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NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NLR-7223-62 AIRFOIL (nl722362-il)
Reynolds number: 500,000
Max Cl/Cd: 70.75 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nl722362-il-500000-n5.txt
Download as CSV file: xf-nl722362-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7223-62 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5081   0.09133   0.08895  -0.0270   1.0000   0.0072
  -9.750  -0.5069   0.08829   0.08593  -0.0283   1.0000   0.0071
  -9.500  -0.5126   0.08322   0.08090  -0.0309   1.0000   0.0071
  -9.250  -0.5188   0.07838   0.07609  -0.0338   1.0000   0.0071
  -9.000  -0.5222   0.07489   0.07263  -0.0364   1.0000   0.0069
  -8.750  -0.5442   0.06797   0.06571  -0.0415   0.9967   0.0070
  -8.500  -0.5400   0.06234   0.05997  -0.0466   0.9752   0.0068
  -8.250  -0.5382   0.05431   0.05172  -0.0515   0.9600   0.0069
  -8.000  -0.5344   0.04813   0.04528  -0.0530   0.9485   0.0069
  -7.750  -0.5403   0.03976   0.03645  -0.0511   0.9373   0.0072
  -7.500  -0.5411   0.03354   0.02977  -0.0480   0.9298   0.0072
  -7.250  -0.5441   0.02687   0.02242  -0.0436   0.9233   0.0074
  -7.000  -0.5295   0.02496   0.02025  -0.0419   0.9197   0.0076
  -6.750  -0.5090   0.02423   0.01940  -0.0410   0.9171   0.0078
  -6.500  -0.4908   0.02244   0.01733  -0.0395   0.9146   0.0081
  -6.250  -0.4704   0.02113   0.01582  -0.0384   0.9123   0.0085
  -6.000  -0.4513   0.01872   0.01299  -0.0366   0.9099   0.0087
  -5.750  -0.4291   0.01699   0.01096  -0.0354   0.9078   0.0089
  -5.500  -0.4055   0.01573   0.00945  -0.0345   0.9060   0.0093
  -5.250  -0.3811   0.01479   0.00833  -0.0337   0.9044   0.0096
  -5.000  -0.3564   0.01407   0.00747  -0.0331   0.9029   0.0098
  -4.750  -0.3328   0.01325   0.00657  -0.0323   0.9015   0.0101
  -4.500  -0.3084   0.01270   0.00599  -0.0317   0.9001   0.0105
  -4.250  -0.2834   0.01232   0.00559  -0.0311   0.8987   0.0111
  -4.000  -0.2587   0.01194   0.00517  -0.0305   0.8971   0.0118
  -3.750  -0.2342   0.01152   0.00471  -0.0298   0.8957   0.0123
  -3.500  -0.2097   0.01114   0.00429  -0.0292   0.8943   0.0126
  -3.250  -0.1853   0.01074   0.00386  -0.0284   0.8929   0.0131
  -3.000  -0.1602   0.01043   0.00355  -0.0279   0.8916   0.0139
  -2.750  -0.1347   0.01019   0.00329  -0.0274   0.8901   0.0149
  -2.500  -0.1091   0.00998   0.00305  -0.0268   0.8874   0.0162
  -2.250  -0.0836   0.00976   0.00280  -0.0262   0.8842   0.0185
  -2.000  -0.0591   0.00954   0.00261  -0.0254   0.8795   0.0249
  -1.750  -0.0353   0.00924   0.00237  -0.0244   0.8711   0.0476
  -1.500  -0.0134   0.00884   0.00212  -0.0229   0.8571   0.1018
  -1.250   0.0061   0.00816   0.00186  -0.0212   0.8414   0.2406
  -1.000   0.0185   0.00697   0.00166  -0.0183   0.8298   0.5260
  -0.750   0.0275   0.00603   0.00160  -0.0141   0.8230   0.7579
  -0.500   0.1272   0.00617   0.00223  -0.0289   0.8137   0.9278
  -0.250   0.1534   0.00626   0.00226  -0.0283   0.8040   0.9397
   0.000   0.1779   0.00635   0.00229  -0.0273   0.7905   0.9496
   0.250   0.2117   0.00646   0.00227  -0.0283   0.7369   0.9557
   0.500   0.2293   0.00710   0.00226  -0.0259   0.6062   0.9637
   0.750   0.2582   0.00764   0.00238  -0.0263   0.5111   0.9673
   1.000   0.2844   0.00807   0.00249  -0.0262   0.4376   0.9719
   1.250   0.3093   0.00846   0.00259  -0.0257   0.3757   0.9760
   1.500   0.3407   0.00880   0.00266  -0.0268   0.3150   0.9779
   1.750   0.3714   0.00908   0.00274  -0.0277   0.2704   0.9802
   2.000   0.4007   0.00933   0.00282  -0.0282   0.2375   0.9828
   2.250   0.4275   0.00955   0.00292  -0.0281   0.2151   0.9856
   2.500   0.4587   0.00971   0.00299  -0.0290   0.1978   0.9870
   2.750   0.4908   0.00985   0.00308  -0.0301   0.1854   0.9885
   3.000   0.5226   0.00999   0.00317  -0.0312   0.1766   0.9903
   3.250   0.5545   0.01017   0.00328  -0.0322   0.1674   0.9926
   3.500   0.5861   0.01030   0.00341  -0.0332   0.1605   0.9948
   3.750   0.6191   0.01045   0.00352  -0.0346   0.1542   0.9964
   4.000   0.6507   0.01056   0.00364  -0.0356   0.1500   0.9980
   4.250   0.6814   0.01069   0.00378  -0.0364   0.1451   0.9993
   4.500   0.7085   0.01086   0.00394  -0.0364   0.1401   1.0000
   4.750   0.7316   0.01103   0.00412  -0.0355   0.1367   1.0000
   5.000   0.7547   0.01118   0.00428  -0.0347   0.1311   1.0000
   5.250   0.7773   0.01138   0.00446  -0.0337   0.1228   1.0000
   5.500   0.8003   0.01154   0.00464  -0.0329   0.1151   1.0000
   5.750   0.8230   0.01174   0.00483  -0.0319   0.1078   1.0000
   6.000   0.8455   0.01195   0.00503  -0.0310   0.0952   1.0000
   6.250   0.8666   0.01230   0.00527  -0.0298   0.0773   1.0000
   6.500   0.8873   0.01269   0.00560  -0.0286   0.0623   1.0000
   6.750   0.9076   0.01314   0.00599  -0.0273   0.0487   1.0000
   7.000   0.9274   0.01363   0.00643  -0.0260   0.0363   1.0000
   7.250   0.9471   0.01413   0.00689  -0.0246   0.0270   1.0000
   7.500   0.9669   0.01461   0.00737  -0.0232   0.0221   1.0000
   7.750   0.9865   0.01511   0.00789  -0.0218   0.0193   1.0000
   8.000   1.0065   0.01553   0.00839  -0.0204   0.0178   1.0000
   8.250   1.0255   0.01606   0.00895  -0.0190   0.0162   1.0000
   8.500   1.0441   0.01661   0.00956  -0.0174   0.0150   1.0000
   8.750   1.0629   0.01710   0.01013  -0.0159   0.0142   1.0000
   9.000   1.0811   0.01762   0.01072  -0.0143   0.0134   1.0000
   9.250   1.0984   0.01821   0.01138  -0.0125   0.0128   1.0000
   9.500   1.1141   0.01891   0.01215  -0.0106   0.0122   1.0000
   9.750   1.1288   0.01965   0.01298  -0.0084   0.0118   1.0000
  10.000   1.1438   0.02031   0.01374  -0.0064   0.0115   1.0000
  10.250   1.1583   0.02096   0.01449  -0.0042   0.0112   1.0000
  10.500   1.1710   0.02170   0.01533  -0.0018   0.0109   1.0000
  10.750   1.1827   0.02246   0.01618   0.0007   0.0105   1.0000
  11.000   1.1927   0.02327   0.01709   0.0035   0.0103   1.0000
  11.250   1.2019   0.02407   0.01800   0.0063   0.0101   1.0000
  11.500   1.2073   0.02487   0.01889   0.0099   0.0098   1.0000
  11.750   1.2089   0.02569   0.01979   0.0140   0.0097   1.0000
  12.000   1.2106   0.02659   0.02078   0.0179   0.0095   1.0000
  12.250   1.2117   0.02763   0.02192   0.0215   0.0094   1.0000
  12.500   1.2084   0.02905   0.02343   0.0253   0.0092   1.0000
  12.750   1.2080   0.03042   0.02492   0.0285   0.0090   1.0000
  13.000   1.2089   0.03179   0.02642   0.0312   0.0090   1.0000
  13.250   1.2082   0.03340   0.02817   0.0337   0.0088   1.0000
  13.500   1.2076   0.03508   0.03001   0.0359   0.0087   1.0000
  13.750   1.2042   0.03711   0.03217   0.0380   0.0087   1.0000
  14.000   1.2008   0.03929   0.03450   0.0395   0.0086   1.0000
  14.250   1.1935   0.04205   0.03742   0.0407   0.0084   1.0000
  14.500   1.1869   0.04505   0.04057   0.0411   0.0084   1.0000
  14.750   1.1764   0.04893   0.04461   0.0405   0.0084   1.0000
  15.000   1.1641   0.05369   0.04954   0.0386   0.0083   1.0000
  15.250   1.1492   0.05960   0.05562   0.0355   0.0083   1.0000
  15.500   1.1333   0.06637   0.06257   0.0314   0.0083   1.0000
  15.750   1.1167   0.07351   0.06985   0.0272   0.0083   1.0000
  16.000   1.0934   0.08187   0.07836   0.0226   0.0083   1.0000
  16.250   1.0748   0.08937   0.08598   0.0186   0.0083   1.0000
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