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NACA 4424 (naca4424-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 4424 (naca4424-il)
Reynolds number: 100,000
Max Cl/Cd: 30.84 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca4424-il-100000.txt
Download as CSV file: xf-naca4424-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 4424                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.8389   0.06440   0.05774  -0.0701   0.9748   0.1761
 -11.500  -0.9128   0.05996   0.05287  -0.0631   0.9644   0.1766
 -11.250  -0.9638   0.05666   0.04912  -0.0554   0.9529   0.1776
 -11.000  -0.8570   0.05838   0.05137  -0.0655   0.9508   0.1830
 -10.750  -0.8728   0.05674   0.04959  -0.0609   0.9397   0.1851
 -10.500  -0.8907   0.05448   0.04705  -0.0565   0.9303   0.1878
 -10.250  -0.9128   0.05194   0.04405  -0.0512   0.9208   0.1906
 -10.000  -0.8997   0.05082   0.04291  -0.0498   0.9124   0.1937
  -9.750  -0.8692   0.05054   0.04273  -0.0505   0.9047   0.1974
  -9.500  -0.8425   0.04938   0.04141  -0.0514   0.8996   0.2025
  -9.250  -0.8646   0.04810   0.03984  -0.0442   0.8871   0.2051
  -9.000  -0.8318   0.04710   0.03884  -0.0456   0.8814   0.2095
  -8.750  -0.8123   0.04676   0.03854  -0.0445   0.8731   0.2134
  -8.500  -0.8026   0.04601   0.03767  -0.0420   0.8639   0.2177
  -8.250  -0.7830   0.04459   0.03590  -0.0412   0.8587   0.2234
  -8.000  -0.7735   0.04438   0.03582  -0.0384   0.8480   0.2265
  -7.750  -0.7464   0.04395   0.03541  -0.0383   0.8409   0.2319
  -7.500  -0.7199   0.04286   0.03397  -0.0382   0.8364   0.2388
  -7.250  -0.7252   0.04263   0.03378  -0.0332   0.8244   0.2417
  -7.000  -0.6897   0.04224   0.03351  -0.0344   0.8186   0.2474
  -6.750  -0.6558   0.04142   0.03247  -0.0352   0.8148   0.2554
  -6.500  -0.6699   0.04132   0.03224  -0.0286   0.8015   0.2585
  -6.250  -0.6293   0.04083   0.03194  -0.0306   0.7967   0.2650
  -6.000  -0.5934   0.04013   0.03109  -0.0315   0.7934   0.2737
  -5.750  -0.6126   0.04042   0.03118  -0.0242   0.7796   0.2768
  -5.500  -0.5707   0.03974   0.03072  -0.0263   0.7752   0.2841
  -5.250  -0.5324   0.03906   0.02992  -0.0275   0.7722   0.2937
  -5.000  -0.5545   0.03970   0.03040  -0.0199   0.7583   0.2968
  -4.750  -0.5158   0.03903   0.02991  -0.0215   0.7540   0.3046
  -4.500  -0.4759   0.03833   0.02912  -0.0227   0.7511   0.3149
  -4.250  -0.4985   0.03921   0.02985  -0.0153   0.7372   0.3184
  -4.000  -0.4628   0.03862   0.02944  -0.0163   0.7328   0.3268
  -3.750  -0.4247   0.03798   0.02872  -0.0172   0.7299   0.3380
  -3.500  -0.4465   0.03905   0.02966  -0.0102   0.7168   0.3416
  -3.250  -0.4130   0.03854   0.02934  -0.0108   0.7118   0.3510
  -3.000  -0.3773   0.03795   0.02862  -0.0112   0.7087   0.3632
  -2.750  -0.3895   0.03892   0.02962  -0.0059   0.6975   0.3679
  -2.500  -0.3673   0.03883   0.02963  -0.0049   0.6910   0.3774
  -2.250  -0.3339   0.03828   0.02898  -0.0050   0.6875   0.3904
  -2.000  -0.2881   0.03739   0.02823  -0.0070   0.6855   0.4045
  -1.750  -0.3259   0.03953   0.03034   0.0014   0.6708   0.4071
  -1.500  -0.2942   0.03908   0.02994   0.0013   0.6667   0.4204
  -1.250  -0.2544   0.03837   0.02920   0.0004   0.6641   0.4371
  -1.000  -0.2828   0.04034   0.03123   0.0071   0.6510   0.4412
  -0.750  -0.2576   0.04025   0.03125   0.0078   0.6460   0.4557
  -0.500  -0.2206   0.03965   0.03074   0.0072   0.6431   0.4734
  -0.250  -0.1761   0.03872   0.02989   0.0059   0.6411   0.4948
   0.000  -0.1297   0.03768   0.02895   0.0044   0.6398   0.5189
   0.250  -0.1905   0.04134   0.03265   0.0142   0.6222   0.5191
   0.500  -0.1502   0.04060   0.03204   0.0135   0.6199   0.5454
   0.750  -0.1035   0.03952   0.03113   0.0122   0.6185   0.5765
   1.000  -0.1607   0.04333   0.03500   0.0208   0.6018   0.5800
   1.250  -0.1246   0.04280   0.03462   0.0206   0.5990   0.6169
   1.500  -0.0746   0.04171   0.03381   0.0189   0.5973   0.6628
   1.750  -0.0152   0.04050   0.03290   0.0156   0.5962   0.7224
   2.250   0.2251   0.03713   0.03007  -0.0115   0.5960   0.8689
   2.500   0.3643   0.03547   0.02834  -0.0278   0.5964   0.9003
   2.750   0.4958   0.03381   0.02650  -0.0425   0.5961   0.9155
   3.000   0.4305   0.03967   0.03260  -0.0337   0.5771   0.9409
   3.250   0.5478   0.03746   0.03022  -0.0455   0.5772   0.9531
   3.500   0.6744   0.03527   0.02783  -0.0596   0.5765   0.9624
   3.750   0.6184   0.04105   0.03386  -0.0531   0.5591   0.9874
   4.000   0.7511   0.03779   0.03041  -0.0673   0.5592   0.9929
   4.250   0.8913   0.03512   0.02750  -0.0843   0.5567   0.9956
   4.500   1.0338   0.03352   0.02560  -0.1035   0.5526   0.9966
   4.750   0.5770   0.04711   0.03971  -0.0388   0.5287   1.0000
   5.000   0.6462   0.04404   0.03651  -0.0419   0.5292   1.0000
   5.250   0.7373   0.04061   0.03293  -0.0483   0.5296   1.0000
   5.500   0.5761   0.05084   0.04326  -0.0296   0.5088   1.0000
   5.750   0.6405   0.04775   0.04005  -0.0317   0.5092   1.0000
   6.000   0.7175   0.04440   0.03658  -0.0355   0.5095   1.0000
   6.500   0.4011   0.07291   0.06536  -0.0128   0.4561   1.0000
   6.750   0.4286   0.07270   0.06510  -0.0121   0.4522   1.0000
   7.000   0.4672   0.07150   0.06383  -0.0117   0.4500   1.0000
   7.250   0.4140   0.07865   0.07103  -0.0090   0.4361   1.0000
   7.500   0.4408   0.07856   0.07089  -0.0083   0.4321   1.0000
   7.750   0.4808   0.07720   0.06947  -0.0078   0.4299   1.0000
   8.000   0.4297   0.08453   0.07685  -0.0058   0.4162   1.0000
   8.250   0.4568   0.08445   0.07673  -0.0051   0.4125   1.0000
   8.500   0.4990   0.08278   0.07500  -0.0046   0.4102   1.0000
   8.750   0.5435   0.08084   0.07301  -0.0041   0.4088   1.0000
   9.000   0.4756   0.09036   0.08261  -0.0026   0.3931   1.0000
   9.250   0.5152   0.08899   0.08118  -0.0020   0.3910   1.0000
   9.500   0.5602   0.08690   0.07904  -0.0014   0.3896   1.0000
   9.750   0.4922   0.09688   0.08911  -0.0007   0.3742   1.0000
  10.000   0.5337   0.09518   0.08736   0.0001   0.3722   1.0000
  10.250   0.4743   0.10465   0.09692   0.0001   0.3593   1.0000
  10.500   0.5074   0.10384   0.09608   0.0008   0.3558   1.0000
  10.750   0.4893   0.10898   0.10124   0.0008   0.3479   1.0000
  11.000   0.4864   0.11232   0.10460   0.0009   0.3414   1.0000
  11.250   0.5178   0.11172   0.10398   0.0016   0.3380   1.0000
  11.500   0.5651   0.10908   0.10128   0.0027   0.3359   1.0000
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