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

RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RG-15 8.9% (rg15-il)
Reynolds number: 200,000
Max Cl/Cd: 63.25 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg15-il-200000-n5.txt
Download as CSV file: xf-rg15-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4977   0.08502   0.08145  -0.0286   1.0000   0.0123
  -9.000  -0.5164   0.07610   0.07265  -0.0333   1.0000   0.0116
  -8.500  -0.5443   0.06145   0.05806  -0.0428   1.0000   0.0110
  -8.250  -0.5596   0.05578   0.05230  -0.0448   1.0000   0.0109
  -8.000  -0.5724   0.05027   0.04661  -0.0454   1.0000   0.0108
  -7.750  -0.5805   0.04519   0.04129  -0.0450   1.0000   0.0107
  -7.500  -0.5844   0.04013   0.03585  -0.0440   1.0000   0.0107
  -7.250  -0.5818   0.03580   0.03110  -0.0428   1.0000   0.0107
  -7.000  -0.5747   0.03170   0.02646  -0.0413   1.0000   0.0109
  -6.750  -0.5621   0.02866   0.02292  -0.0399   1.0000   0.0110
  -6.500  -0.5485   0.02536   0.01919  -0.0386   1.0000   0.0114
  -6.250  -0.5308   0.02349   0.01705  -0.0375   1.0000   0.0120
  -6.000  -0.5114   0.02208   0.01541  -0.0365   1.0000   0.0126
  -5.750  -0.4910   0.02094   0.01408  -0.0355   1.0000   0.0138
  -5.500  -0.4590   0.01997   0.01285  -0.0366   0.9974   0.0160
  -5.250  -0.4259   0.01844   0.01106  -0.0379   0.9946   0.0171
  -5.000  -0.3949   0.01691   0.00943  -0.0390   0.9912   0.0191
  -4.750  -0.3618   0.01605   0.00844  -0.0404   0.9873   0.0217
  -4.500  -0.3271   0.01539   0.00766  -0.0420   0.9838   0.0253
  -4.250  -0.2956   0.01450   0.00672  -0.0431   0.9791   0.0286
  -4.000  -0.2624   0.01400   0.00615  -0.0443   0.9742   0.0338
  -3.750  -0.2271   0.01334   0.00545  -0.0461   0.9704   0.0406
  -3.500  -0.1964   0.01281   0.00491  -0.0468   0.9639   0.0547
  -3.250  -0.1622   0.01226   0.00447  -0.0483   0.9589   0.0903
  -3.000  -0.1299   0.01171   0.00414  -0.0496   0.9530   0.1480
  -2.750  -0.0978   0.01106   0.00386  -0.0509   0.9467   0.2388
  -2.500  -0.0649   0.01023   0.00361  -0.0526   0.9416   0.3851
  -2.250  -0.0356   0.00961   0.00344  -0.0530   0.9336   0.5098
  -2.000  -0.0043   0.00923   0.00343  -0.0535   0.9268   0.6263
  -1.750   0.0267   0.00906   0.00336  -0.0538   0.9181   0.6848
  -1.500   0.0577   0.00894   0.00328  -0.0541   0.9085   0.7219
  -1.250   0.0904   0.00883   0.00316  -0.0547   0.8992   0.7506
  -1.000   0.1220   0.00873   0.00306  -0.0551   0.8883   0.7754
  -0.750   0.1521   0.00865   0.00298  -0.0551   0.8755   0.7968
  -0.250   0.2110   0.00853   0.00282  -0.0549   0.8466   0.8345
   0.000   0.2385   0.00849   0.00276  -0.0544   0.8302   0.8527
   0.250   0.2652   0.00847   0.00271  -0.0537   0.8123   0.8711
   0.500   0.2917   0.00846   0.00266  -0.0530   0.7936   0.8890
   0.750   0.3191   0.00846   0.00261  -0.0524   0.7742   0.9071
   1.000   0.3478   0.00849   0.00258  -0.0523   0.7531   0.9248
   1.250   0.3788   0.00854   0.00256  -0.0527   0.7313   0.9411
   1.500   0.4118   0.00861   0.00254  -0.0536   0.7079   0.9565
   1.750   0.4465   0.00870   0.00254  -0.0550   0.6829   0.9722
   2.000   0.4812   0.00881   0.00257  -0.0565   0.6567   0.9910
   2.250   0.5085   0.00897   0.00262  -0.0565   0.6308   1.0000
   2.500   0.5322   0.00917   0.00270  -0.0557   0.6046   1.0000
   2.750   0.5562   0.00938   0.00280  -0.0550   0.5776   1.0000
   3.000   0.5803   0.00961   0.00292  -0.0543   0.5493   1.0000
   3.250   0.6045   0.00986   0.00309  -0.0536   0.5203   1.0000
   3.500   0.6287   0.01013   0.00325  -0.0529   0.4905   1.0000
   3.750   0.6528   0.01042   0.00344  -0.0522   0.4599   1.0000
   4.000   0.6767   0.01074   0.00365  -0.0515   0.4285   1.0000
   4.250   0.7004   0.01109   0.00392  -0.0508   0.3958   1.0000
   4.500   0.7242   0.01145   0.00418  -0.0501   0.3628   1.0000
   4.750   0.7478   0.01184   0.00447  -0.0495   0.3302   1.0000
   5.000   0.7713   0.01227   0.00480  -0.0488   0.2971   1.0000
   5.250   0.7945   0.01273   0.00515  -0.0481   0.2621   1.0000
   5.500   0.8173   0.01326   0.00558  -0.0474   0.2252   1.0000
   5.750   0.8399   0.01382   0.00601  -0.0467   0.1910   1.0000
   6.000   0.8626   0.01439   0.00649  -0.0460   0.1612   1.0000
   6.250   0.8851   0.01500   0.00701  -0.0453   0.1332   1.0000
   6.500   0.9074   0.01564   0.00757  -0.0446   0.1094   1.0000
   6.750   0.9298   0.01626   0.00818  -0.0438   0.0900   1.0000
   7.000   0.9513   0.01698   0.00888  -0.0430   0.0719   1.0000
   7.250   0.9725   0.01772   0.00956  -0.0422   0.0536   1.0000
   7.500   0.9933   0.01851   0.01027  -0.0413   0.0381   1.0000
   7.750   1.0141   0.01928   0.01107  -0.0404   0.0290   1.0000
   8.000   1.0338   0.02021   0.01206  -0.0392   0.0217   1.0000
   8.250   1.0513   0.02137   0.01327  -0.0378   0.0168   1.0000
   8.500   1.0694   0.02242   0.01447  -0.0364   0.0144   1.0000
   8.750   1.0863   0.02354   0.01572  -0.0350   0.0126   1.0000
   9.000   1.1018   0.02476   0.01707  -0.0334   0.0113   1.0000
   9.250   1.1178   0.02589   0.01836  -0.0319   0.0101   1.0000
   9.500   1.1318   0.02718   0.01980  -0.0302   0.0095   1.0000
   9.750   1.1443   0.02854   0.02131  -0.0284   0.0090   1.0000
  10.000   1.1548   0.03005   0.02297  -0.0264   0.0086   1.0000
  10.250   1.1615   0.03169   0.02475  -0.0239   0.0083   1.0000
  10.500   1.1644   0.03371   0.02694  -0.0211   0.0080   1.0000
  10.750   1.1663   0.03594   0.02934  -0.0185   0.0078   1.0000
  11.000   1.1693   0.03803   0.03166  -0.0162   0.0077   1.0000
  11.250   1.1698   0.04037   0.03425  -0.0140   0.0076   1.0000
  11.750   1.1639   0.04583   0.04023  -0.0107   0.0075   1.0000
  12.000   1.1566   0.04919   0.04385  -0.0097   0.0074   1.0000
  12.250   1.1470   0.05302   0.04794  -0.0095   0.0073   1.0000
  12.500   1.1353   0.05739   0.05255  -0.0101   0.0073   1.0000
  12.750   1.1225   0.06227   0.05767  -0.0116   0.0073   1.0000
  13.000   1.1078   0.06793   0.06355  -0.0142   0.0073   1.0000
  13.250   1.0915   0.07438   0.07021  -0.0177   0.0073   1.0000
  13.500   1.0754   0.08135   0.07737  -0.0219   0.0073   1.0000
  13.750   1.0576   0.08924   0.08544  -0.0270   0.0074   1.0000
  14.000   1.0380   0.09823   0.09459  -0.0328   0.0074   1.0000
  14.250   1.0186   0.10776   0.10427  -0.0390   0.0075   1.0000
  14.500   1.0005   0.11750   0.11409  -0.0450   0.0076   1.0000
  14.750   0.9790   0.12882   0.12550  -0.0518   0.0077   1.0000
  15.000   0.9567   0.14106   0.13780  -0.0587   0.0078   1.0000
<< Back to RG-15 8.9% (rg15-il)

Polar data table (+)

Polar graphs


<< Back to RG-15 8.9% (rg15-il)