06109  -0.0397   0.9417   0.0330
  -7.750  -0.4906   0.06138   0.05648  -0.0410   0.9277   0.0330
  -7.500  -0.4857   0.05722   0.05207  -0.0419   0.9144   0.0330
  -7.250  -0.4766   0.05340   0.04802  -0.0422   0.9018   0.0328
  -7.000  -0.4654   0.04974   0.04412  -0.0424   0.8899   0.0324
  -6.750  -0.4531   0.04613   0.04019  -0.0421   0.8790   0.0321
  -6.500  -0.4380   0.04261   0.03628  -0.0418   0.8682   0.0319
  -6.250  -0.4202   0.03931   0.03252  -0.0414   0.8578   0.0318
  -6.000  -0.4017   0.03642   0.02915  -0.0405   0.8490   0.0320
  -5.750  -0.3790   0.03400   0.02606  -0.0399   0.8389   0.0332
  -5.500  -0.3574   0.03172   0.02352  -0.0394   0.8301   0.0342
  -5.250  -0.3337   0.02983   0.02135  -0.0388   0.8213   0.0346
  -5.000  -0.3088   0.02809   0.01930  -0.0382   0.8128   0.0350
  -4.750  -0.2839   0.02656   0.01751  -0.0375   0.8048   0.0356
  -4.500  -0.2577   0.02519   0.01591  -0.0370   0.7966   0.0364
  -4.250  -0.2321   0.02403   0.01456  -0.0362   0.7889   0.0378
  -4.000  -0.2053   0.02308   0.01338  -0.0358   0.7809   0.0400
  -3.750  -0.1790   0.02216   0.01228  -0.0351   0.7736   0.0415
  -3.500  -0.1532   0.02101   0.01115  -0.0347   0.7662   0.0430
  -3.250  -0.1272   0.02018   0.01029  -0.0342   0.7586   0.0449
  -3.000  -0.1011   0.01949   0.00953  -0.0338   0.7514   0.0476
  -2.750  -0.0743   0.01891   0.00885  -0.0335   0.7432   0.0520
  -2.500  -0.0477   0.01832   0.00821  -0.0332   0.7353   0.0576
  -2.250  -0.0206   0.01778   0.00756  -0.0329   0.7269   0.0655
  -2.000   0.0068   0.01715   0.00695  -0.0328   0.7189   0.0861
  -1.750   0.0286   0.01495   0.00655  -0.0327   0.7118   0.4800
  -1.500   0.0457   0.01421   0.00666  -0.0294   0.7056   0.7086
  -1.250   0.0622   0.01406   0.00679  -0.0253   0.6983   0.8302
  -1.000   0.0818   0.01402   0.00674  -0.0217   0.6927   0.9146
  -0.750   0.1217   0.01398   0.00656  -0.0234   0.6847   0.9618
  -0.500   0.1663   0.01394   0.00629  -0.0267   0.6780   0.9844
  -0.250   0.2080   0.01395   0.00613  -0.0298   0.6705   1.0000
   0.000   0.2319   0.01399   0.00600  -0.0294   0.6635   1.0000
   0.250   0.2568   0.01406   0.00590  -0.0291   0.6569   1.0000
   0.500   0.2835   0.01416   0.00588  -0.0292   0.6492   1.0000
   0.750   0.3095   0.01425   0.00580  -0.0289   0.6434   1.0000
   1.000   0.3380   0.01440   0.00588  -0.0294   0.6350   1.0000
   1.250   0.3652   0.01451   0.00586  -0.0294   0.6285   1.0000
   1.500   0.3938   0.01467   0.00596  -0.0298   0.6207   1.0000
   1.750   0.4218   0.01480   0.00600  -0.0299   0.6137   1.0000
   2.000   0.4503   0.01496   0.00610  -0.0303   0.6063   1.0000
   2.250   0.4788   0.01512   0.00622  -0.0305   0.5987   1.0000
   2.500   0.5071   0.01528   0.00632  -0.0308   0.5917   1.0000
   2.750   0.5359   0.01546   0.00649  -0.0312   0.5837   1.0000
   3.000   0.5641   0.01561   0.00660  -0.0313   0.5770   1.0000
   3.250   0.5929   0.01581   0.00682  -0.0318   0.5685   1.0000
   3.500   0.6211   0.01597   0.00693  -0.0319   0.5619   1.0000
   3.750   0.6499   0.01619   0.00720  -0.0323   0.5532   1.0000
   4.000   0.6780   0.01635   0.00733  -0.0324   0.5464   1.0000
   4.250   0.7065   0.01658   0.00763  -0.0328   0.5373   1.0000
   4.500   0.7346   0.01675   0.00781  -0.0330   0.5288   1.0000
   4.750   0.7627   0.01693   0.00801  -0.0332   0.5190   1.0000
   5.000   0.7908   0.01715   0.00829  -0.0335   0.5090   1.0000
   5.250   0.8185   0.01732   0.00845  -0.0335   0.5009   1.0000
   5.500   0.8464   0.01759   0.00882  -0.0338   0.4898   1.0000
   5.750   0.8740   0.01782   0.00910  -0.0340   0.4793   1.0000
   6.000   0.9014   0.01801   0.00929  -0.0340   0.4696   1.0000
   6.250   0.9288   0.01833   0.00975  -0.0343   0.4580   1.0000
   6.500   0.9559   0.01863   0.01013  -0.0344   0.4469   1.0000
   6.750   0.9827   0.01890   0.01047  -0.0345   0.4344   1.0000
   7.000   1.0089   0.01917   0.01083  -0.0345   0.4175   1.0000
   7.250   1.0344   0.01947   0.01116  -0.0345   0.3982   1.0000
   7.500   1.0593   0.01983   0.01151  -0.0344   0.3788   1.0000
   7.750   1.0841   0.02029   0.01204  -0.0343   0.3619   1.0000
   8.000   1.1083   0.02080   0.01265  -0.0343   0.3439   1.0000
   8.250   1.1316   0.02137   0.01331  -0.0342   0.3219   1.0000
   8.500   1.1531   0.02205   0.01402  -0.0340   0.2961   1.0000
   8.750   1.1724   0.02291   0.01483  -0.0336   0.2656   1.0000
   9.000   1.1888   0.02401   0.01583  -0.0331   0.2319   1.0000
   9.250   1.2017   0.02539   0.01706  -0.0323   0.1993   1.0000
   9.500   1.2118   0.02695   0.01850  -0.0314   0.1732   1.0000
   9.750   1.2204   0.02858   0.02009  -0.0305   0.1497   1.0000
  10.000   1.2247   0.03034   0.02180  -0.0292   0.1308   1.0000
  10.250   1.2276   0.03224   0.02368  -0.0280   0.1162   1.0000
  10.500   1.2309   0.03427   0.02572  -0.0270   0.1039   1.0000
  10.750   1.2332   0.03650   0.02796  -0.0263   0.0945   1.0000
  11.000   1.2340   0.03897   0.03043  -0.0258   0.0869   1.0000
  11.250   1.2366   0.04135   0.03290  -0.0253   0.0803   1.0000
  11.500   1.2364   0.04409   0.03569  -0.0251   0.0750   1.0000
  11.750   1.2377   0.04673   0.03841  -0.0248   0.0701   1.0000
  12.000   1.2389   0.04943   0.04122  -0.0247   0.0655   1.0000
  12.250   1.2366   0.05251   0.04431  -0.0246   0.0622   1.0000
  12.500   1.2390   0.05512   0.04705  -0.0243   0.0590   1.0000
  12.750   1.2407   0.05784   0.04989  -0.0242   0.0559   1.0000
  13.000   1.2408   0.06077   0.05288  -0.0242   0.0533   1.0000
  13.250   1.2400   0.06371   0.05580  -0.0240   0.0510   1.0000
  13.500   1.2432   0.06642   0.05874  -0.0240   0.0486   1.0000
  13.750   1.2451   0.06930   0.06177  -0.0240   0.0463   1.0000
  14.000   1.2466   0.07224   0.06482  -0.0242   0.0445   1.0000
  14.250   1.2477   0.07524   0.06789  -0.0244   0.0431   1.0000
  14.500   1.2496   0.07810   0.07076  -0.0244   0.0416   1.0000
  14.750   1.2498   0.08155   0.07446  -0.0249   0.0402   1.0000
  15.000   1.2486   0.08522   0.07833  -0.0257   0.0388   1.0000
  15.250   1.2465   0.08906   0.08235  -0.0266   0.0375   1.0000
  15.500   1.2444   0.09296   0.08638  -0.0277   0.0364   1.0000
  15.750   1.2425   0.09683   0.09036  -0.0289   0.0355   1.0000
  16.000   1.2413   0.10057   0.09419  -0.0300   0.0347   1.0000
  16.250   1.2395   0.10444   0.09813  -0.0310   0.0338   1.0000
  16.500   1.2289   0.11035   0.10432  -0.0337   0.0332   1.0000
  16.750   1.2165   0.11679   0.11102  -0.0368   0.0327   1.0000
  17.000   1.2021   0.12387   0.11834  -0.0406   0.0322   1.0000
  17.250   1.1853   0.13175   0.12645  -0.0450   0.0319   1.0000
  17.500   1.1651   0.14088   0.13580  -0.0505   0.0317   1.0000
  17.750   1.1376   0.15255   0.14768  -0.0578   0.0319   1.0000
  18.000   1.0903   0.17143   0.16674  -0.0698   0.0327   1.0000
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