Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD5060 (9.5%) (sd5060-il)
Reynolds number: 50,000
Max Cl/Cd: 33.57 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd5060-il-50000.txt
Download as CSV file: xf-sd5060-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD5060 (9.5%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4324   0.09984   0.09313  -0.0052   1.0000   0.2650
  -8.000  -0.4201   0.09565   0.08896  -0.0050   1.0000   0.2728
  -7.500  -0.4262   0.09081   0.08431  -0.0062   1.0000   0.2956
  -7.250  -0.4101   0.08666   0.08015  -0.0054   1.0000   0.3075
  -7.000  -0.4078   0.08344   0.07701  -0.0055   1.0000   0.3164
  -6.500  -0.4678   0.05690   0.05015  -0.0436   1.0000   0.1335
  -6.250  -0.4595   0.05242   0.04553  -0.0443   1.0000   0.1318
  -6.000  -0.4519   0.04776   0.04058  -0.0452   1.0000   0.1312
  -5.750  -0.4417   0.04338   0.03580  -0.0456   1.0000   0.1311
  -5.500  -0.4288   0.03925   0.03117  -0.0456   1.0000   0.1316
  -5.250  -0.4129   0.03550   0.02679  -0.0452   1.0000   0.1334
  -5.000  -0.3955   0.03298   0.02410  -0.0442   1.0000   0.1392
  -4.750  -0.3766   0.03067   0.02135  -0.0433   1.0000   0.1507
  -4.500  -0.3568   0.02867   0.01913  -0.0421   1.0000   0.1653
  -4.250  -0.3374   0.02715   0.01753  -0.0408   1.0000   0.1912
  -4.000  -0.3194   0.02604   0.01660  -0.0393   1.0000   0.2285
  -3.750  -0.3013   0.02511   0.01577  -0.0378   1.0000   0.2719
  -3.500  -0.2813   0.02407   0.01469  -0.0365   1.0000   0.3126
  -3.250  -0.2619   0.02323   0.01394  -0.0350   1.0000   0.3501
  -3.000  -0.2417   0.02246   0.01319  -0.0338   1.0000   0.3894
  -2.750  -0.2218   0.02181   0.01258  -0.0325   1.0000   0.4310
  -2.500  -0.2021   0.02121   0.01210  -0.0311   1.0000   0.4757
  -2.250  -0.1817   0.02065   0.01172  -0.0297   1.0000   0.5268
  -2.000  -0.1629   0.02008   0.01138  -0.0278   1.0000   0.5905
  -1.750  -0.1478   0.01945   0.01116  -0.0249   1.0000   0.6751
  -1.500  -0.1413   0.01866   0.01100  -0.0193   1.0000   0.8043
  -1.250  -0.0909   0.01810   0.01008  -0.0255   1.0000   1.0000
  -1.000  -0.0684   0.01839   0.00996  -0.0262   1.0000   1.0000
  -0.750  -0.0474   0.01874   0.01000  -0.0264   1.0000   1.0000
  -0.500  -0.0272   0.01915   0.01015  -0.0264   1.0000   1.0000
  -0.250  -0.0076   0.01960   0.01038  -0.0264   1.0000   1.0000
   0.000   0.0118   0.02011   0.01070  -0.0264   1.0000   1.0000
   0.250   0.0309   0.02067   0.01109  -0.0264   1.0000   1.0000
   0.500   0.0497   0.02128   0.01155  -0.0264   1.0000   1.0000
   0.750   0.1017   0.02251   0.01262  -0.0326   0.9848   1.0000
   1.000   0.1534   0.02369   0.01368  -0.0384   0.9686   1.0000
   1.250   0.1998   0.02470   0.01462  -0.0430   0.9509   1.0000
   1.500   0.2468   0.02568   0.01555  -0.0476   0.9327   1.0000
   1.750   0.2974   0.02661   0.01646  -0.0523   0.9142   1.0000
   2.000   0.3396   0.02738   0.01725  -0.0555   0.8944   1.0000
   2.250   0.3828   0.02805   0.01796  -0.0584   0.8736   1.0000
   2.500   0.4393   0.02849   0.01849  -0.0629   0.8537   1.0000
   2.750   0.4743   0.02895   0.01902  -0.0640   0.8306   1.0000
   3.000   0.5285   0.02891   0.01910  -0.0669   0.8098   1.0000
   3.250   0.5609   0.02909   0.01939  -0.0666   0.7857   1.0000
   3.500   0.6077   0.02855   0.01898  -0.0671   0.7646   1.0000
   3.750   0.6360   0.02850   0.01905  -0.0655   0.7391   1.0000
   4.000   0.6684   0.02809   0.01873  -0.0638   0.7142   1.0000
   4.250   0.7043   0.02718   0.01790  -0.0616   0.6905   1.0000
   4.500   0.7317   0.02669   0.01747  -0.0590   0.6621   1.0000
   4.750   0.7593   0.02613   0.01696  -0.0562   0.6323   1.0000
   5.000   0.7846   0.02577   0.01660  -0.0534   0.5990   1.0000
   5.250   0.8093   0.02554   0.01633  -0.0507   0.5630   1.0000
   5.500   0.8347   0.02540   0.01607  -0.0481   0.5265   1.0000
   5.750   0.8577   0.02571   0.01626  -0.0459   0.4879   1.0000
   6.000   0.8810   0.02624   0.01663  -0.0440   0.4515   1.0000
   6.250   0.9035   0.02707   0.01736  -0.0424   0.4174   1.0000
   6.500   0.9263   0.02805   0.01826  -0.0409   0.3869   1.0000
   6.750   0.9491   0.02926   0.01941  -0.0397   0.3604   1.0000
   7.000   0.9732   0.03044   0.02044  -0.0386   0.3367   1.0000
   7.250   0.9941   0.03205   0.02220  -0.0376   0.3151   1.0000
   7.500   1.0172   0.03351   0.02365  -0.0366   0.2957   1.0000
   7.750   1.0395   0.03521   0.02538  -0.0357   0.2782   1.0000
   8.000   1.0589   0.03720   0.02759  -0.0347   0.2621   1.0000
   8.250   1.0774   0.03924   0.02981  -0.0336   0.2465   1.0000
   8.500   1.0962   0.04152   0.03226  -0.0326   0.2330   1.0000
   8.750   1.1135   0.04376   0.03470  -0.0315   0.2191   1.0000
   9.000   1.1332   0.04617   0.03716  -0.0305   0.2066   1.0000
   9.250   1.1363   0.04956   0.04116  -0.0288   0.1967   1.0000
   9.500   1.1427   0.05297   0.04488  -0.0274   0.1874   1.0000
   9.750   1.1607   0.05574   0.04766  -0.0264   0.1773   1.0000
  10.000   1.1439   0.06090   0.05344  -0.0247   0.1740   1.0000
  10.250   1.1253   0.06608   0.05899  -0.0235   0.1712   1.0000
  10.500   1.1125   0.07066   0.06376  -0.0226   0.1676   1.0000
  10.750   1.0939   0.07569   0.06893  -0.0220   0.1660   1.0000
  11.000   1.0793   0.08096   0.07427  -0.0219   0.1646   1.0000
<< Back to SD5060 (9.5%) (sd5060-il)

Polar data table (+)

Polar graphs


<< Back to SD5060 (9.5%) (sd5060-il)