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RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il)
Reynolds number: 200,000
Max Cl/Cd: 62.68 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg15a111-il-200000-n5.txt
Download as CSV file: xf-rg15a111-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 15A-1.8/11.0 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5286   0.09851   0.09475  -0.0311   1.0000   0.0148
 -11.250  -0.6870   0.05531   0.05111  -0.0597   1.0000   0.0129
 -11.000  -0.7068   0.05042   0.04607  -0.0622   1.0000   0.0128
 -10.750  -0.7274   0.04665   0.04212  -0.0623   1.0000   0.0128
 -10.500  -0.7490   0.04395   0.03925  -0.0597   1.0000   0.0129
 -10.250  -0.7634   0.04122   0.03627  -0.0567   1.0000   0.0129
 -10.000  -0.7726   0.03831   0.03312  -0.0540   1.0000   0.0131
  -9.750  -0.7736   0.03596   0.03059  -0.0516   1.0000   0.0133
  -9.500  -0.7696   0.03402   0.02848  -0.0494   1.0000   0.0136
  -9.250  -0.7626   0.03228   0.02656  -0.0473   1.0000   0.0139
  -9.000  -0.7539   0.03054   0.02462  -0.0453   1.0000   0.0143
  -8.750  -0.7433   0.02896   0.02282  -0.0433   1.0000   0.0148
  -8.500  -0.7309   0.02751   0.02115  -0.0414   1.0000   0.0155
  -8.250  -0.7170   0.02619   0.01959  -0.0396   1.0000   0.0165
  -8.000  -0.7015   0.02509   0.01818  -0.0379   1.0000   0.0174
  -7.750  -0.6876   0.02344   0.01644  -0.0361   1.0000   0.0181
  -7.500  -0.6668   0.02231   0.01522  -0.0355   0.9991   0.0190
  -7.250  -0.6352   0.02120   0.01398  -0.0370   0.9958   0.0201
  -7.000  -0.6035   0.02022   0.01285  -0.0383   0.9925   0.0217
  -6.750  -0.5727   0.01924   0.01172  -0.0394   0.9885   0.0235
  -6.500  -0.5407   0.01829   0.01072  -0.0409   0.9849   0.0253
  -6.250  -0.5090   0.01754   0.00989  -0.0421   0.9809   0.0272
  -6.000  -0.4782   0.01692   0.00916  -0.0430   0.9758   0.0298
  -5.750  -0.4454   0.01616   0.00838  -0.0445   0.9718   0.0333
  -5.500  -0.4148   0.01557   0.00770  -0.0452   0.9665   0.0375
  -5.250  -0.3835   0.01494   0.00708  -0.0462   0.9611   0.0449
  -5.000  -0.3489   0.01439   0.00654  -0.0479   0.9575   0.0599
  -4.750  -0.3200   0.01391   0.00611  -0.0483   0.9505   0.0776
  -4.500  -0.2864   0.01346   0.00569  -0.0497   0.9457   0.0975
  -4.250  -0.2528   0.01301   0.00533  -0.0511   0.9410   0.1229
  -4.000  -0.2227   0.01253   0.00501  -0.0518   0.9338   0.1626
  -3.750  -0.1876   0.01200   0.00467  -0.0536   0.9292   0.2124
  -3.500  -0.1586   0.01158   0.00440  -0.0540   0.9207   0.2601
  -3.250  -0.1244   0.01111   0.00411  -0.0555   0.9149   0.3156
  -3.000  -0.0955   0.01069   0.00389  -0.0558   0.9055   0.3757
  -2.750  -0.0629   0.01020   0.00367  -0.0569   0.8986   0.4538
  -2.500  -0.0350   0.00981   0.00359  -0.0568   0.8883   0.5359
  -2.250  -0.0057   0.00960   0.00357  -0.0568   0.8783   0.6043
  -2.000   0.0257   0.00949   0.00349  -0.0572   0.8684   0.6468
  -1.750   0.0555   0.00943   0.00342  -0.0573   0.8569   0.6760
  -1.500   0.0842   0.00938   0.00337  -0.0571   0.8444   0.6990
  -1.250   0.1129   0.00935   0.00330  -0.0569   0.8316   0.7193
  -1.000   0.1411   0.00934   0.00325  -0.0566   0.8184   0.7366
  -0.750   0.1687   0.00933   0.00322  -0.0563   0.8047   0.7522
  -0.500   0.1960   0.00934   0.00318  -0.0558   0.7904   0.7667
  -0.250   0.2230   0.00935   0.00315  -0.0553   0.7755   0.7804
   0.000   0.2494   0.00937   0.00313  -0.0547   0.7601   0.7933
   0.250   0.2755   0.00940   0.00313  -0.0540   0.7443   0.8059
   0.500   0.3012   0.00944   0.00313  -0.0532   0.7283   0.8182
   0.750   0.3268   0.00948   0.00313  -0.0525   0.7118   0.8304
   1.000   0.3521   0.00954   0.00314  -0.0517   0.6951   0.8425
   1.250   0.3773   0.00960   0.00316  -0.0508   0.6780   0.8547
   1.500   0.4020   0.00965   0.00319  -0.0499   0.6599   0.8665
   1.750   0.4266   0.00972   0.00323  -0.0490   0.6412   0.8786
   2.000   0.4515   0.00981   0.00326  -0.0481   0.6222   0.8907
   2.250   0.4770   0.00990   0.00331  -0.0475   0.6025   0.9029
   2.500   0.5034   0.01000   0.00337  -0.0470   0.5815   0.9157
   2.750   0.5309   0.01014   0.00344  -0.0468   0.5598   0.9293
   3.000   0.5607   0.01028   0.00353  -0.0472   0.5366   0.9436
   3.250   0.5928   0.01046   0.00363  -0.0481   0.5128   0.9585
   3.500   0.6262   0.01067   0.00377  -0.0495   0.4881   0.9748
   3.750   0.6601   0.01089   0.00391  -0.0510   0.4626   0.9961
   4.000   0.6837   0.01114   0.00408  -0.0503   0.4401   1.0000
   4.250   0.7061   0.01141   0.00427  -0.0494   0.4168   1.0000
   4.500   0.7289   0.01171   0.00448  -0.0486   0.3928   1.0000
   4.750   0.7515   0.01203   0.00471  -0.0477   0.3681   1.0000
   5.000   0.7743   0.01237   0.00496  -0.0469   0.3434   1.0000
   5.250   0.7973   0.01272   0.00525  -0.0462   0.3200   1.0000
   5.500   0.8200   0.01310   0.00555  -0.0454   0.2973   1.0000
   5.750   0.8429   0.01348   0.00588  -0.0446   0.2748   1.0000
   6.250   0.8880   0.01432   0.00662  -0.0431   0.2323   1.0000
   6.500   0.9097   0.01481   0.00703  -0.0422   0.2101   1.0000
   6.750   0.9313   0.01532   0.00747  -0.0413   0.1869   1.0000
   7.000   0.9523   0.01587   0.00794  -0.0404   0.1649   1.0000
   7.250   0.9733   0.01643   0.00844  -0.0395   0.1455   1.0000
   7.500   0.9939   0.01701   0.00899  -0.0385   0.1288   1.0000
   7.750   1.0142   0.01761   0.00956  -0.0375   0.1141   1.0000
   8.000   1.0345   0.01821   0.01015  -0.0364   0.1014   1.0000
   8.250   1.0542   0.01884   0.01078  -0.0353   0.0896   1.0000
   8.500   1.0734   0.01949   0.01145  -0.0342   0.0793   1.0000
   8.750   1.0917   0.02018   0.01219  -0.0329   0.0708   1.0000
   9.000   1.1085   0.02098   0.01298  -0.0314   0.0629   1.0000
   9.250   1.1262   0.02167   0.01375  -0.0301   0.0565   1.0000
   9.500   1.1405   0.02257   0.01464  -0.0283   0.0509   1.0000
   9.750   1.1556   0.02330   0.01551  -0.0265   0.0467   1.0000
  10.000   1.1678   0.02417   0.01642  -0.0244   0.0430   1.0000
  10.250   1.1780   0.02517   0.01746  -0.0221   0.0398   1.0000
  10.500   1.1905   0.02603   0.01847  -0.0203   0.0367   1.0000
  10.750   1.2008   0.02704   0.01953  -0.0183   0.0337   1.0000
  11.000   1.2089   0.02821   0.02075  -0.0162   0.0309   1.0000
  11.250   1.2198   0.02922   0.02189  -0.0145   0.0282   1.0000
  11.500   1.2281   0.03043   0.02319  -0.0128   0.0260   1.0000
  11.750   1.2307   0.03209   0.02490  -0.0108   0.0241   1.0000
  12.000   1.2381   0.03348   0.02645  -0.0093   0.0226   1.0000
  12.250   1.2445   0.03501   0.02812  -0.0079   0.0207   1.0000
  12.500   1.2482   0.03681   0.03006  -0.0067   0.0194   1.0000
  12.750   1.2478   0.03907   0.03242  -0.0056   0.0184   1.0000
  13.000   1.2465   0.04157   0.03505  -0.0047   0.0174   1.0000
  13.250   1.2468   0.04408   0.03774  -0.0042   0.0164   1.0000
  13.500   1.2459   0.04684   0.04065  -0.0040   0.0154   1.0000
  13.750   1.2435   0.04990   0.04385  -0.0042   0.0147   1.0000
  14.000   1.2397   0.05330   0.04737  -0.0048   0.0139   1.0000
  14.250   1.2330   0.05724   0.05142  -0.0058   0.0135   1.0000
  14.500   1.2256   0.06152   0.05586  -0.0072   0.0129   1.0000
  14.750   1.2188   0.06593   0.06045  -0.0087   0.0124   1.0000
  15.000   1.2103   0.07079   0.06549  -0.0107   0.0120   1.0000
  15.250   1.2011   0.07601   0.07088  -0.0131   0.0116   1.0000
  15.500   1.1902   0.08174   0.07676  -0.0159   0.0114   1.0000
  15.750   1.1783   0.08787   0.08305  -0.0190   0.0112   1.0000
  16.000   1.1664   0.09428   0.08961  -0.0225   0.0109   1.0000
  16.250   1.1529   0.10114   0.09662  -0.0262   0.0108   1.0000
  16.500   1.1389   0.10839   0.10403  -0.0303   0.0107   1.0000
  16.750   1.1249   0.11581   0.11159  -0.0344   0.0107   1.0000
  17.000   1.1100   0.12364   0.11956  -0.0389   0.0106   1.0000
  17.250   1.0951   0.13174   0.12780  -0.0436   0.0105   1.0000
  17.500   1.0803   0.14006   0.13624  -0.0485   0.0104   1.0000
  17.750   1.0642   0.14893   0.14525  -0.0538   0.0104   1.0000
  18.000   1.0439   0.15935   0.15583  -0.0599   0.0106   1.0000
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