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RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RG-15 8.9% (rg15-il)
Reynolds number: 50,000
Max Cl/Cd: 36.58 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg15-il-50000-n5.txt
Download as CSV file: xf-rg15-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-15 8.9%                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4831   0.09329   0.08622  -0.0290   1.0000   0.0439
  -8.750  -0.4854   0.08900   0.08201  -0.0307   1.0000   0.0433
  -8.500  -0.4894   0.08463   0.07773  -0.0328   1.0000   0.0427
  -8.250  -0.4963   0.08000   0.07319  -0.0352   1.0000   0.0420
  -8.000  -0.5051   0.07515   0.06842  -0.0380   1.0000   0.0415
  -7.750  -0.5124   0.07037   0.06363  -0.0400   1.0000   0.0409
  -7.500  -0.5187   0.06566   0.05887  -0.0415   1.0000   0.0406
  -7.250  -0.5223   0.06117   0.05426  -0.0424   1.0000   0.0402
  -7.000  -0.5229   0.05680   0.04968  -0.0428   1.0000   0.0408
  -6.750  -0.5196   0.05269   0.04530  -0.0429   1.0000   0.0416
  -6.500  -0.5131   0.04864   0.04087  -0.0427   1.0000   0.0431
  -6.250  -0.5031   0.04473   0.03647  -0.0422   1.0000   0.0445
  -6.000  -0.4896   0.04103   0.03222  -0.0415   1.0000   0.0454
  -5.750  -0.4729   0.03763   0.02822  -0.0406   1.0000   0.0462
  -5.500  -0.4546   0.03457   0.02476  -0.0396   1.0000   0.0474
  -5.250  -0.4355   0.03241   0.02243  -0.0388   1.0000   0.0505
  -5.000  -0.4147   0.03059   0.02028  -0.0378   1.0000   0.0563
  -4.750  -0.3919   0.02852   0.01771  -0.0365   1.0000   0.0599
  -4.500  -0.3707   0.02680   0.01594  -0.0353   1.0000   0.0639
  -4.250  -0.3486   0.02542   0.01433  -0.0339   1.0000   0.0702
  -4.000  -0.3276   0.02427   0.01314  -0.0327   1.0000   0.0816
  -3.750  -0.3062   0.02307   0.01187  -0.0314   1.0000   0.0943
  -3.500  -0.2844   0.02192   0.01077  -0.0306   1.0000   0.1189
  -3.250  -0.2631   0.02067   0.00982  -0.0300   1.0000   0.1732
  -3.000  -0.2425   0.01914   0.00900  -0.0296   1.0000   0.3001
  -2.750  -0.2276   0.01782   0.00884  -0.0272   1.0000   0.5127
  -2.500  -0.2175   0.01752   0.00905  -0.0223   1.0000   0.6858
  -2.250  -0.2066   0.01743   0.00905  -0.0177   1.0000   0.7786
  -2.000  -0.1925   0.01734   0.00896  -0.0138   1.0000   0.8539
  -1.750  -0.1509   0.01726   0.00870  -0.0154   1.0000   0.9413
  -1.500  -0.1065   0.01715   0.00822  -0.0194   1.0000   1.0000
  -1.250  -0.0923   0.01715   0.00799  -0.0183   1.0000   1.0000
  -1.000  -0.0749   0.01724   0.00784  -0.0175   1.0000   1.0000
  -0.750  -0.0427   0.01749   0.00786  -0.0195   0.9943   1.0000
  -0.500   0.0006   0.01782   0.00792  -0.0234   0.9832   1.0000
  -0.250   0.0422   0.01810   0.00800  -0.0270   0.9712   1.0000
   0.000   0.0828   0.01834   0.00807  -0.0301   0.9587   1.0000
   0.250   0.1228   0.01854   0.00815  -0.0331   0.9457   1.0000
   0.500   0.1625   0.01872   0.00823  -0.0358   0.9324   1.0000
   0.750   0.2020   0.01887   0.00831  -0.0384   0.9187   1.0000
   1.000   0.2415   0.01897   0.00838  -0.0409   0.9048   1.0000
   1.250   0.2811   0.01904   0.00844  -0.0433   0.8907   1.0000
   1.500   0.3210   0.01908   0.00849  -0.0455   0.8763   1.0000
   1.750   0.3593   0.01909   0.00853  -0.0473   0.8612   1.0000
   2.000   0.3964   0.01907   0.00855  -0.0487   0.8452   1.0000
   2.250   0.4283   0.01910   0.00863  -0.0492   0.8262   1.0000
   2.500   0.4624   0.01909   0.00871  -0.0499   0.8076   1.0000
   2.750   0.4964   0.01906   0.00874  -0.0504   0.7885   1.0000
   3.000   0.5263   0.01910   0.00885  -0.0503   0.7662   1.0000
   3.250   0.5568   0.01913   0.00894  -0.0501   0.7436   1.0000
   3.500   0.5874   0.01917   0.00909  -0.0499   0.7200   1.0000
   3.750   0.6149   0.01929   0.00927  -0.0492   0.6935   1.0000
   4.000   0.6420   0.01945   0.00947  -0.0484   0.6658   1.0000
   4.250   0.6684   0.01964   0.00969  -0.0474   0.6367   1.0000
   4.500   0.6936   0.01989   0.01003  -0.0463   0.6056   1.0000
   4.750   0.7176   0.02020   0.01037  -0.0451   0.5723   1.0000
   5.000   0.7413   0.02055   0.01072  -0.0438   0.5383   1.0000
   5.250   0.7635   0.02098   0.01116  -0.0424   0.5017   1.0000
   5.500   0.7852   0.02147   0.01162  -0.0410   0.4640   1.0000
   5.750   0.8058   0.02203   0.01220  -0.0394   0.4247   1.0000
   6.000   0.8253   0.02269   0.01282  -0.0379   0.3838   1.0000
   6.250   0.8440   0.02345   0.01352  -0.0363   0.3418   1.0000
   6.500   0.8618   0.02433   0.01432  -0.0347   0.2993   1.0000
   6.750   0.8789   0.02536   0.01526  -0.0332   0.2581   1.0000
   7.000   0.8955   0.02653   0.01634  -0.0317   0.2183   1.0000
   7.250   0.9119   0.02785   0.01759  -0.0303   0.1829   1.0000
   7.500   0.9277   0.02931   0.01906  -0.0289   0.1531   1.0000
   7.750   0.9436   0.03093   0.02066  -0.0275   0.1294   1.0000
   8.000   0.9585   0.03263   0.02233  -0.0261   0.1097   1.0000
   8.250   0.9743   0.03451   0.02423  -0.0247   0.0941   1.0000
   8.500   0.9893   0.03642   0.02628  -0.0233   0.0797   1.0000
   8.750   1.0039   0.03858   0.02848  -0.0219   0.0690   1.0000
   9.000   1.0166   0.04062   0.03073  -0.0204   0.0589   1.0000
   9.250   1.0323   0.04345   0.03391  -0.0190   0.0521   1.0000
   9.500   1.0417   0.04563   0.03611  -0.0176   0.0465   1.0000
   9.750   1.0505   0.04866   0.03969  -0.0159   0.0421   1.0000
  10.000   1.0570   0.05198   0.04339  -0.0143   0.0397   1.0000
  10.250   1.0592   0.05518   0.04689  -0.0125   0.0381   1.0000
  10.500   1.0575   0.05821   0.05011  -0.0107   0.0367   1.0000
  11.000   1.0420   0.06544   0.05774  -0.0080   0.0350   1.0000
  11.250   1.0260   0.06975   0.06236  -0.0077   0.0347   1.0000
  11.500   1.0097   0.07456   0.06742  -0.0086   0.0347   1.0000
  11.750   0.9921   0.07998   0.07305  -0.0106   0.0348   1.0000
  12.000   0.9735   0.08623   0.07947  -0.0139   0.0350   1.0000
  12.250   0.9559   0.09305   0.08642  -0.0179   0.0352   1.0000
  12.500   0.8955   0.11247   0.10611  -0.0327   0.0397   1.0000
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