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MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MB253515 15.0% smoothed (mb253515sm-il)
Reynolds number: 50,000
Max Cl/Cd: 7.54 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mb253515sm-il-50000.txt
Download as CSV file: xf-mb253515sm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MB253515 15.0% smoothed                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3355   0.10977   0.10310  -0.0276   1.0000   0.3539
  -9.500  -0.3174   0.10514   0.09846  -0.0273   1.0000   0.3597
  -9.250  -0.3345   0.10370   0.09718  -0.0263   1.0000   0.3706
  -9.000  -0.3253   0.09970   0.09321  -0.0261   1.0000   0.3726
  -8.750  -0.3277   0.09661   0.09021  -0.0257   1.0000   0.3733
  -8.500  -0.4835   0.08070   0.07492  -0.0430   1.0000   0.1944
  -8.250  -0.5297   0.07940   0.07381  -0.0378   1.0000   0.1935
  -8.000  -0.5770   0.07768   0.07220  -0.0330   1.0000   0.1920
  -7.750  -0.6079   0.07436   0.06887  -0.0300   1.0000   0.1812
  -7.500  -0.6662   0.07102   0.06531  -0.0258   1.0000   0.1752
  -7.250  -0.6760   0.06654   0.06069  -0.0236   1.0000   0.1632
  -7.000  -0.6890   0.06263   0.05649  -0.0209   1.0000   0.1538
  -6.750  -0.7076   0.05842   0.05159  -0.0176   1.0000   0.1437
  -6.500  -0.7035   0.05495   0.04796  -0.0154   1.0000   0.1390
  -6.250  -0.7116   0.05163   0.04354  -0.0115   1.0000   0.1309
  -6.000  -0.7000   0.04864   0.04035  -0.0098   1.0000   0.1293
  -5.750  -0.6902   0.04618   0.03749  -0.0077   1.0000   0.1291
  -5.500  -0.6779   0.04394   0.03484  -0.0057   1.0000   0.1293
  -5.250  -0.6630   0.04184   0.03237  -0.0040   1.0000   0.1291
  -5.000  -0.6459   0.03985   0.02999  -0.0024   1.0000   0.1289
  -4.750  -0.6280   0.03823   0.02800  -0.0008   1.0000   0.1297
  -4.500  -0.6093   0.03664   0.02624   0.0003   1.0000   0.1329
  -4.250  -0.5895   0.03537   0.02490   0.0013   1.0000   0.1370
  -4.000  -0.5683   0.03429   0.02367   0.0024   1.0000   0.1404
  -3.750  -0.5467   0.03345   0.02263   0.0035   1.0000   0.1442
  -3.500  -0.5269   0.03258   0.02188   0.0046   1.0000   0.1515
  -3.250  -0.5082   0.03194   0.02120   0.0059   1.0000   0.1616
  -3.000  -0.4902   0.03133   0.02057   0.0072   1.0000   0.1734
  -2.750  -0.4728   0.03059   0.01997   0.0083   1.0000   0.1918
  -2.500  -0.4493   0.02860   0.01972   0.0080   0.9943   0.3959
  -2.250  -0.0897   0.03751   0.02903  -0.0342   0.9845   1.0000
  -2.000  -0.0700   0.03719   0.02850  -0.0364   0.9753   1.0000
  -1.750  -0.0489   0.03707   0.02817  -0.0386   0.9661   1.0000
  -1.500  -0.0266   0.03709   0.02797  -0.0407   0.9568   1.0000
  -1.250  -0.0152   0.03705   0.02779  -0.0406   0.9472   1.0000
  -1.000   0.0050   0.03725   0.02782  -0.0418   0.9377   1.0000
  -0.750   0.0232   0.03747   0.02786  -0.0424   0.9276   1.0000
  -0.500   0.0321   0.03765   0.02792  -0.0413   0.9172   1.0000
  -0.250   0.0513   0.03803   0.02815  -0.0417   0.9069   1.0000
   0.000   0.0739   0.03847   0.02846  -0.0425   0.8960   1.0000
   0.250   0.0776   0.03877   0.02866  -0.0400   0.8848   1.0000
   0.500   0.0918   0.03926   0.02902  -0.0391   0.8737   1.0000
   0.750   0.1168   0.03989   0.02952  -0.0399   0.8623   1.0000
   1.000   0.1380   0.04048   0.03000  -0.0399   0.8504   1.0000
   1.250   0.1452   0.04105   0.03048  -0.0377   0.8383   1.0000
   1.500   0.1607   0.04175   0.03107  -0.0367   0.8262   1.0000
   1.750   0.1831   0.04251   0.03174  -0.0367   0.8140   1.0000
   2.000   0.2130   0.04329   0.03244  -0.0378   0.8017   1.0000
   2.250   0.2322   0.04407   0.03315  -0.0372   0.7892   1.0000
   2.500   0.2438   0.04489   0.03391  -0.0356   0.7759   1.0000
   2.750   0.2574   0.04581   0.03477  -0.0342   0.7632   1.0000
   3.000   0.2755   0.04673   0.03565  -0.0335   0.7505   1.0000
   3.250   0.2985   0.04765   0.03654  -0.0334   0.7383   1.0000
   3.500   0.3345   0.04842   0.03730  -0.0348   0.7270   1.0000
   3.750   0.3369   0.04961   0.03845  -0.0323   0.7142   1.0000
   4.000   0.3453   0.05082   0.03964  -0.0305   0.7018   1.0000
   4.250   0.3599   0.05203   0.04085  -0.0295   0.6905   1.0000
   4.500   0.3906   0.05294   0.04177  -0.0302   0.6801   1.0000
   4.750   0.3974   0.05436   0.04318  -0.0286   0.6689   1.0000
   5.000   0.4004   0.05602   0.04484  -0.0268   0.6586   1.0000
   5.250   0.4257   0.05715   0.04602  -0.0270   0.6491   1.0000
   5.500   0.4315   0.05884   0.04771  -0.0256   0.6395   1.0000
   5.750   0.4371   0.06067   0.04955  -0.0244   0.6309   1.0000
   6.000   0.4658   0.06180   0.05074  -0.0248   0.6221   1.0000
   6.250   0.4546   0.06435   0.05329  -0.0228   0.6151   1.0000
   6.500   0.4826   0.06565   0.05467  -0.0233   0.6072   1.0000
   6.750   0.4727   0.06831   0.05734  -0.0216   0.6014   1.0000
   7.000   0.4778   0.07056   0.05964  -0.0210   0.5961   1.0000
   7.250   0.4983   0.07242   0.06156  -0.0212   0.5896   1.0000
   7.500   0.4905   0.07531   0.06448  -0.0203   0.5874   1.0000
   7.750   0.4899   0.07821   0.06742  -0.0200   0.5872   1.0000
   8.000   0.4962   0.08123   0.07054  -0.0203   0.5894   1.0000
   8.250   0.4268   0.08958   0.07884  -0.0218   0.6808   1.0000
   8.500   0.4227   0.09069   0.07999  -0.0202   0.6726   1.0000
   8.750   0.4543   0.09444   0.08384  -0.0225   0.6662   1.0000
   9.000   0.4458   0.09520   0.08465  -0.0205   0.6569   1.0000
   9.250   0.4756   0.09901   0.08860  -0.0225   0.6510   1.0000
   9.500   0.4667   0.09983   0.08946  -0.0207   0.6424   1.0000
   9.750   0.4980   0.10390   0.09366  -0.0228   0.6361   1.0000
  10.000   0.4900   0.10463   0.09444  -0.0211   0.6260   1.0000
  10.250   0.5169   0.10865   0.09862  -0.0229   0.6209   1.0000
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