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NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NLR-7223-43 AIRFOIL (nl722343-il)
Reynolds number: 100,000
Max Cl/Cd: 41.39 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nl722343-il-100000-n5.txt
Download as CSV file: xf-nl722343-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7223-43 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5133   0.09195   0.08686  -0.0337   1.0000   0.0563
  -8.750  -0.5294   0.08772   0.08267  -0.0375   1.0000   0.0565
  -8.500  -0.5483   0.08445   0.07937  -0.0391   1.0000   0.0567
  -8.250  -0.5593   0.08120   0.07603  -0.0396   1.0000   0.0569
  -7.750  -0.5423   0.07265   0.06773  -0.0367   1.0000   0.0597
  -7.250  -0.5514   0.06111   0.05580  -0.0370   1.0000   0.0345
  -7.000  -0.5587   0.05478   0.04892  -0.0358   1.0000   0.0284
  -6.750  -0.5521   0.05189   0.04602  -0.0344   1.0000   0.0278
  -6.500  -0.5465   0.04870   0.04270  -0.0329   1.0000   0.0273
  -6.250  -0.5391   0.04553   0.03931  -0.0314   1.0000   0.0266
  -6.000  -0.5296   0.04229   0.03579  -0.0298   1.0000   0.0260
  -5.750  -0.5177   0.03913   0.03227  -0.0283   1.0000   0.0254
  -5.500  -0.5034   0.03601   0.02874  -0.0267   1.0000   0.0248
  -5.250  -0.4868   0.03317   0.02548  -0.0253   1.0000   0.0246
  -5.000  -0.4682   0.03070   0.02261  -0.0239   1.0000   0.0245
  -4.750  -0.4482   0.02860   0.02014  -0.0226   1.0000   0.0247
  -4.500  -0.4274   0.02700   0.01824  -0.0215   1.0000   0.0260
  -4.250  -0.4052   0.02546   0.01632  -0.0203   1.0000   0.0275
  -4.000  -0.3824   0.02396   0.01452  -0.0191   1.0000   0.0281
  -3.750  -0.3595   0.02261   0.01298  -0.0180   1.0000   0.0286
  -3.500  -0.3371   0.02130   0.01164  -0.0170   1.0000   0.0294
  -3.250  -0.3148   0.02031   0.01062  -0.0161   1.0000   0.0306
  -3.000  -0.2926   0.01949   0.00978  -0.0151   1.0000   0.0324
  -2.750  -0.2704   0.01887   0.00907  -0.0141   1.0000   0.0355
  -2.500  -0.2486   0.01811   0.00835  -0.0132   1.0000   0.0390
  -2.250  -0.2173   0.01754   0.00768  -0.0141   0.9969   0.0438
  -2.000  -0.1858   0.01704   0.00716  -0.0150   0.9936   0.0554
  -1.750  -0.1556   0.01616   0.00664  -0.0159   0.9900   0.1180
  -1.500  -0.1410   0.01470   0.00759  -0.0131   0.9860   0.7318
  -1.250  -0.1265   0.01485   0.00792  -0.0084   0.9800   0.8047
  -1.000  -0.1095   0.01483   0.00799  -0.0044   0.9744   0.8542
  -0.750  -0.0804   0.01480   0.00783  -0.0046   0.9686   0.8660
  -0.500  -0.0440   0.01484   0.00770  -0.0066   0.9629   0.8679
  -0.250  -0.0076   0.01485   0.00759  -0.0086   0.9564   0.8694
   0.000   0.0312   0.01484   0.00748  -0.0109   0.9487   0.8708
   0.250   0.0718   0.01474   0.00730  -0.0135   0.9375   0.8721
   0.500   0.1303   0.01435   0.00682  -0.0189   0.9185   0.8715
   0.750   0.1808   0.01390   0.00631  -0.0225   0.8970   0.8714
   1.000   0.2186   0.01367   0.00605  -0.0240   0.8816   0.8726
   1.250   0.2526   0.01349   0.00588  -0.0249   0.8668   0.8745
   1.500   0.2836   0.01333   0.00574  -0.0252   0.8490   0.8768
   1.750   0.3153   0.01317   0.00560  -0.0256   0.8279   0.8788
   2.000   0.3463   0.01301   0.00544  -0.0257   0.8002   0.8809
   2.250   0.3777   0.01286   0.00530  -0.0259   0.7605   0.8830
   2.500   0.4138   0.01273   0.00497  -0.0266   0.6751   0.8846
   2.750   0.4456   0.01310   0.00471  -0.0265   0.5509   0.8867
   3.000   0.4677   0.01374   0.00485  -0.0253   0.4500   0.8905
   3.250   0.4901   0.01434   0.00511  -0.0245   0.3743   0.8954
   3.500   0.5142   0.01489   0.00539  -0.0240   0.3212   0.9009
   3.750   0.5398   0.01537   0.00571  -0.0238   0.2860   0.9073
   4.000   0.5666   0.01581   0.00606  -0.0238   0.2631   0.9147
   4.250   0.5949   0.01626   0.00649  -0.0242   0.2466   0.9243
   4.500   0.6251   0.01671   0.00694  -0.0250   0.2328   0.9373
   4.750   0.6568   0.01719   0.00742  -0.0261   0.2211   0.9604
   5.000   0.6846   0.01770   0.00792  -0.0265   0.2112   1.0000
   5.250   0.7102   0.01818   0.00843  -0.0264   0.2019   1.0000
   5.500   0.7355   0.01872   0.00898  -0.0263   0.1937   1.0000
   5.750   0.7609   0.01926   0.00954  -0.0261   0.1855   1.0000
   6.000   0.7863   0.01981   0.01019  -0.0260   0.1770   1.0000
   6.250   0.8110   0.02040   0.01078  -0.0257   0.1686   1.0000
   6.500   0.8361   0.02092   0.01146  -0.0254   0.1590   1.0000
   6.750   0.8601   0.02144   0.01209  -0.0251   0.1484   1.0000
   7.000   0.8832   0.02182   0.01256  -0.0246   0.1345   1.0000
   7.250   0.9065   0.02212   0.01300  -0.0241   0.1185   1.0000
   7.500   0.9302   0.02248   0.01350  -0.0237   0.1008   1.0000
   7.750   0.9531   0.02303   0.01407  -0.0231   0.0819   1.0000
   8.000   0.9734   0.02404   0.01497  -0.0223   0.0658   1.0000
   8.250   0.9922   0.02534   0.01625  -0.0213   0.0540   1.0000
   8.500   1.0106   0.02666   0.01772  -0.0202   0.0468   1.0000
   8.750   1.0276   0.02811   0.01929  -0.0188   0.0422   1.0000
   9.000   1.0444   0.02947   0.02077  -0.0176   0.0383   1.0000
   9.250   1.0591   0.03103   0.02244  -0.0161   0.0356   1.0000
   9.500   1.0741   0.03266   0.02432  -0.0146   0.0337   1.0000
   9.750   1.0878   0.03438   0.02625  -0.0131   0.0322   1.0000
  10.000   1.0999   0.03611   0.02812  -0.0115   0.0308   1.0000
  10.250   1.1100   0.03797   0.03005  -0.0098   0.0296   1.0000
  10.500   1.1186   0.04012   0.03249  -0.0080   0.0285   1.0000
  10.750   1.1243   0.04233   0.03503  -0.0059   0.0274   1.0000
  11.000   1.1255   0.04463   0.03760  -0.0035   0.0266   1.0000
  11.250   1.1238   0.04715   0.04038  -0.0010   0.0261   1.0000
  11.500   1.1188   0.04990   0.04340   0.0012   0.0257   1.0000
  11.750   1.1107   0.05294   0.04668   0.0029   0.0254   1.0000
  12.000   1.0994   0.05647   0.05045   0.0039   0.0252   1.0000
  12.250   1.0846   0.06061   0.05484   0.0040   0.0251   1.0000
  12.500   1.0659   0.06576   0.06024   0.0025   0.0252   1.0000
  12.750   1.0419   0.07260   0.06733  -0.0012   0.0253   1.0000
  13.000   1.0101   0.08264   0.07761  -0.0086   0.0257   1.0000
  13.250   0.9582   0.10004   0.09522  -0.0215   0.0267   1.0000
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