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DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DSMA-523B AIRFOIL (dsma523b-il)
Reynolds number: 200,000
Max Cl/Cd: 39.29 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dsma523b-il-200000-n5.txt
Download as CSV file: xf-dsma523b-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DSMA-523B 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  -0.9065   0.07120   0.06603  -0.0523   1.0000   0.0302
 -13.250  -0.9414   0.06353   0.05811  -0.0558   1.0000   0.0302
 -13.000  -0.9694   0.05782   0.05214  -0.0571   1.0000   0.0303
 -12.750  -0.9937   0.05322   0.04728  -0.0569   1.0000   0.0304
 -12.500  -1.0153   0.04952   0.04334  -0.0555   1.0000   0.0305
 -12.250  -1.0314   0.04692   0.04057  -0.0530   1.0000   0.0307
 -12.000  -1.0312   0.04493   0.03850  -0.0520   1.0000   0.0309
 -11.750  -1.0248   0.04311   0.03660  -0.0517   1.0000   0.0311
 -11.500  -1.0145   0.04148   0.03489  -0.0519   1.0000   0.0315
 -11.250  -1.0017   0.03981   0.03312  -0.0524   1.0000   0.0318
 -11.000  -0.9866   0.03815   0.03132  -0.0531   1.0000   0.0323
 -10.750  -0.9701   0.03644   0.02943  -0.0536   1.0000   0.0329
 -10.500  -0.9522   0.03467   0.02746  -0.0541   1.0000   0.0335
 -10.250  -0.9330   0.03284   0.02539  -0.0545   1.0000   0.0342
 -10.000  -0.9125   0.03103   0.02330  -0.0548   1.0000   0.0350
  -9.750  -0.8904   0.02980   0.02197  -0.0550   1.0000   0.0355
  -9.500  -0.8670   0.02898   0.02111  -0.0554   1.0000   0.0360
  -9.250  -0.8429   0.02817   0.02025  -0.0557   1.0000   0.0366
  -9.000  -0.8182   0.02742   0.01943  -0.0561   1.0000   0.0375
  -8.750  -0.7932   0.02660   0.01848  -0.0564   1.0000   0.0387
  -8.500  -0.7680   0.02564   0.01734  -0.0565   1.0000   0.0402
  -8.250  -0.7422   0.02508   0.01680  -0.0569   1.0000   0.0409
  -8.000  -0.7159   0.02452   0.01622  -0.0573   1.0000   0.0419
  -7.750  -0.6895   0.02390   0.01553  -0.0576   1.0000   0.0432
  -7.500  -0.6626   0.02325   0.01478  -0.0579   1.0000   0.0448
  -7.250  -0.6355   0.02270   0.01421  -0.0583   1.0000   0.0462
  -7.000  -0.6079   0.02224   0.01376  -0.0588   1.0000   0.0478
  -6.750  -0.5798   0.02182   0.01324  -0.0593   1.0000   0.0501
  -6.500  -0.5517   0.02131   0.01273  -0.0598   1.0000   0.0520
  -6.250  -0.5231   0.02080   0.01226  -0.0604   1.0000   0.0540
  -6.000  -0.4941   0.02042   0.01181  -0.0611   1.0000   0.0565
  -5.750  -0.4636   0.01984   0.01131  -0.0622   1.0000   0.0590
  -5.500  -0.4326   0.01938   0.01087  -0.0634   1.0000   0.0620
  -5.250  -0.4001   0.01891   0.01041  -0.0650   1.0000   0.0646
  -5.000  -0.3658   0.01842   0.00997  -0.0671   1.0000   0.0678
  -4.750  -0.3326   0.01809   0.00965  -0.0687   1.0000   0.0711
  -4.250  -0.2651   0.01750   0.00917  -0.0722   1.0000   0.0793
  -4.000  -0.2317   0.01728   0.00907  -0.0739   1.0000   0.0865
  -3.750  -0.1980   0.01708   0.00901  -0.0756   1.0000   0.1059
  -3.500  -0.1624   0.01684   0.00895  -0.0777   1.0000   0.1375
  -3.250  -0.1253   0.01658   0.00893  -0.0802   1.0000   0.1810
  -3.000  -0.0868   0.01632   0.00893  -0.0831   1.0000   0.2356
  -2.750  -0.0401   0.01585   0.00894  -0.0881   1.0000   0.3372
  -2.500   0.0048   0.01551   0.00911  -0.0924   1.0000   0.4470
  -2.250   0.0245   0.01589   0.01007  -0.0901   1.0000   0.5394
  -1.750   0.0637   0.01678   0.01116  -0.0857   1.0000   0.6038
  -1.500   0.0933   0.01699   0.01136  -0.0863   1.0000   0.6211
  -1.250   0.1355   0.01719   0.01156  -0.0890   0.9954   0.6404
  -1.000   0.1917   0.01737   0.01176  -0.0937   0.9829   0.6634
  -0.750   0.2417   0.01725   0.01171  -0.0970   0.9721   0.6729
  -0.500   0.2762   0.01677   0.01127  -0.0975   0.9537   0.6773
   0.000   0.4473   0.01436   0.00796  -0.1184   0.6706   0.6881
   0.250   0.4539   0.01627   0.00850  -0.1135   0.3894   0.6909
   0.500   0.4735   0.01714   0.00885  -0.1116   0.2754   0.6941
   0.750   0.4977   0.01783   0.00910  -0.1109   0.1836   0.6977
   1.000   0.5267   0.01840   0.00931  -0.1115   0.1234   0.7021
   1.250   0.5557   0.01878   0.00954  -0.1118   0.1021   0.7058
   1.500   0.5793   0.01911   0.00983  -0.1105   0.0921   0.7078
   1.750   0.6049   0.01944   0.01012  -0.1098   0.0844   0.7095
   2.000   0.6319   0.01973   0.01040  -0.1095   0.0788   0.7109
   2.250   0.6596   0.02002   0.01069  -0.1094   0.0743   0.7122
   2.500   0.6872   0.02045   0.01104  -0.1094   0.0703   0.7133
   2.750   0.7156   0.02073   0.01135  -0.1095   0.0670   0.7147
   3.000   0.7439   0.02106   0.01167  -0.1096   0.0638   0.7162
   3.250   0.7723   0.02148   0.01204  -0.1098   0.0613   0.7174
   3.500   0.8006   0.02197   0.01251  -0.1100   0.0592   0.7184
   3.750   0.8296   0.02236   0.01295  -0.1102   0.0568   0.7195
   4.000   0.8585   0.02277   0.01334  -0.1105   0.0545   0.7205
   4.250   0.8871   0.02324   0.01377  -0.1108   0.0527   0.7215
   4.500   0.9154   0.02391   0.01441  -0.1110   0.0511   0.7225
   4.750   0.9446   0.02446   0.01503  -0.1114   0.0495   0.7236
   5.000   0.9714   0.02498   0.01560  -0.1111   0.0477   0.7246
   5.250   0.9973   0.02547   0.01612  -0.1106   0.0462   0.7253
   5.500   1.0231   0.02604   0.01670  -0.1103   0.0450   0.7260
   5.750   1.0490   0.02687   0.01754  -0.1099   0.0440   0.7266
   6.000   1.0753   0.02767   0.01849  -0.1095   0.0429   0.7273
   6.250   1.1013   0.02852   0.01948  -0.1091   0.0418   0.7280
   6.500   1.1268   0.02940   0.02048  -0.1087   0.0408   0.7287
   6.750   1.1519   0.03023   0.02140  -0.1082   0.0399   0.7294
   7.000   1.1765   0.03098   0.02219  -0.1077   0.0391   0.7301
   7.250   1.2006   0.03179   0.02303  -0.1071   0.0383   0.7309
   7.500   1.2240   0.03297   0.02435  -0.1064   0.0375   0.7317
   7.750   1.2464   0.03431   0.02598  -0.1054   0.0366   0.7325
   8.000   1.2677   0.03578   0.02771  -0.1043   0.0358   0.7333
   8.250   1.2877   0.03725   0.02942  -0.1031   0.0350   0.7343
   8.500   1.3068   0.03865   0.03101  -0.1017   0.0344   0.7355
   8.750   1.3256   0.03986   0.03238  -0.1004   0.0338   0.7366
   9.000   1.3438   0.04099   0.03362  -0.0990   0.0333   0.7375
   9.250   1.3613   0.04215   0.03488  -0.0976   0.0329   0.7383
   9.500   1.3778   0.04337   0.03617  -0.0961   0.0325   0.7391
   9.750   1.3852   0.04590   0.03907  -0.0933   0.0320   0.7398
  10.000   1.3832   0.04941   0.04312  -0.0893   0.0314   0.7404
  10.250   1.3737   0.05335   0.04755  -0.0846   0.0310   0.7410
  10.500   1.3554   0.05742   0.05204  -0.0791   0.0307   0.7415
  10.750   1.3263   0.06153   0.05651  -0.0726   0.0305   0.7420
  11.000   1.2903   0.06713   0.06250  -0.0675   0.0303   0.7424
  11.250   1.2413   0.07501   0.07078  -0.0648   0.0303   0.7426
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