Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RG 8 AIRFOIL (rg8-il)
Reynolds number: 200,000
Max Cl/Cd: 68.33 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg8-il-200000-n5.txt
Download as CSV file: xf-rg8-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 8 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5113   0.09246   0.08879  -0.0375   1.0000   0.0166
 -10.500  -0.5908   0.06625   0.06254  -0.0523   1.0000   0.0152
 -10.250  -0.6188   0.05812   0.05429  -0.0583   1.0000   0.0151
 -10.000  -0.6431   0.05315   0.04925  -0.0605   1.0000   0.0150
  -9.750  -0.6685   0.05002   0.04606  -0.0595   1.0000   0.0149
  -9.500  -0.6888   0.04657   0.04243  -0.0582   1.0000   0.0149
  -9.250  -0.7027   0.04294   0.03851  -0.0567   1.0000   0.0150
  -9.000  -0.7072   0.03988   0.03508  -0.0552   1.0000   0.0153
  -8.750  -0.7090   0.03641   0.03124  -0.0538   1.0000   0.0157
  -8.500  -0.7027   0.03369   0.02827  -0.0526   1.0000   0.0161
  -8.250  -0.6911   0.03180   0.02620  -0.0515   1.0000   0.0165
  -8.000  -0.6777   0.02979   0.02393  -0.0505   1.0000   0.0168
  -7.750  -0.6530   0.02761   0.02142  -0.0515   0.9982   0.0172
  -7.500  -0.6236   0.02569   0.01917  -0.0530   0.9956   0.0177
  -7.250  -0.5937   0.02401   0.01723  -0.0544   0.9932   0.0182
  -7.000  -0.5643   0.02256   0.01555  -0.0554   0.9903   0.0189
  -6.750  -0.5337   0.02131   0.01412  -0.0566   0.9874   0.0195
  -6.500  -0.5015   0.02032   0.01296  -0.0580   0.9848   0.0205
  -6.250  -0.4699   0.01937   0.01186  -0.0592   0.9821   0.0216
  -6.000  -0.4415   0.01825   0.01067  -0.0600   0.9780   0.0227
  -5.750  -0.4098   0.01743   0.00977  -0.0612   0.9745   0.0238
  -5.500  -0.3758   0.01673   0.00898  -0.0629   0.9717   0.0252
  -5.250  -0.3461   0.01610   0.00826  -0.0636   0.9671   0.0271
  -5.000  -0.3144   0.01552   0.00756  -0.0646   0.9626   0.0296
  -4.750  -0.2801   0.01493   0.00696  -0.0662   0.9594   0.0365
  -4.500  -0.2497   0.01432   0.00644  -0.0671   0.9546   0.0546
  -4.250  -0.2185   0.01378   0.00601  -0.0681   0.9496   0.0839
  -4.000  -0.1838   0.01333   0.00563  -0.0698   0.9462   0.1147
  -3.750  -0.1535   0.01286   0.00532  -0.0706   0.9407   0.1550
  -3.250  -0.0867   0.01165   0.00469  -0.0737   0.9321   0.2986
  -3.000  -0.0576   0.01115   0.00445  -0.0743   0.9254   0.3758
  -2.750  -0.0251   0.01071   0.00434  -0.0753   0.9203   0.4674
  -2.500   0.0105   0.01048   0.00423  -0.0768   0.9162   0.5281
  -2.250   0.0401   0.01036   0.00413  -0.0769   0.9077   0.5597
  -2.000   0.0780   0.01022   0.00397  -0.0788   0.9031   0.5848
  -1.750   0.1083   0.01013   0.00388  -0.0791   0.8936   0.6048
  -1.500   0.1445   0.01002   0.00373  -0.0806   0.8867   0.6239
  -1.250   0.1776   0.00992   0.00363  -0.0814   0.8771   0.6399
  -1.000   0.2108   0.00983   0.00354  -0.0823   0.8669   0.6546
  -0.750   0.2454   0.00974   0.00343  -0.0835   0.8562   0.6688
  -0.500   0.2794   0.00967   0.00334  -0.0845   0.8444   0.6827
  -0.250   0.3117   0.00961   0.00327  -0.0851   0.8307   0.6952
   0.000   0.3425   0.00958   0.00322  -0.0855   0.8155   0.7067
   0.250   0.3723   0.00956   0.00319  -0.0856   0.7989   0.7179
   0.500   0.4016   0.00958   0.00316  -0.0857   0.7812   0.7286
   0.750   0.4303   0.00960   0.00315  -0.0856   0.7628   0.7383
   1.000   0.4581   0.00964   0.00315  -0.0854   0.7436   0.7472
   1.250   0.4851   0.00971   0.00317  -0.0850   0.7233   0.7569
   1.500   0.5116   0.00979   0.00321  -0.0845   0.7028   0.7666
   1.750   0.5372   0.00987   0.00326  -0.0839   0.6815   0.7767
   2.000   0.5625   0.00998   0.00332  -0.0832   0.6598   0.7878
   2.250   0.5873   0.01010   0.00341  -0.0823   0.6375   0.7998
   2.500   0.6113   0.01023   0.00350  -0.0814   0.6149   0.8130
   2.750   0.6348   0.01036   0.00361  -0.0803   0.5917   0.8276
   3.000   0.6576   0.01051   0.00372  -0.0790   0.5687   0.8439
   3.250   0.6798   0.01065   0.00387  -0.0777   0.5449   0.8627
   3.500   0.7015   0.01080   0.00399  -0.0762   0.5210   0.8867
   3.750   0.7239   0.01095   0.00412  -0.0749   0.4969   0.9192
   4.000   0.7547   0.01114   0.00426  -0.0756   0.4699   0.9858
   4.250   0.7794   0.01143   0.00448  -0.0751   0.4437   1.0000
   4.500   0.8036   0.01176   0.00472  -0.0745   0.4180   1.0000
   4.750   0.8273   0.01211   0.00498  -0.0739   0.3916   1.0000
   5.000   0.8507   0.01249   0.00526  -0.0731   0.3648   1.0000
   5.250   0.8738   0.01288   0.00556  -0.0724   0.3388   1.0000
   5.500   0.8968   0.01330   0.00592  -0.0716   0.3124   1.0000
   5.750   0.9195   0.01374   0.00628  -0.0708   0.2855   1.0000
   6.000   0.9417   0.01421   0.00667  -0.0700   0.2582   1.0000
   6.250   0.9637   0.01472   0.00709  -0.0691   0.2317   1.0000
   6.500   0.9853   0.01526   0.00754  -0.0682   0.2053   1.0000
   6.750   1.0066   0.01583   0.00805  -0.0673   0.1811   1.0000
   7.000   1.0279   0.01640   0.00857  -0.0663   0.1588   1.0000
   7.250   1.0486   0.01701   0.00913  -0.0653   0.1385   1.0000
   7.500   1.0682   0.01773   0.00975  -0.0642   0.1153   1.0000
   7.750   1.0870   0.01850   0.01040  -0.0629   0.0912   1.0000
   8.000   1.1051   0.01932   0.01113  -0.0616   0.0699   1.0000
   8.250   1.1235   0.02010   0.01186  -0.0603   0.0557   1.0000
   8.500   1.1417   0.02086   0.01263  -0.0590   0.0455   1.0000
   8.750   1.1588   0.02169   0.01347  -0.0575   0.0359   1.0000
   9.000   1.1742   0.02264   0.01442  -0.0558   0.0269   1.0000
   9.250   1.1872   0.02366   0.01545  -0.0536   0.0203   1.0000
   9.500   1.1986   0.02475   0.01657  -0.0513   0.0169   1.0000
   9.750   1.2102   0.02578   0.01775  -0.0490   0.0151   1.0000
  10.000   1.2209   0.02686   0.01895  -0.0467   0.0138   1.0000
  10.250   1.2296   0.02808   0.02027  -0.0443   0.0129   1.0000
  10.500   1.2344   0.02958   0.02186  -0.0415   0.0122   1.0000
  10.750   1.2409   0.03096   0.02340  -0.0391   0.0117   1.0000
  11.000   1.2461   0.03248   0.02508  -0.0368   0.0113   1.0000
  11.250   1.2505   0.03411   0.02686  -0.0346   0.0109   1.0000
  11.500   1.2543   0.03586   0.02875  -0.0326   0.0104   1.0000
  11.750   1.2580   0.03767   0.03070  -0.0309   0.0100   1.0000
  12.000   1.2603   0.03968   0.03284  -0.0294   0.0096   1.0000
  12.250   1.2613   0.04191   0.03519  -0.0281   0.0092   1.0000
  12.500   1.2598   0.04450   0.03794  -0.0271   0.0089   1.0000
  12.750   1.2558   0.04754   0.04111  -0.0264   0.0086   1.0000
  13.000   1.2500   0.05098   0.04471  -0.0259   0.0085   1.0000
  13.250   1.2466   0.05435   0.04822  -0.0259   0.0084   1.0000
  13.500   1.2429   0.05794   0.05200  -0.0262   0.0083   1.0000
  13.750   1.2380   0.06184   0.05609  -0.0269   0.0082   1.0000
  14.000   1.2315   0.06617   0.06062  -0.0280   0.0081   1.0000
  14.250   1.2242   0.07083   0.06546  -0.0295   0.0081   1.0000
  14.500   1.2158   0.07586   0.07068  -0.0314   0.0080   1.0000
  14.750   1.2061   0.08138   0.07640  -0.0338   0.0080   1.0000
  15.000   1.1952   0.08736   0.08257  -0.0367   0.0080   1.0000
  15.250   1.1832   0.09382   0.08922  -0.0400   0.0079   1.0000
  15.500   1.1705   0.10070   0.09628  -0.0438   0.0079   1.0000
  15.750   1.1566   0.10815   0.10393  -0.0481   0.0079   1.0000
  16.000   1.1423   0.11596   0.11191  -0.0527   0.0079   1.0000
  16.250   1.1273   0.12430   0.12042  -0.0578   0.0080   1.0000
  16.500   1.1114   0.13318   0.12946  -0.0633   0.0080   1.0000
  16.750   1.0949   0.14260   0.13903  -0.0691   0.0080   1.0000
  17.000   1.0771   0.15286   0.14944  -0.0756   0.0081   1.0000
  17.250   1.0578   0.16416   0.16086  -0.0825   0.0082   1.0000
  17.500   1.0340   0.17769   0.17450  -0.0905   0.0084   1.0000
<< Back to RG 8 AIRFOIL (rg8-il)

Polar data table (+)

Polar graphs


<< Back to RG 8 AIRFOIL (rg8-il)