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RAE6-9CK AIRFOIL (rae69ck-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAE6-9CK AIRFOIL (rae69ck-il)
Reynolds number: 200,000
Max Cl/Cd: 49.1 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae69ck-il-200000-n5.txt
Download as CSV file: xf-rae69ck-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE6-9CK AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7179   0.08429   0.08026  -0.0480   1.0000   0.0142
 -13.250  -0.7523   0.07422   0.07000  -0.0543   1.0000   0.0142
 -13.000  -0.7788   0.06695   0.06257  -0.0582   1.0000   0.0139
 -12.750  -0.8013   0.06101   0.05643  -0.0607   1.0000   0.0139
 -12.500  -0.8201   0.05607   0.05127  -0.0623   1.0000   0.0139
 -12.250  -0.8361   0.05181   0.04680  -0.0630   1.0000   0.0140
 -12.000  -0.8496   0.04811   0.04287  -0.0629   1.0000   0.0141
 -11.750  -0.8606   0.04490   0.03943  -0.0622   1.0000   0.0143
 -11.500  -0.8692   0.04210   0.03639  -0.0609   1.0000   0.0145
 -11.250  -0.8759   0.03965   0.03370  -0.0591   1.0000   0.0148
 -11.000  -0.8811   0.03762   0.03145  -0.0567   1.0000   0.0151
 -10.750  -0.8867   0.03592   0.02953  -0.0535   1.0000   0.0154
 -10.500  -0.8882   0.03446   0.02783  -0.0504   1.0000   0.0158
 -10.250  -0.8855   0.03289   0.02623  -0.0479   1.0000   0.0164
 -10.000  -0.8798   0.03168   0.02492  -0.0455   1.0000   0.0168
  -9.750  -0.8727   0.03060   0.02376  -0.0432   1.0000   0.0174
  -9.500  -0.8644   0.02939   0.02243  -0.0408   1.0000   0.0179
  -9.250  -0.8551   0.02821   0.02112  -0.0385   1.0000   0.0185
  -9.000  -0.8448   0.02705   0.01984  -0.0363   1.0000   0.0191
  -8.750  -0.8339   0.02597   0.01860  -0.0340   1.0000   0.0199
  -8.500  -0.8220   0.02504   0.01752  -0.0319   1.0000   0.0207
  -8.250  -0.7993   0.02377   0.01621  -0.0322   0.9979   0.0221
  -8.000  -0.7700   0.02286   0.01525  -0.0337   0.9948   0.0238
  -7.750  -0.7423   0.02187   0.01418  -0.0347   0.9915   0.0254
  -7.500  -0.7139   0.02093   0.01309  -0.0358   0.9878   0.0272
  -7.250  -0.6851   0.01986   0.01199  -0.0373   0.9845   0.0297
  -7.000  -0.6564   0.01916   0.01125  -0.0384   0.9809   0.0330
  -6.750  -0.6285   0.01844   0.01042  -0.0392   0.9765   0.0361
  -6.500  -0.5988   0.01758   0.00954  -0.0406   0.9730   0.0412
  -6.250  -0.5664   0.01693   0.00883  -0.0424   0.9705   0.0480
  -6.000  -0.5406   0.01633   0.00821  -0.0426   0.9651   0.0561
  -5.750  -0.5109   0.01571   0.00761  -0.0438   0.9612   0.0697
  -5.500  -0.4790   0.01504   0.00702  -0.0454   0.9583   0.0919
  -5.250  -0.4467   0.01428   0.00644  -0.0473   0.9558   0.1340
  -5.000  -0.4235   0.01341   0.00587  -0.0475   0.9496   0.2021
  -4.750  -0.3969   0.01187   0.00521  -0.0490   0.9457   0.3878
  -4.500  -0.3637   0.01160   0.00519  -0.0504   0.9432   0.4750
  -4.250  -0.3318   0.01156   0.00514  -0.0513   0.9399   0.5075
  -4.000  -0.3034   0.01156   0.00509  -0.0515   0.9345   0.5296
  -3.750  -0.2708   0.01157   0.00505  -0.0525   0.9311   0.5478
  -3.500  -0.2371   0.01160   0.00507  -0.0536   0.9285   0.5650
  -3.250  -0.2080   0.01172   0.00518  -0.0537   0.9239   0.5824
  -3.000  -0.1786   0.01172   0.00513  -0.0540   0.9188   0.5925
  -2.750  -0.1457   0.01162   0.00498  -0.0551   0.9154   0.5957
  -2.500  -0.1114   0.01151   0.00481  -0.0566   0.9128   0.5993
  -2.250  -0.0845   0.01145   0.00468  -0.0565   0.9064   0.6033
  -2.000  -0.0532   0.01136   0.00455  -0.0573   0.9020   0.6065
  -1.750  -0.0200   0.01126   0.00444  -0.0584   0.8988   0.6093
  -1.500   0.0079   0.01122   0.00438  -0.0585   0.8930   0.6129
  -1.250   0.0382   0.01116   0.00429  -0.0590   0.8878   0.6168
  -1.000   0.0708   0.01107   0.00418  -0.0601   0.8841   0.6205
  -0.750   0.0985   0.01104   0.00418  -0.0601   0.8781   0.6234
  -0.500   0.1281   0.01099   0.00415  -0.0605   0.8726   0.6269
  -0.250   0.1602   0.01093   0.00409  -0.0613   0.8687   0.6311
   0.000   0.1871   0.01093   0.00410  -0.0612   0.8617   0.6353
   0.250   0.2170   0.01088   0.00411  -0.0616   0.8564   0.6383
   0.500   0.2463   0.01086   0.00413  -0.0619   0.8508   0.6420
   0.750   0.2744   0.01085   0.00417  -0.0619   0.8438   0.6463
   1.000   0.3052   0.01081   0.00415  -0.0625   0.8382   0.6508
   1.250   0.3316   0.01081   0.00423  -0.0621   0.8291   0.6545
   1.500   0.3606   0.01078   0.00425  -0.0622   0.8206   0.6588
   1.750   0.3896   0.01073   0.00425  -0.0623   0.8099   0.6635
   2.000   0.4170   0.01068   0.00425  -0.0619   0.7954   0.6675
   2.250   0.4428   0.01061   0.00421  -0.0610   0.7717   0.6720
   2.500   0.4688   0.01057   0.00409  -0.0601   0.7357   0.6773
   2.750   0.4935   0.01061   0.00408  -0.0591   0.6978   0.6820
   3.000   0.5179   0.01072   0.00412  -0.0581   0.6549   0.6867
   3.250   0.5396   0.01099   0.00415  -0.0566   0.5831   0.6920
   3.500   0.5532   0.01175   0.00433  -0.0537   0.4535   0.6971
   3.750   0.5643   0.01283   0.00478  -0.0509   0.3149   0.7024
   4.000   0.5795   0.01385   0.00527  -0.0490   0.2019   0.7087
   4.250   0.5973   0.01469   0.00576  -0.0475   0.1243   0.7141
   4.500   0.6180   0.01531   0.00625  -0.0465   0.0866   0.7203
   4.750   0.6399   0.01585   0.00672  -0.0456   0.0666   0.7265
   5.000   0.6620   0.01632   0.00723  -0.0446   0.0560   0.7330
   5.250   0.6841   0.01686   0.00779  -0.0437   0.0487   0.7404
   5.500   0.7058   0.01734   0.00836  -0.0427   0.0429   0.7474
   5.750   0.7265   0.01798   0.00906  -0.0415   0.0392   0.7553
   6.000   0.7478   0.01851   0.00971  -0.0404   0.0358   0.7629
   6.250   0.7688   0.01910   0.01034  -0.0394   0.0325   0.7713
   6.500   0.7880   0.01990   0.01123  -0.0380   0.0303   0.7805
   6.750   0.8084   0.02061   0.01209  -0.0367   0.0285   0.7899
   7.000   0.8289   0.02135   0.01294  -0.0356   0.0267   0.8004
   7.250   0.8489   0.02202   0.01368  -0.0344   0.0250   0.8116
   7.500   0.8680   0.02305   0.01479  -0.0332   0.0234   0.8234
   7.750   0.8887   0.02397   0.01590  -0.0320   0.0223   0.8370
   8.000   0.9090   0.02502   0.01715  -0.0307   0.0212   0.8527
   8.250   0.9285   0.02608   0.01839  -0.0294   0.0202   0.8717
   8.500   0.9461   0.02701   0.01949  -0.0278   0.0194   0.8980
   8.750   0.9660   0.02789   0.02049  -0.0269   0.0185   0.9821
   9.000   0.9867   0.02954   0.02232  -0.0263   0.0176   1.0000
   9.250   1.0061   0.03125   0.02432  -0.0254   0.0167   1.0000
   9.500   1.0229   0.03332   0.02671  -0.0242   0.0161   1.0000
   9.750   1.0365   0.03549   0.02917  -0.0227   0.0156   1.0000
  10.000   1.0470   0.03767   0.03163  -0.0209   0.0151   1.0000
  10.250   1.0540   0.03995   0.03419  -0.0188   0.0148   1.0000
  10.500   1.0561   0.04216   0.03664  -0.0161   0.0145   1.0000
  10.750   1.0551   0.04436   0.03906  -0.0132   0.0143   1.0000
  11.000   1.0506   0.04681   0.04173  -0.0103   0.0141   1.0000
  11.250   1.0435   0.04940   0.04454  -0.0077   0.0140   1.0000
  11.500   1.0336   0.05232   0.04766  -0.0055   0.0139   1.0000
  11.750   1.0252   0.05506   0.05053  -0.0041   0.0136   1.0000
  12.000   1.0068   0.05930   0.05503  -0.0031   0.0136   1.0000
  12.250   0.9885   0.06380   0.05968  -0.0032   0.0135   1.0000
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