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RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il)
Reynolds number: 500,000
Max Cl/Cd: 87.88 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg15a111-il-500000.txt
Download as CSV file: xf-rg15a111-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5621   0.08831   0.08598  -0.0355   1.0000   0.0164
 -11.250  -0.5596   0.08600   0.08369  -0.0368   1.0000   0.0168
 -11.000  -0.7510   0.04417   0.04100  -0.0643   1.0000   0.0123
 -10.750  -0.7698   0.04185   0.03861  -0.0617   1.0000   0.0125
 -10.500  -0.7891   0.03937   0.03596  -0.0577   1.0000   0.0125
 -10.250  -0.8016   0.03655   0.03285  -0.0543   1.0000   0.0124
 -10.000  -0.8075   0.03390   0.02998  -0.0512   1.0000   0.0125
  -9.750  -0.8067   0.03175   0.02764  -0.0485   1.0000   0.0127
  -9.500  -0.8026   0.02978   0.02549  -0.0460   1.0000   0.0129
  -9.250  -0.7950   0.02813   0.02366  -0.0436   1.0000   0.0131
  -9.000  -0.7831   0.02709   0.02253  -0.0417   1.0000   0.0135
  -8.750  -0.7714   0.02587   0.02117  -0.0397   1.0000   0.0140
  -8.500  -0.7591   0.02453   0.01966  -0.0376   1.0000   0.0145
  -8.250  -0.7453   0.02332   0.01825  -0.0357   1.0000   0.0151
  -8.000  -0.7202   0.02198   0.01666  -0.0359   0.9988   0.0156
  -7.750  -0.6865   0.02094   0.01540  -0.0375   0.9964   0.0160
  -7.500  -0.6586   0.01808   0.01230  -0.0387   0.9944   0.0170
  -7.250  -0.6267   0.01712   0.01130  -0.0401   0.9918   0.0180
  -7.000  -0.5939   0.01628   0.01037  -0.0415   0.9888   0.0190
  -6.750  -0.5592   0.01563   0.00964  -0.0432   0.9862   0.0204
  -6.500  -0.5250   0.01453   0.00842  -0.0450   0.9841   0.0220
  -6.250  -0.4930   0.01376   0.00764  -0.0462   0.9808   0.0238
  -6.000  -0.4606   0.01319   0.00702  -0.0473   0.9767   0.0256
  -5.750  -0.4251   0.01269   0.00646  -0.0490   0.9738   0.0276
  -5.500  -0.3889   0.01196   0.00571  -0.0510   0.9716   0.0316
  -5.250  -0.3563   0.01155   0.00525  -0.0521   0.9673   0.0351
  -5.000  -0.3240   0.01087   0.00466  -0.0531   0.9626   0.0501
  -4.750  -0.2878   0.01032   0.00425  -0.0551   0.9598   0.0799
  -4.500  -0.2498   0.00989   0.00391  -0.0574   0.9578   0.1058
  -4.250  -0.2184   0.00949   0.00362  -0.0582   0.9523   0.1339
  -4.000  -0.1849   0.00906   0.00334  -0.0595   0.9475   0.1723
  -3.750  -0.1493   0.00859   0.00305  -0.0613   0.9439   0.2219
  -3.500  -0.1200   0.00816   0.00282  -0.0617   0.9362   0.2772
  -3.250  -0.0874   0.00764   0.00257  -0.0629   0.9299   0.3534
  -3.000  -0.0591   0.00717   0.00237  -0.0631   0.9203   0.4359
  -2.750  -0.0288   0.00676   0.00220  -0.0637   0.9117   0.5116
  -2.500  -0.0007   0.00649   0.00212  -0.0636   0.9006   0.5809
  -2.250   0.0269   0.00637   0.00208  -0.0633   0.8885   0.6294
  -2.000   0.0547   0.00631   0.00205  -0.0630   0.8762   0.6625
  -1.750   0.0825   0.00629   0.00201  -0.0627   0.8635   0.6869
  -1.500   0.1101   0.00629   0.00197  -0.0624   0.8503   0.7051
  -1.250   0.1373   0.00630   0.00195  -0.0620   0.8366   0.7209
  -1.000   0.1644   0.00632   0.00192  -0.0616   0.8225   0.7352
  -0.750   0.1913   0.00635   0.00191  -0.0611   0.8081   0.7483
  -0.500   0.2179   0.00638   0.00191  -0.0606   0.7933   0.7603
  -0.250   0.2444   0.00641   0.00191  -0.0601   0.7783   0.7714
   0.000   0.2710   0.00645   0.00191  -0.0596   0.7630   0.7823
   0.250   0.2975   0.00651   0.00191  -0.0591   0.7472   0.7932
   0.500   0.3236   0.00655   0.00193  -0.0586   0.7312   0.8031
   0.750   0.3498   0.00660   0.00195  -0.0580   0.7145   0.8130
   1.250   0.4014   0.00673   0.00201  -0.0568   0.6798   0.8338
   1.750   0.4522   0.00688   0.00209  -0.0554   0.6428   0.8554
   2.000   0.4772   0.00696   0.00214  -0.0547   0.6232   0.8668
   2.250   0.5015   0.00706   0.00220  -0.0538   0.6032   0.8781
   2.500   0.5256   0.00714   0.00227  -0.0528   0.5827   0.8906
   2.750   0.5490   0.00724   0.00234  -0.0517   0.5615   0.9044
   3.000   0.5720   0.00735   0.00241  -0.0505   0.5403   0.9191
   3.250   0.5952   0.00745   0.00249  -0.0494   0.5180   0.9358
   3.500   0.6213   0.00760   0.00259  -0.0489   0.4952   0.9544
   4.250   0.7252   0.00828   0.00299  -0.0539   0.4124   1.0000
   4.500   0.7482   0.00852   0.00314  -0.0531   0.3909   1.0000
   4.750   0.7720   0.00879   0.00331  -0.0525   0.3666   1.0000
   5.000   0.7962   0.00906   0.00351  -0.0519   0.3430   1.0000
   5.250   0.8203   0.00937   0.00372  -0.0513   0.3208   1.0000
   5.500   0.8445   0.00968   0.00394  -0.0508   0.2962   1.0000
   5.750   0.8680   0.01005   0.00420  -0.0501   0.2684   1.0000
   6.000   0.8914   0.01043   0.00448  -0.0494   0.2422   1.0000
   6.250   0.9146   0.01083   0.00477  -0.0488   0.2182   1.0000
   6.500   0.9380   0.01123   0.00508  -0.0481   0.1949   1.0000
   6.750   0.9610   0.01166   0.00542  -0.0474   0.1740   1.0000
   7.000   0.9838   0.01210   0.00579  -0.0467   0.1535   1.0000
   7.250   1.0059   0.01259   0.00619  -0.0458   0.1341   1.0000
   7.500   1.0285   0.01304   0.00659  -0.0451   0.1178   1.0000
   7.750   1.0506   0.01353   0.00703  -0.0442   0.1027   1.0000
   8.000   1.0722   0.01404   0.00749  -0.0433   0.0891   1.0000
   8.250   1.0934   0.01458   0.00800  -0.0424   0.0772   1.0000
   8.500   1.1138   0.01516   0.00855  -0.0413   0.0664   1.0000
   8.750   1.1331   0.01582   0.00916  -0.0401   0.0564   1.0000
   9.000   1.1532   0.01639   0.00971  -0.0390   0.0487   1.0000
   9.250   1.1730   0.01695   0.01030  -0.0378   0.0429   1.0000
   9.500   1.1905   0.01767   0.01101  -0.0363   0.0378   1.0000
   9.750   1.2089   0.01827   0.01167  -0.0350   0.0347   1.0000
  10.000   1.2269   0.01886   0.01231  -0.0336   0.0318   1.0000
  10.250   1.2369   0.01989   0.01335  -0.0310   0.0284   1.0000
  10.500   1.2543   0.02035   0.01390  -0.0294   0.0267   1.0000
  10.750   1.2686   0.02099   0.01458  -0.0275   0.0244   1.0000
  11.000   1.2725   0.02224   0.01587  -0.0242   0.0218   1.0000
  11.250   1.2888   0.02277   0.01650  -0.0227   0.0201   1.0000
  11.500   1.3011   0.02355   0.01733  -0.0208   0.0183   1.0000
  11.750   1.2998   0.02519   0.01903  -0.0175   0.0165   1.0000
  12.000   1.3125   0.02599   0.01993  -0.0159   0.0151   1.0000
  12.250   1.3208   0.02710   0.02112  -0.0139   0.0141   1.0000
  12.500   1.3254   0.02851   0.02259  -0.0119   0.0131   1.0000
  12.750   1.3166   0.03102   0.02520  -0.0092   0.0123   1.0000
  13.000   1.3219   0.03261   0.02691  -0.0078   0.0118   1.0000
  13.250   1.3254   0.03442   0.02885  -0.0065   0.0113   1.0000
  13.500   1.3267   0.03654   0.03108  -0.0055   0.0109   1.0000
  13.750   1.3277   0.03880   0.03346  -0.0047   0.0105   1.0000
  14.000   1.3269   0.04139   0.03615  -0.0043   0.0101   1.0000
  14.250   1.3248   0.04426   0.03913  -0.0042   0.0099   1.0000
  14.500   1.3190   0.04774   0.04272  -0.0044   0.0097   1.0000
  14.750   1.3105   0.05174   0.04684  -0.0051   0.0095   1.0000
  15.000   1.2943   0.05696   0.05220  -0.0063   0.0092   1.0000
  15.250   1.2849   0.06159   0.05698  -0.0078   0.0090   1.0000
  15.500   1.2801   0.06583   0.06136  -0.0094   0.0089   1.0000
  15.750   1.2721   0.07070   0.06637  -0.0114   0.0088   1.0000
  16.000   1.2640   0.07577   0.07159  -0.0137   0.0087   1.0000
  16.250   1.2543   0.08132   0.07728  -0.0164   0.0086   1.0000
  16.500   1.2445   0.08705   0.08315  -0.0192   0.0086   1.0000
  16.750   1.2345   0.09311   0.08935  -0.0224   0.0083   1.0000
  17.000   1.2212   0.09974   0.09613  -0.0258   0.0084   1.0000
  17.250   1.2112   0.10616   0.10267  -0.0295   0.0082   1.0000
  17.500   1.1958   0.11358   0.11025  -0.0335   0.0083   1.0000
  17.750   1.1852   0.12043   0.11722  -0.0375   0.0081   1.0000
  18.000   1.1730   0.12765   0.12457  -0.0418   0.0081   1.0000
  18.250   1.1585   0.13553   0.13259  -0.0464   0.0081   1.0000
  18.500   1.1439   0.14369   0.14088  -0.0513   0.0081   1.0000
  18.750   1.1289   0.15218   0.14952  -0.0566   0.0081   1.0000
  19.000   1.1132   0.16114   0.15861  -0.0622   0.0081   1.0000
  19.250   1.0888   0.17288   0.17052  -0.0694   0.0083   1.0000
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