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WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)
Reynolds number: 50,000
Max Cl/Cd: 16.01 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w153-il-50000-n5.txt
Download as CSV file: xf-fx77w153-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-W-153 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3304   0.12369   0.11725  -0.0035   0.6996   0.1224
  -9.750  -0.3403   0.12139   0.11490  -0.0071   0.6861   0.1265
  -9.500  -0.3499   0.11864   0.11211  -0.0109   0.6750   0.1273
  -9.250  -0.3318   0.11435   0.10768  -0.0091   0.6580   0.1290
  -9.000  -0.3195   0.11095   0.10419  -0.0088   0.6444   0.1311
  -8.500  -0.3389   0.09373   0.08683  -0.0259   0.6389   0.0666
  -8.250  -0.3270   0.09101   0.08406  -0.0250   0.6278   0.0656
  -8.000  -0.3220   0.08722   0.08022  -0.0269   0.6199   0.0641
  -7.750  -0.3234   0.08284   0.07581  -0.0298   0.6137   0.0624
  -7.250  -0.3401   0.07056   0.06309  -0.0380   0.6066   0.0572
  -7.000  -0.3335   0.06698   0.05939  -0.0388   0.6000   0.0567
  -6.750  -0.3271   0.06331   0.05550  -0.0394   0.5947   0.0561
  -6.500  -0.3196   0.05964   0.05154  -0.0397   0.5900   0.0556
  -6.250  -0.3097   0.05605   0.04768  -0.0399   0.5846   0.0552
  -6.000  -0.2981   0.05267   0.04393  -0.0396   0.5798   0.0550
  -5.750  -0.2845   0.04952   0.04033  -0.0390   0.5757   0.0549
  -5.500  -0.2683   0.04659   0.03697  -0.0384   0.5710   0.0552
  -5.250  -0.2505   0.04390   0.03376  -0.0377   0.5664   0.0564
  -5.000  -0.2308   0.04158   0.03093  -0.0368   0.5623   0.0582
  -4.750  -0.2084   0.04018   0.02941  -0.0363   0.5586   0.0606
  -4.500  -0.1849   0.03852   0.02742  -0.0359   0.5543   0.0630
  -4.250  -0.1602   0.03684   0.02525  -0.0352   0.5501   0.0660
  -4.000  -0.1355   0.03565   0.02396  -0.0349   0.5461   0.0699
  -3.750  -0.1094   0.03455   0.02250  -0.0343   0.5426   0.0752
  -3.500  -0.0824   0.03350   0.02133  -0.0342   0.5388   0.0801
  -3.250  -0.0538   0.03255   0.02024  -0.0341   0.5346   0.0846
  -3.000  -0.0252   0.03175   0.01933  -0.0341   0.5311   0.0910
  -2.750   0.0040   0.03110   0.01854  -0.0341   0.5283   0.0971
  -2.500   0.0335   0.03048   0.01778  -0.0341   0.5258   0.1033
  -2.000   0.0882   0.02978   0.01705  -0.0343   0.5201   0.1290
  -1.750   0.1130   0.02936   0.01679  -0.0341   0.5170   0.1552
  -1.500   0.1352   0.02849   0.01655  -0.0336   0.5141   0.2508
  -1.250   0.2758   0.02668   0.01669  -0.0512   0.5089   1.0000
  -1.000   0.2983   0.02712   0.01689  -0.0510   0.5057   1.0000
  -0.750   0.3206   0.02763   0.01721  -0.0508   0.5022   1.0000
  -0.500   0.3428   0.02811   0.01748  -0.0504   0.4990   1.0000
  -0.250   0.3649   0.02854   0.01770  -0.0498   0.4962   1.0000
   0.000   0.3873   0.02896   0.01788  -0.0491   0.4937   1.0000
   0.250   0.4098   0.02936   0.01804  -0.0483   0.4916   1.0000
   0.500   0.4300   0.03029   0.01896  -0.0482   0.4878   1.0000
   0.750   0.4503   0.03111   0.01969  -0.0478   0.4843   1.0000
   1.000   0.4710   0.03184   0.02031  -0.0472   0.4815   1.0000
   1.250   0.4920   0.03253   0.02088  -0.0465   0.4792   1.0000
   1.500   0.5134   0.03317   0.02138  -0.0458   0.4771   1.0000
   1.750   0.5353   0.03376   0.02182  -0.0450   0.4752   1.0000
   2.000   0.5490   0.03538   0.02352  -0.0446   0.4711   1.0000
   2.250   0.5641   0.03671   0.02486  -0.0439   0.4670   1.0000
   2.500   0.5819   0.03768   0.02576  -0.0431   0.4638   1.0000
   2.750   0.6019   0.03843   0.02641  -0.0422   0.4612   1.0000
   3.000   0.6241   0.03897   0.02683  -0.0413   0.4591   1.0000
   3.250   0.6258   0.04151   0.02950  -0.0403   0.4531   1.0000
   3.500   0.6365   0.04301   0.03099  -0.0392   0.4482   1.0000
   3.750   0.6564   0.04365   0.03155  -0.0381   0.4450   1.0000
   4.000   0.6804   0.04398   0.03177  -0.0372   0.4427   1.0000
   4.500   0.6701   0.05000   0.03796  -0.0348   0.4306   1.0000
   4.750   0.6903   0.05070   0.03859  -0.0338   0.4279   1.0000
   5.000   0.7071   0.05175   0.03959  -0.0328   0.4249   1.0000
   5.500   0.6863   0.05885   0.04678  -0.0312   0.4116   1.0000
   5.750   0.7098   0.05937   0.04726  -0.0303   0.4098   1.0000
   6.250   0.6708   0.06824   0.05617  -0.0297   0.3953   1.0000
   6.500   0.6575   0.07218   0.06011  -0.0296   0.3882   1.0000
   6.750   0.6598   0.07473   0.06266  -0.0293   0.3826   1.0000
   7.000   0.6788   0.07578   0.06370  -0.0287   0.3795   1.0000
   7.250   0.7007   0.07658   0.06447  -0.0280   0.3770   1.0000
   7.500   0.6741   0.08185   0.06980  -0.0287   0.3674   1.0000
   7.750   0.6916   0.08310   0.07103  -0.0282   0.3642   1.0000
   8.000   0.7156   0.08373   0.07165  -0.0274   0.3620   1.0000
   8.250   0.6890   0.08922   0.07719  -0.0284   0.3530   1.0000
   8.500   0.7021   0.09098   0.07896  -0.0282   0.3496   1.0000
   8.750   0.7204   0.09230   0.08031  -0.0277   0.3473   1.0000
   9.000   0.7082   0.09676   0.08482  -0.0286   0.3419   1.0000
   9.250   0.7067   0.10012   0.08822  -0.0290   0.3374   1.0000
   9.500   0.7188   0.10207   0.09019  -0.0289   0.3340   1.0000
   9.750   0.7386   0.10325   0.09140  -0.0285   0.3316   1.0000
  10.000   0.7253   0.10768   0.09587  -0.0294   0.3253   1.0000
  10.250   0.7290   0.11056   0.09880  -0.0298   0.3215   1.0000
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