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OAF139 AIRFOIL (oaf139-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: OAF139 AIRFOIL (oaf139-il)
Reynolds number: 50,000
Max Cl/Cd: 20.87 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf139-il-50000-n5.txt
Download as CSV file: xf-oaf139-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF139 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -1.1276   0.08603   0.07792   0.0333   1.0000   0.1274
 -12.500  -1.1888   0.07260   0.06410   0.0254   1.0000   0.1283
 -12.250  -1.2235   0.06471   0.05586   0.0218   1.0000   0.1300
 -12.000  -1.2030   0.06415   0.05544   0.0230   1.0000   0.1339
 -11.750  -1.2102   0.06029   0.05142   0.0224   1.0000   0.1371
 -11.500  -1.2238   0.05608   0.04695   0.0222   1.0000   0.1403
 -11.250  -1.2324   0.05274   0.04335   0.0232   1.0000   0.1440
 -11.000  -1.2191   0.05136   0.04204   0.0241   1.0000   0.1485
 -10.750  -1.2153   0.04887   0.03934   0.0250   1.0000   0.1538
 -10.500  -1.2067   0.04673   0.03706   0.0258   1.0000   0.1594
 -10.250  -1.1934   0.04517   0.03546   0.0266   1.0000   0.1657
 -10.000  -1.1826   0.04306   0.03312   0.0274   1.0000   0.1728
  -9.750  -1.1657   0.04178   0.03187   0.0282   1.0000   0.1802
  -9.500  -1.1507   0.04008   0.03000   0.0288   1.0000   0.1889
  -9.250  -1.1329   0.03875   0.02861   0.0295   1.0000   0.1980
  -9.000  -1.1140   0.03751   0.02736   0.0301   1.0000   0.2076
  -8.750  -1.0954   0.03610   0.02580   0.0306   1.0000   0.2188
  -8.500  -1.0742   0.03517   0.02488   0.0312   1.0000   0.2296
  -8.250  -1.0524   0.03425   0.02396   0.0317   1.0000   0.2409
  -8.000  -1.0305   0.03328   0.02290   0.0321   1.0000   0.2534
  -7.750  -1.0080   0.03232   0.02182   0.0324   1.0000   0.2668
  -7.500  -0.9841   0.03165   0.02114   0.0328   1.0000   0.2793
  -7.250  -0.9596   0.03101   0.02051   0.0332   1.0000   0.2917
  -7.000  -0.9350   0.03032   0.01977   0.0335   1.0000   0.3049
  -6.750  -0.9100   0.02961   0.01898   0.0337   1.0000   0.3185
  -6.500  -0.8844   0.02900   0.01830   0.0339   1.0000   0.3323
  -6.250  -0.8580   0.02857   0.01793   0.0342   1.0000   0.3444
  -6.000  -0.8316   0.02804   0.01738   0.0344   1.0000   0.3573
  -5.750  -0.8050   0.02746   0.01675   0.0345   1.0000   0.3709
  -5.500  -0.7780   0.02692   0.01614   0.0345   1.0000   0.3845
  -5.250  -0.7505   0.02652   0.01583   0.0348   1.0000   0.3959
  -5.000  -0.7228   0.02601   0.01530   0.0348   1.0000   0.4085
  -4.750  -0.6949   0.02544   0.01466   0.0346   1.0000   0.4220
  -4.500  -0.6668   0.02506   0.01436   0.0348   1.0000   0.4330
  -4.250  -0.6383   0.02459   0.01392   0.0347   1.0000   0.4451
  -4.000  -0.6095   0.02407   0.01336   0.0343   1.0000   0.4582
  -3.750  -0.5807   0.02370   0.01309   0.0343   1.0000   0.4696
  -3.500  -0.5515   0.02328   0.01272   0.0340   1.0000   0.4815
  -3.250  -0.5217   0.02283   0.01229   0.0335   1.0000   0.4949
  -3.000  -0.4920   0.02248   0.01207   0.0332   1.0000   0.5066
  -2.750  -0.4615   0.02210   0.01181   0.0326   1.0000   0.5189
  -2.500  -0.4299   0.02172   0.01152   0.0315   1.0000   0.5326
  -2.250  -0.3953   0.02153   0.01145   0.0300   0.9334   0.5464
  -2.000  -0.3665   0.02169   0.01155   0.0305   0.8455   0.5591
  -1.750  -0.3440   0.02178   0.01153   0.0323   0.7958   0.5723
  -1.500  -0.3206   0.02182   0.01142   0.0337   0.7582   0.5867
  -1.250  -0.2971   0.02187   0.01141   0.0354   0.7274   0.5990
  -1.000  -0.2716   0.02187   0.01135   0.0364   0.6995   0.6126
  -0.750  -0.2456   0.02185   0.01125   0.0373   0.6750   0.6269
  -0.500  -0.2194   0.02186   0.01118   0.0381   0.6529   0.6415
  -0.250  -0.1930   0.02185   0.01117   0.0390   0.6315   0.6554
   0.000  -0.1660   0.02184   0.01115   0.0396   0.6113   0.6701
   0.250  -0.1390   0.02184   0.01114   0.0402   0.5918   0.6859
   0.500  -0.1120   0.02185   0.01115   0.0409   0.5733   0.7025
   0.750  -0.0852   0.02186   0.01118   0.0416   0.5555   0.7200
   1.000  -0.0587   0.02189   0.01122   0.0424   0.5387   0.7383
   1.250  -0.0323   0.02191   0.01131   0.0433   0.5223   0.7574
   1.500  -0.0058   0.02195   0.01142   0.0441   0.5058   0.7775
   1.750   0.0206   0.02199   0.01156   0.0450   0.4900   0.7990
   2.000   0.0469   0.02204   0.01169   0.0459   0.4747   0.8223
   2.250   0.0738   0.02210   0.01179   0.0467   0.4598   0.8482
   2.500   0.1024   0.02215   0.01188   0.0472   0.4453   0.8751
   2.750   0.1349   0.02225   0.01203   0.0468   0.4287   0.9051
   3.000   0.1736   0.02240   0.01223   0.0449   0.4110   0.9356
   3.250   0.2168   0.02260   0.01244   0.0420   0.3925   0.9672
   3.500   0.2594   0.02281   0.01264   0.0388   0.3743   1.0000
   3.750   0.2838   0.02309   0.01287   0.0387   0.3594   1.0000
   4.000   0.3104   0.02343   0.01315   0.0384   0.3447   1.0000
   4.250   0.3377   0.02380   0.01344   0.0382   0.3307   1.0000
   4.500   0.3652   0.02415   0.01369   0.0380   0.3172   1.0000
   4.750   0.3935   0.02462   0.01415   0.0376   0.3027   1.0000
   5.000   0.4219   0.02516   0.01472   0.0372   0.2881   1.0000
   5.250   0.4502   0.02575   0.01531   0.0368   0.2744   1.0000
   5.500   0.4781   0.02631   0.01584   0.0366   0.2617   1.0000
   5.750   0.5056   0.02686   0.01631   0.0365   0.2498   1.0000
   6.000   0.5337   0.02766   0.01722   0.0360   0.2365   1.0000
   6.250   0.5613   0.02851   0.01812   0.0356   0.2245   1.0000
   6.500   0.5883   0.02920   0.01873   0.0355   0.2143   1.0000
   6.750   0.6153   0.03017   0.01982   0.0350   0.2030   1.0000
   7.000   0.6419   0.03130   0.02106   0.0346   0.1925   1.0000
   7.250   0.6679   0.03201   0.02165   0.0346   0.1841   1.0000
   7.500   0.6935   0.03354   0.02347   0.0338   0.1737   1.0000
   7.750   0.7185   0.03464   0.02459   0.0336   0.1656   1.0000
   8.000   0.7427   0.03606   0.02619   0.0331   0.1570   1.0000
   8.250   0.7658   0.03761   0.02786   0.0326   0.1495   1.0000
   8.500   0.7885   0.03908   0.02945   0.0323   0.1424   1.0000
   8.750   0.8092   0.04097   0.03149   0.0317   0.1359   1.0000
   9.000   0.8283   0.04300   0.03373   0.0311   0.1296   1.0000
   9.250   0.8486   0.04451   0.03523   0.0310   0.1247   1.0000
   9.500   0.8572   0.04838   0.03957   0.0291   0.1191   1.0000
   9.750   0.8755   0.04986   0.04103   0.0291   0.1149   1.0000
  10.000   0.8783   0.05395   0.04542   0.0272   0.1112   1.0000
  10.250   0.8487   0.06262   0.05458   0.0207   0.1089   1.0000
  10.500   0.7198   0.09181   0.08402  -0.0038   0.1092   1.0000
  10.750   0.6947   0.10181   0.09399  -0.0099   0.1062   1.0000
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