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WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)
Reynolds number: 500,000
Max Cl/Cd: 101.92 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w153-il-500000-n5.txt
Download as CSV file: xf-fx77w153-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6692   0.04122   0.03656  -0.0355   0.4537   0.0122
  -9.500  -0.6921   0.03321   0.02782  -0.0336   0.4525   0.0122
  -9.250  -0.6855   0.02987   0.02403  -0.0320   0.4477   0.0122
  -8.750  -0.6556   0.02560   0.01910  -0.0295   0.4383   0.0122
  -8.500  -0.6363   0.02409   0.01732  -0.0285   0.4337   0.0123
  -8.250  -0.6153   0.02282   0.01582  -0.0277   0.4294   0.0123
  -8.000  -0.5931   0.02174   0.01453  -0.0269   0.4255   0.0123
  -7.750  -0.5704   0.02070   0.01331  -0.0261   0.4224   0.0123
  -7.500  -0.5471   0.01974   0.01217  -0.0254   0.4193   0.0124
  -7.250  -0.5231   0.01892   0.01120  -0.0247   0.4162   0.0125
  -7.000  -0.4986   0.01820   0.01034  -0.0241   0.4134   0.0126
  -6.750  -0.4734   0.01759   0.00961  -0.0236   0.4107   0.0127
  -6.500  -0.4479   0.01703   0.00896  -0.0231   0.4084   0.0128
  -6.250  -0.4220   0.01653   0.00838  -0.0226   0.4063   0.0130
  -6.000  -0.3958   0.01608   0.00786  -0.0222   0.4040   0.0132
  -5.750  -0.3694   0.01568   0.00738  -0.0218   0.4020   0.0134
  -5.500  -0.3427   0.01531   0.00695  -0.0214   0.4001   0.0136
  -5.250  -0.3160   0.01498   0.00655  -0.0211   0.3984   0.0139
  -5.000  -0.2891   0.01467   0.00618  -0.0208   0.3968   0.0142
  -4.750  -0.2621   0.01439   0.00583  -0.0205   0.3953   0.0145
  -4.500  -0.2350   0.01414   0.00552  -0.0202   0.3939   0.0150
  -4.250  -0.2077   0.01391   0.00526  -0.0199   0.3927   0.0155
  -4.000  -0.1800   0.01373   0.00509  -0.0197   0.3916   0.0164
  -3.750  -0.1522   0.01357   0.00493  -0.0196   0.3904   0.0175
  -3.500  -0.1244   0.01342   0.00476  -0.0194   0.3890   0.0190
  -3.250  -0.0964   0.01330   0.00460  -0.0192   0.3876   0.0215
  -3.000  -0.0684   0.01317   0.00444  -0.0191   0.3862   0.0233
  -2.750  -0.0405   0.01305   0.00429  -0.0190   0.3850   0.0251
  -2.500  -0.0124   0.01297   0.00416  -0.0189   0.3840   0.0265
  -2.250   0.0151   0.01279   0.00396  -0.0187   0.3829   0.0279
  -2.000   0.0429   0.01266   0.00381  -0.0186   0.3817   0.0296
  -1.750   0.0708   0.01258   0.00368  -0.0185   0.3805   0.0312
  -1.500   0.0985   0.01246   0.00355  -0.0183   0.3795   0.0331
  -1.250   0.1264   0.01238   0.00346  -0.0182   0.3786   0.0346
  -1.000   0.1544   0.01234   0.00339  -0.0181   0.3777   0.0359
  -0.750   0.1824   0.01228   0.00333  -0.0181   0.3770   0.0373
  -0.500   0.2105   0.01221   0.00329  -0.0180   0.3764   0.0407
  -0.250   0.2386   0.01215   0.00324  -0.0180   0.3758   0.0465
   0.000   0.2668   0.01209   0.00319  -0.0179   0.3747   0.0534
   0.250   0.2948   0.01200   0.00316  -0.0178   0.3735   0.0649
   0.500   0.3227   0.01191   0.00313  -0.0178   0.3723   0.0921
   0.750   0.3499   0.01175   0.00312  -0.0177   0.3712   0.1403
   1.000   0.3768   0.01154   0.00312  -0.0176   0.3703   0.2160
   1.250   0.4033   0.01131   0.00313  -0.0174   0.3692   0.2979
   1.500   0.4286   0.01097   0.00315  -0.0170   0.3681   0.4210
   1.750   0.4506   0.01041   0.00316  -0.0160   0.3667   0.6061
   2.000   0.4689   0.00960   0.00324  -0.0137   0.3653   0.8615
   2.250   0.5427   0.00987   0.00358  -0.0231   0.3632   0.9569
   2.500   0.5746   0.01006   0.00372  -0.0238   0.3617   0.9713
   2.750   0.6088   0.01019   0.00383  -0.0251   0.3606   0.9806
   3.000   0.6564   0.01030   0.00392  -0.0292   0.3593   0.9875
   3.250   0.7194   0.01041   0.00401  -0.0367   0.3579   0.9973
   3.500   0.7589   0.01048   0.00407  -0.0392   0.3567   1.0000
   3.750   0.7852   0.01057   0.00415  -0.0390   0.3555   1.0000
   4.000   0.8115   0.01066   0.00423  -0.0387   0.3542   1.0000
   4.250   0.8376   0.01075   0.00431  -0.0385   0.3528   1.0000
   4.500   0.8638   0.01085   0.00441  -0.0382   0.3515   1.0000
   4.750   0.8898   0.01097   0.00451  -0.0379   0.3502   1.0000
   5.000   0.9157   0.01110   0.00462  -0.0376   0.3488   1.0000
   5.250   0.9414   0.01125   0.00475  -0.0373   0.3472   1.0000
   5.500   0.9672   0.01140   0.00490  -0.0370   0.3456   1.0000
   5.750   0.9931   0.01148   0.00502  -0.0367   0.3441   1.0000
   6.000   1.0189   0.01158   0.00516  -0.0365   0.3426   1.0000
   6.250   1.0446   0.01170   0.00532  -0.0361   0.3409   1.0000
   6.500   1.0701   0.01181   0.00546  -0.0358   0.3390   1.0000
   6.750   1.0956   0.01192   0.00560  -0.0355   0.3369   1.0000
   7.000   1.1209   0.01205   0.00574  -0.0352   0.3349   1.0000
   7.250   1.1460   0.01218   0.00589  -0.0348   0.3328   1.0000
   7.500   1.1707   0.01234   0.00604  -0.0344   0.3304   1.0000
   7.750   1.1962   0.01241   0.00620  -0.0341   0.3271   1.0000
   8.000   1.2215   0.01250   0.00636  -0.0337   0.3230   1.0000
   8.250   1.2464   0.01259   0.00647  -0.0333   0.3182   1.0000
   8.500   1.2712   0.01268   0.00660  -0.0330   0.3121   1.0000
   9.000   1.3188   0.01294   0.00682  -0.0319   0.2944   1.0000
   9.250   1.3406   0.01323   0.00706  -0.0312   0.2855   1.0000
   9.500   1.3622   0.01356   0.00739  -0.0304   0.2771   1.0000
   9.750   1.3830   0.01393   0.00775  -0.0295   0.2696   1.0000
  10.000   1.4036   0.01430   0.00813  -0.0287   0.2593   1.0000
  10.250   1.4228   0.01475   0.00856  -0.0276   0.2492   1.0000
  10.500   1.4403   0.01526   0.00906  -0.0263   0.2401   1.0000
  10.750   1.4574   0.01579   0.00957  -0.0250   0.2324   1.0000
  11.000   1.4733   0.01635   0.01013  -0.0235   0.2256   1.0000
  11.250   1.4897   0.01686   0.01067  -0.0222   0.2179   1.0000
  11.500   1.5031   0.01751   0.01133  -0.0204   0.2104   1.0000
  11.750   1.5162   0.01817   0.01200  -0.0187   0.1997   1.0000
  12.000   1.5236   0.01908   0.01289  -0.0164   0.1893   1.0000
  12.250   1.5253   0.02012   0.01394  -0.0135   0.1813   1.0000
  12.500   1.5282   0.02136   0.01520  -0.0113   0.1738   1.0000
  12.750   1.5283   0.02310   0.01698  -0.0098   0.1661   1.0000
  13.000   1.5221   0.02591   0.01982  -0.0093   0.1521   1.0000
  13.250   1.5045   0.03079   0.02474  -0.0105   0.1384   1.0000
  13.500   1.4858   0.03609   0.03012  -0.0119   0.1311   1.0000
  13.750   1.4664   0.04131   0.03542  -0.0128   0.1261   1.0000
  14.000   1.4475   0.04630   0.04049  -0.0135   0.1200   1.0000
  14.500   1.4034   0.05677   0.05109  -0.0147   0.1078   1.0000
  14.750   1.3799   0.06222   0.05657  -0.0153   0.1002   1.0000
  15.000   1.3616   0.06732   0.06170  -0.0162   0.0953   1.0000
  15.250   1.3461   0.07221   0.06660  -0.0170   0.0901   1.0000
  15.500   1.3366   0.07639   0.07082  -0.0178   0.0835   1.0000
  15.750   1.3228   0.08122   0.07566  -0.0187   0.0764   1.0000
  16.000   1.3105   0.08589   0.08035  -0.0197   0.0656   1.0000
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