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OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: OAF095 AIRFOIL (oaf095-il)
Reynolds number: 50,000
Max Cl/Cd: 43.83 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf095-il-50000-n5.txt
Download as CSV file: xf-oaf095-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF095 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4451   0.13198   0.12426  -0.0161   1.0000   0.0748
 -11.000  -0.4414   0.12809   0.12039  -0.0178   1.0000   0.0740
 -10.500  -0.4496   0.11828   0.11066  -0.0250   1.0000   0.0688
 -10.250  -0.4438   0.11432   0.10671  -0.0263   1.0000   0.0684
 -10.000  -0.4402   0.11020   0.10262  -0.0280   1.0000   0.0683
  -9.750  -0.4405   0.10567   0.09814  -0.0306   1.0000   0.0686
  -9.500  -0.4304   0.10315   0.09565  -0.0305   1.0000   0.0710
  -9.250  -0.4241   0.10006   0.09259  -0.0314   1.0000   0.0727
  -9.000  -0.4224   0.09618   0.08876  -0.0332   1.0000   0.0733
  -8.750  -0.4229   0.09202   0.08467  -0.0353   1.0000   0.0734
  -8.500  -0.4253   0.08790   0.08062  -0.0372   1.0000   0.0735
  -8.250  -0.4289   0.08394   0.07676  -0.0389   1.0000   0.0740
  -8.000  -0.4309   0.07974   0.07264  -0.0416   1.0000   0.0752
  -7.750  -0.4349   0.07484   0.06783  -0.0453   1.0000   0.0766
  -7.500  -0.4405   0.06839   0.06146  -0.0512   1.0000   0.0776
  -7.250  -0.4441   0.05633   0.04926  -0.0655   1.0000   0.0786
  -7.000  -0.4235   0.04212   0.03400  -0.0850   1.0000   0.0815
  -6.750  -0.4062   0.04132   0.03329  -0.0840   1.0000   0.0850
  -6.500  -0.3796   0.03753   0.02902  -0.0884   1.0000   0.0913
  -6.250  -0.3517   0.03424   0.02527  -0.0917   1.0000   0.0968
  -6.000  -0.3269   0.03265   0.02345  -0.0929   1.0000   0.1042
  -5.750  -0.3004   0.03086   0.02140  -0.0944   1.0000   0.1117
  -5.500  -0.2719   0.02918   0.01930  -0.0960   1.0000   0.1223
  -5.250  -0.2485   0.02852   0.01868  -0.0961   1.0000   0.1315
  -5.000  -0.2225   0.02764   0.01764  -0.0968   1.0000   0.1431
  -4.750  -0.1963   0.02686   0.01671  -0.0974   1.0000   0.1564
  -4.500  -0.1703   0.02627   0.01602  -0.0979   1.0000   0.1713
  -4.250  -0.1450   0.02581   0.01545  -0.0983   1.0000   0.1866
  -4.000  -0.1198   0.02547   0.01504  -0.0986   1.0000   0.2029
  -3.750  -0.0815   0.02508   0.01452  -0.1013   0.9948   0.2243
  -3.500  -0.0431   0.02477   0.01411  -0.1039   0.9885   0.2448
  -3.250  -0.0034   0.02457   0.01387  -0.1067   0.9830   0.2657
  -3.000   0.0336   0.02437   0.01356  -0.1089   0.9758   0.2874
  -2.750   0.0738   0.02423   0.01337  -0.1117   0.9703   0.3088
  -2.500   0.1085   0.02413   0.01325  -0.1133   0.9623   0.3294
  -2.250   0.1492   0.02404   0.01307  -0.1161   0.9566   0.3538
  -2.000   0.1825   0.02400   0.01303  -0.1174   0.9482   0.3745
  -1.750   0.2229   0.02392   0.01289  -0.1201   0.9423   0.3992
  -1.500   0.2556   0.02390   0.01289  -0.1212   0.9337   0.4209
  -1.250   0.2955   0.02381   0.01279  -0.1236   0.9276   0.4458
  -1.000   0.3277   0.02381   0.01283  -0.1246   0.9189   0.4685
  -0.750   0.3654   0.02374   0.01278  -0.1265   0.9122   0.4952
  -0.500   0.3953   0.02375   0.01289  -0.1270   0.9029   0.5199
  -0.250   0.4310   0.02366   0.01290  -0.1284   0.8962   0.5492
   0.000   0.4589   0.02370   0.01307  -0.1284   0.8864   0.5787
   0.250   0.4933   0.02356   0.01309  -0.1294   0.8799   0.6146
   0.500   0.5182   0.02360   0.01333  -0.1289   0.8697   0.6531
   0.750   0.5483   0.02335   0.01337  -0.1287   0.8629   0.7092
   1.000   0.5645   0.02314   0.01354  -0.1259   0.8523   0.8115
   1.250   0.5909   0.02323   0.01364  -0.1257   0.8420   1.0000
   1.500   0.6256   0.02346   0.01379  -0.1270   0.8342   1.0000
   1.750   0.6540   0.02385   0.01414  -0.1272   0.8235   1.0000
   2.000   0.6877   0.02401   0.01427  -0.1280   0.8156   1.0000
   2.250   0.7157   0.02434   0.01463  -0.1280   0.8044   1.0000
   2.500   0.7434   0.02468   0.01500  -0.1278   0.7933   1.0000
   2.750   0.7754   0.02478   0.01514  -0.1280   0.7845   1.0000
   3.000   0.8029   0.02506   0.01551  -0.1276   0.7728   1.0000
   3.250   0.8296   0.02533   0.01586  -0.1271   0.7601   1.0000
   3.500   0.8574   0.02545   0.01607  -0.1264   0.7470   1.0000
   3.750   0.8854   0.02544   0.01616  -0.1255   0.7324   1.0000
   4.000   0.9130   0.02535   0.01619  -0.1243   0.7160   1.0000
   4.250   0.9403   0.02516   0.01611  -0.1228   0.6979   1.0000
   4.500   0.9684   0.02480   0.01584  -0.1212   0.6781   1.0000
   4.750   0.9918   0.02472   0.01589  -0.1193   0.6523   1.0000
   5.000   1.0158   0.02451   0.01576  -0.1171   0.6228   1.0000
   5.250   1.0390   0.02435   0.01563  -0.1149   0.5873   1.0000
   5.500   1.0603   0.02440   0.01571  -0.1126   0.5432   1.0000
   5.750   1.0799   0.02464   0.01583  -0.1101   0.4867   1.0000
   6.000   1.0968   0.02526   0.01614  -0.1075   0.4073   1.0000
   6.250   1.1078   0.02664   0.01685  -0.1046   0.3131   1.0000
   6.500   1.1161   0.02862   0.01824  -0.1021   0.2389   1.0000
   6.750   1.1254   0.03066   0.01991  -0.1000   0.1908   1.0000
   7.000   1.1359   0.03261   0.02160  -0.0980   0.1597   1.0000
   7.250   1.1483   0.03440   0.02329  -0.0961   0.1381   1.0000
   7.500   1.1615   0.03614   0.02497  -0.0943   0.1223   1.0000
   7.750   1.1763   0.03783   0.02667  -0.0925   0.1107   1.0000
   8.000   1.1920   0.03953   0.02832  -0.0910   0.1011   1.0000
   8.250   1.2116   0.04112   0.03007  -0.0896   0.0925   1.0000
   8.500   1.2327   0.04288   0.03185  -0.0885   0.0859   1.0000
   8.750   1.2533   0.04461   0.03373  -0.0874   0.0794   1.0000
   9.000   1.2776   0.04668   0.03578  -0.0868   0.0749   1.0000
   9.250   1.2990   0.04889   0.03836  -0.0858   0.0703   1.0000
   9.500   1.3162   0.05100   0.04060  -0.0846   0.0663   1.0000
   9.750   1.3369   0.05361   0.04322  -0.0840   0.0635   1.0000
  10.000   1.3493   0.05669   0.04682  -0.0823   0.0614   1.0000
  10.250   1.3566   0.05978   0.05034  -0.0804   0.0592   1.0000
  10.500   1.3612   0.06272   0.05360  -0.0784   0.0571   1.0000
  10.750   1.3633   0.06555   0.05665  -0.0764   0.0553   1.0000
  11.000   1.3634   0.06848   0.05976  -0.0743   0.0541   1.0000
  11.250   1.3621   0.07193   0.06340  -0.0724   0.0533   1.0000
  11.500   1.3537   0.07588   0.06758  -0.0705   0.0528   1.0000
  11.750   1.3360   0.08027   0.07233  -0.0688   0.0526   1.0000
  12.000   1.3159   0.08514   0.07753  -0.0680   0.0525   1.0000
  12.250   1.2938   0.09058   0.08327  -0.0682   0.0524   1.0000
  12.500   1.2701   0.09669   0.08964  -0.0695   0.0525   1.0000
  12.750   1.2454   0.10353   0.09672  -0.0720   0.0526   1.0000
  13.000   1.2202   0.11121   0.10459  -0.0758   0.0527   1.0000
  13.250   1.1266   0.13736   0.13115  -0.0963   0.0559   1.0000
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