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CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: CLARK Z AIRFOIL (clarkz-il)
Reynolds number: 50,000
Max Cl/Cd: 30.41 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkz-il-50000.txt
Download as CSV file: xf-clarkz-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK Z 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3063   0.11202   0.10479  -0.0302   1.0000   0.2150
  -8.750  -0.3119   0.11053   0.10339  -0.0298   1.0000   0.2227
  -8.500  -0.3498   0.11223   0.10532  -0.0296   1.0000   0.2256
  -8.250  -0.3078   0.10506   0.09808  -0.0277   1.0000   0.2341
  -8.000  -0.3285   0.10483   0.09802  -0.0263   1.0000   0.2414
  -7.750  -0.3312   0.10207   0.09537  -0.0246   1.0000   0.2460
  -7.500  -0.3253   0.09951   0.09286  -0.0224   1.0000   0.2549
  -7.250  -0.3656   0.10058   0.09415  -0.0187   1.0000   0.2594
  -7.000  -0.3461   0.09623   0.08982  -0.0170   1.0000   0.2673
  -6.750  -0.3695   0.09584   0.08957  -0.0132   1.0000   0.2745
  -6.500  -0.4220   0.09723   0.09118  -0.0120   1.0000   0.2779
  -6.250  -0.3889   0.09231   0.08624  -0.0074   1.0000   0.2898
  -6.000  -0.4182   0.09142   0.08551  -0.0061   1.0000   0.2970
  -5.750  -0.4172   0.08934   0.08348  -0.0029   1.0000   0.3102
  -5.500  -0.4157   0.08680   0.08101   0.0003   1.0000   0.3219
  -5.250  -0.4253   0.08490   0.07920   0.0026   1.0000   0.3357
  -5.000  -0.4317   0.08297   0.07735   0.0051   1.0000   0.3524
  -4.750  -0.4338   0.08097   0.07542   0.0082   1.0000   0.3714
  -4.500  -0.4363   0.07909   0.07361   0.0114   1.0000   0.3933
  -4.250  -0.4437   0.07723   0.07183   0.0143   1.0000   0.4200
  -4.000  -0.4406   0.07528   0.06994   0.0190   1.0000   0.4467
  -3.750  -0.4405   0.07338   0.06811   0.0241   1.0000   0.4800
  -3.250  -0.1659   0.06097   0.05533   0.0209   1.0000   0.8612
  -3.000  -0.1570   0.05919   0.05359   0.0211   1.0000   0.8853
  -2.750  -0.1932   0.05895   0.05350   0.0275   1.0000   0.8605
  -2.500  -0.2531   0.04665   0.03845  -0.0384   1.0000   0.1892
  -2.250  -0.2288   0.04430   0.03587  -0.0395   1.0000   0.1815
  -2.000  -0.1992   0.04235   0.03325  -0.0410   1.0000   0.1711
  -1.750  -0.1750   0.04083   0.03147  -0.0417   1.0000   0.1678
  -1.500  -0.1272   0.03950   0.02966  -0.0462   0.9935   0.1665
  -1.250  -0.0705   0.03868   0.02831  -0.0520   0.9825   0.1714
  -1.000  -0.0198   0.03783   0.02713  -0.0566   0.9709   0.1761
  -0.750   0.0249   0.03731   0.02649  -0.0602   0.9586   0.1860
  -0.500   0.0675   0.03692   0.02601  -0.0631   0.9461   0.2027
  -0.250   0.1123   0.03651   0.02560  -0.0662   0.9339   0.2309
   0.000   0.1650   0.03534   0.02508  -0.0706   0.9234   0.3358
   0.250   0.1976   0.03324   0.02461  -0.0696   0.9110   1.0000
   0.500   0.2329   0.03404   0.02499  -0.0715   0.8961   1.0000
   0.750   0.2672   0.03482   0.02548  -0.0732   0.8813   1.0000
   1.000   0.3008   0.03560   0.02603  -0.0748   0.8665   1.0000
   1.250   0.3344   0.03636   0.02659  -0.0763   0.8518   1.0000
   1.500   0.3682   0.03711   0.02718  -0.0778   0.8375   1.0000
   1.750   0.4043   0.03778   0.02770  -0.0794   0.8235   1.0000
   2.000   0.4461   0.03830   0.02810  -0.0816   0.8106   1.0000
   2.250   0.4714   0.03905   0.02877  -0.0816   0.7954   1.0000
   2.500   0.4960   0.03986   0.02952  -0.0815   0.7806   1.0000
   2.750   0.5203   0.04071   0.03031  -0.0814   0.7660   1.0000
   3.000   0.5459   0.04153   0.03108  -0.0813   0.7518   1.0000
   3.250   0.5740   0.04228   0.03180  -0.0815   0.7386   1.0000
   3.750   0.6371   0.04336   0.03284  -0.0823   0.7134   1.0000
   4.000   0.6532   0.04461   0.03409  -0.0812   0.6992   1.0000
   4.250   0.6710   0.04581   0.03529  -0.0803   0.6856   1.0000
   4.500   0.6972   0.04662   0.03612  -0.0801   0.6737   1.0000
   4.750   0.7374   0.04648   0.03601  -0.0806   0.6633   1.0000
   5.000   0.7439   0.04845   0.03800  -0.0790   0.6491   1.0000
   5.250   0.7542   0.05026   0.03983  -0.0777   0.6357   1.0000
   5.500   0.7759   0.05133   0.04093  -0.0770   0.6241   1.0000
   5.750   0.8175   0.05081   0.04050  -0.0771   0.6142   1.0000
   6.000   0.8170   0.05353   0.04325  -0.0754   0.6000   1.0000
   6.250   0.8209   0.05600   0.04575  -0.0740   0.5868   1.0000
   6.500   0.9000   0.05192   0.04183  -0.0745   0.5800   1.0000
   6.750   0.8911   0.05544   0.04539  -0.0726   0.5650   1.0000
   7.000   0.8854   0.05882   0.04881  -0.0710   0.5504   1.0000
   7.250   0.8855   0.06171   0.05175  -0.0697   0.5365   1.0000
   7.500   0.8966   0.06349   0.05360  -0.0683   0.5227   1.0000
   7.750   0.9235   0.06346   0.05368  -0.0667   0.5085   1.0000
   8.000   1.0490   0.05180   0.04226  -0.0646   0.4932   1.0000
   8.250   1.1180   0.04712   0.03767  -0.0640   0.4742   1.0000
   8.500   1.1745   0.04413   0.03472  -0.0638   0.4546   1.0000
   8.750   1.2293   0.04167   0.03215  -0.0640   0.4327   1.0000
   9.000   1.2390   0.04265   0.03326  -0.0611   0.4119   1.0000
   9.250   1.2726   0.04193   0.03243  -0.0600   0.3874   1.0000
   9.500   1.2885   0.04263   0.03312  -0.0576   0.3642   1.0000
   9.750   1.3054   0.04343   0.03390  -0.0554   0.3417   1.0000
  10.000   1.3337   0.04386   0.03411  -0.0545   0.3199   1.0000
  10.250   1.3438   0.04545   0.03575  -0.0521   0.3031   1.0000
  10.500   1.3604   0.04694   0.03722  -0.0505   0.2882   1.0000
  10.750   1.3589   0.04945   0.03997  -0.0474   0.2776   1.0000
  11.000   1.3615   0.05197   0.04267  -0.0449   0.2684   1.0000
  11.250   1.3894   0.05318   0.04379  -0.0446   0.2575   1.0000
  11.500   1.3602   0.05725   0.04827  -0.0398   0.2534   1.0000
  11.750   1.3425   0.06081   0.05205  -0.0363   0.2488   1.0000
  12.000   1.3662   0.06270   0.05394  -0.0359   0.2418   1.0000
  12.250   1.3156   0.06877   0.06029  -0.0318   0.2414   1.0000
  12.500   1.2443   0.07846   0.07018  -0.0306   0.2422   1.0000
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