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RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RG 8 AIRFOIL (rg8-il)
Reynolds number: 500,000
Max Cl/Cd: 96.49 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg8-il-500000.txt
Download as CSV file: xf-rg8-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3697   0.10206   0.09986  -0.0334   1.0000   0.0278
 -10.750  -0.3772   0.09656   0.09438  -0.0353   1.0000   0.0294
  -8.250  -0.6952   0.03227   0.02824  -0.0509   0.9986   0.0176
  -8.000  -0.6660   0.02972   0.02536  -0.0531   0.9962   0.0174
  -7.750  -0.6367   0.02666   0.02194  -0.0554   0.9943   0.0174
  -7.500  -0.6100   0.02375   0.01868  -0.0566   0.9917   0.0174
  -7.250  -0.5826   0.02060   0.01517  -0.0579   0.9893   0.0177
  -7.000  -0.5526   0.01842   0.01280  -0.0592   0.9873   0.0183
  -6.750  -0.5188   0.01745   0.01176  -0.0610   0.9855   0.0194
  -6.500  -0.4838   0.01647   0.01069  -0.0629   0.9841   0.0201
  -6.250  -0.4539   0.01556   0.00969  -0.0636   0.9808   0.0208
  -6.000  -0.4220   0.01474   0.00878  -0.0647   0.9776   0.0215
  -5.750  -0.3876   0.01405   0.00800  -0.0663   0.9752   0.0224
  -5.500  -0.3516   0.01346   0.00734  -0.0682   0.9733   0.0231
  -5.250  -0.3153   0.01253   0.00636  -0.0704   0.9718   0.0257
  -5.000  -0.2867   0.01204   0.00583  -0.0706   0.9669   0.0278
  -4.750  -0.2526   0.01162   0.00534  -0.0720   0.9636   0.0305
  -4.500  -0.2165   0.01091   0.00472  -0.0739   0.9613   0.0498
  -4.250  -0.1793   0.01029   0.00434  -0.0762   0.9596   0.0996
  -4.000  -0.1484   0.00986   0.00405  -0.0770   0.9551   0.1361
  -3.750  -0.1156   0.00943   0.00377  -0.0782   0.9509   0.1788
  -3.500  -0.0792   0.00893   0.00349  -0.0803   0.9483   0.2367
  -3.250  -0.0419   0.00827   0.00318  -0.0826   0.9464   0.3335
  -3.000  -0.0095   0.00764   0.00297  -0.0839   0.9425   0.4486
  -2.750   0.0227   0.00733   0.00284  -0.0847   0.9373   0.5170
  -2.500   0.0605   0.00713   0.00269  -0.0867   0.9341   0.5517
  -2.250   0.0995   0.00695   0.00254  -0.0889   0.9313   0.5788
  -2.000   0.1288   0.00684   0.00244  -0.0890   0.9224   0.5979
  -1.750   0.1672   0.00671   0.00229  -0.0910   0.9174   0.6136
  -1.500   0.1979   0.00662   0.00220  -0.0914   0.9070   0.6257
  -1.250   0.2314   0.00655   0.00211  -0.0924   0.8972   0.6381
  -1.000   0.2648   0.00650   0.00201  -0.0934   0.8862   0.6502
  -0.750   0.2961   0.00647   0.00196  -0.0939   0.8731   0.6612
  -0.500   0.3256   0.00645   0.00192  -0.0940   0.8582   0.6710
  -0.250   0.3541   0.00647   0.00189  -0.0939   0.8421   0.6811
   0.000   0.3819   0.00650   0.00188  -0.0937   0.8248   0.6913
   0.250   0.4092   0.00653   0.00188  -0.0934   0.8068   0.7011
   0.500   0.4362   0.00659   0.00189  -0.0930   0.7883   0.7112
   0.750   0.4627   0.00666   0.00191  -0.0926   0.7689   0.7214
   1.000   0.4886   0.00672   0.00194  -0.0920   0.7485   0.7313
   1.250   0.5144   0.00682   0.00198  -0.0914   0.7280   0.7415
   1.500   0.5401   0.00691   0.00203  -0.0908   0.7063   0.7518
   1.750   0.5653   0.00701   0.00209  -0.0901   0.6845   0.7613
   2.000   0.5906   0.00712   0.00215  -0.0894   0.6620   0.7718
   2.500   0.6401   0.00737   0.00233  -0.0880   0.6150   0.7954
   2.750   0.6644   0.00751   0.00243  -0.0871   0.5912   0.8086
   3.000   0.6884   0.00765   0.00254  -0.0862   0.5669   0.8234
   3.250   0.7122   0.00779   0.00267  -0.0853   0.5421   0.8406
   3.500   0.7347   0.00794   0.00280  -0.0841   0.5171   0.8603
   3.750   0.7562   0.00809   0.00294  -0.0826   0.4919   0.8850
   4.000   0.7750   0.00819   0.00306  -0.0805   0.4666   0.9203
   4.250   0.8038   0.00833   0.00317  -0.0807   0.4387   1.0000
   4.500   0.8293   0.00863   0.00335  -0.0804   0.4117   1.0000
   4.750   0.8543   0.00894   0.00355  -0.0800   0.3849   1.0000
   5.000   0.8788   0.00927   0.00378  -0.0794   0.3561   1.0000
   5.250   0.9030   0.00963   0.00402  -0.0789   0.3265   1.0000
   5.500   0.9271   0.01001   0.00428  -0.0783   0.2985   1.0000
   6.000   0.9746   0.01080   0.00487  -0.0771   0.2442   1.0000
   6.250   0.9974   0.01128   0.00521  -0.0763   0.2141   1.0000
   6.500   1.0199   0.01179   0.00558  -0.0755   0.1824   1.0000
   6.750   1.0417   0.01235   0.00598  -0.0746   0.1508   1.0000
   7.000   1.0636   0.01291   0.00642  -0.0737   0.1253   1.0000
   7.250   1.0849   0.01350   0.00688  -0.0728   0.1022   1.0000
   7.500   1.1065   0.01406   0.00735  -0.0719   0.0823   1.0000
   7.750   1.1270   0.01470   0.00789  -0.0708   0.0646   1.0000
   8.000   1.1480   0.01527   0.00842  -0.0697   0.0510   1.0000
   8.250   1.1673   0.01600   0.00906  -0.0684   0.0357   1.0000
   8.500   1.1836   0.01700   0.00997  -0.0666   0.0212   1.0000
   8.750   1.2007   0.01788   0.01089  -0.0648   0.0166   1.0000
   9.000   1.2169   0.01878   0.01183  -0.0630   0.0144   1.0000
   9.250   1.2330   0.01963   0.01276  -0.0612   0.0131   1.0000
   9.500   1.2495   0.02035   0.01355  -0.0594   0.0121   1.0000
   9.750   1.2630   0.02116   0.01443  -0.0571   0.0115   1.0000
  10.000   1.2736   0.02212   0.01547  -0.0545   0.0109   1.0000
  10.250   1.2786   0.02343   0.01688  -0.0511   0.0104   1.0000
  10.500   1.2801   0.02503   0.01860  -0.0474   0.0101   1.0000
  10.750   1.2902   0.02606   0.01973  -0.0451   0.0099   1.0000
  11.000   1.2974   0.02733   0.02110  -0.0425   0.0097   1.0000
  11.250   1.3046   0.02863   0.02252  -0.0401   0.0095   1.0000
  11.500   1.3096   0.03016   0.02417  -0.0377   0.0093   1.0000
  11.750   1.3141   0.03179   0.02593  -0.0354   0.0091   1.0000
  12.000   1.3175   0.03361   0.02787  -0.0333   0.0090   1.0000
  12.250   1.3205   0.03552   0.02991  -0.0314   0.0088   1.0000
  12.500   1.3223   0.03767   0.03221  -0.0296   0.0087   1.0000
  12.750   1.3233   0.03997   0.03464  -0.0281   0.0085   1.0000
  13.000   1.3231   0.04251   0.03734  -0.0269   0.0084   1.0000
  13.250   1.3219   0.04527   0.04024  -0.0259   0.0083   1.0000
  13.500   1.3190   0.04836   0.04350  -0.0253   0.0083   1.0000
  13.750   1.3148   0.05174   0.04704  -0.0249   0.0082   1.0000
  14.000   1.3090   0.05550   0.05098  -0.0250   0.0082   1.0000
  14.250   1.3017   0.05960   0.05526  -0.0256   0.0082   1.0000
  14.500   1.2935   0.06402   0.05984  -0.0266   0.0081   1.0000
  14.750   1.2824   0.06915   0.06516  -0.0282   0.0081   1.0000
  15.000   1.2728   0.07426   0.07043  -0.0303   0.0081   1.0000
  15.250   1.2606   0.08012   0.07646  -0.0329   0.0080   1.0000
  15.500   1.2470   0.08655   0.08306  -0.0362   0.0080   1.0000
  15.750   1.2313   0.09373   0.09044  -0.0401   0.0081   1.0000
  16.000   1.2104   0.10243   0.09935  -0.0450   0.0082   1.0000
  16.250   1.1932   0.11072   0.10782  -0.0500   0.0082   1.0000
  16.500   1.1598   0.12349   0.12087  -0.0581   0.0084   1.0000
  16.750   1.1295   0.13638   0.13399  -0.0665   0.0087   1.0000
  17.000   1.0929   0.15198   0.14981  -0.0765   0.0090   1.0000
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