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

RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: RG 14 9.5% AIRFOIL (rg1495-il)
Reynolds number: 1,000,000
Max Cl/Cd: 84.98 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg1495-il-1000000-n5.txt
Download as CSV file: xf-rg1495-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9.5% AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -1.0695   0.04994   0.04743  -0.0553   1.0000   0.0040
 -14.750  -1.0985   0.04104   0.03831  -0.0632   1.0000   0.0040
 -14.500  -1.1132   0.03688   0.03398  -0.0647   1.0000   0.0041
 -14.250  -1.1212   0.03421   0.03116  -0.0641   1.0000   0.0041
 -14.000  -1.1312   0.03186   0.02865  -0.0622   1.0000   0.0041
 -13.750  -1.1383   0.03023   0.02689  -0.0589   1.0000   0.0041
 -13.500  -1.1390   0.02886   0.02540  -0.0558   1.0000   0.0042
 -13.250  -1.1326   0.02761   0.02403  -0.0536   1.0000   0.0042
 -13.000  -1.1262   0.02624   0.02252  -0.0513   1.0000   0.0043
 -12.750  -1.1216   0.02457   0.02068  -0.0488   1.0000   0.0045
 -12.500  -1.1106   0.02342   0.01940  -0.0468   1.0000   0.0046
 -12.250  -1.0974   0.02240   0.01828  -0.0450   1.0000   0.0049
 -12.000  -1.0829   0.02149   0.01727  -0.0433   1.0000   0.0050
 -11.750  -1.0672   0.02067   0.01636  -0.0417   1.0000   0.0051
 -11.500  -1.0505   0.01992   0.01553  -0.0401   1.0000   0.0053
 -11.250  -1.0335   0.01918   0.01469  -0.0386   1.0000   0.0055
 -11.000  -1.0158   0.01852   0.01394  -0.0371   1.0000   0.0057
 -10.750  -0.9976   0.01788   0.01321  -0.0356   1.0000   0.0059
 -10.500  -0.9792   0.01724   0.01249  -0.0342   1.0000   0.0061
 -10.250  -0.9600   0.01667   0.01184  -0.0328   1.0000   0.0063
 -10.000  -0.9311   0.01604   0.01112  -0.0335   0.9989   0.0065
  -9.750  -0.9022   0.01533   0.01034  -0.0343   0.9976   0.0070
  -9.500  -0.8721   0.01483   0.00979  -0.0351   0.9963   0.0075
  -9.250  -0.8414   0.01440   0.00932  -0.0361   0.9951   0.0079
  -9.000  -0.8104   0.01400   0.00888  -0.0371   0.9939   0.0085
  -8.750  -0.7819   0.01360   0.00843  -0.0374   0.9920   0.0090
  -8.500  -0.7524   0.01326   0.00803  -0.0380   0.9901   0.0094
  -8.250  -0.7227   0.01274   0.00746  -0.0387   0.9880   0.0102
  -8.000  -0.6916   0.01241   0.00712  -0.0396   0.9863   0.0108
  -7.750  -0.6597   0.01207   0.00676  -0.0407   0.9848   0.0115
  -7.250  -0.6000   0.01144   0.00605  -0.0418   0.9796   0.0127
  -7.000  -0.5702   0.01121   0.00578  -0.0423   0.9761   0.0131
  -6.750  -0.5395   0.01072   0.00524  -0.0431   0.9732   0.0139
  -6.250  -0.4802   0.01003   0.00452  -0.0441   0.9650   0.0155
  -6.000  -0.4497   0.00975   0.00421  -0.0447   0.9602   0.0163
  -5.750  -0.4173   0.00948   0.00391  -0.0458   0.9560   0.0171
  -5.500  -0.3877   0.00923   0.00362  -0.0461   0.9486   0.0176
  -5.250  -0.3554   0.00899   0.00335  -0.0471   0.9417   0.0181
  -5.000  -0.3254   0.00868   0.00299  -0.0475   0.9311   0.0194
  -4.750  -0.2963   0.00845   0.00271  -0.0478   0.9189   0.0206
  -4.500  -0.2682   0.00826   0.00248  -0.0478   0.9052   0.0220
  -4.250  -0.2410   0.00811   0.00228  -0.0475   0.8907   0.0235
  -4.000  -0.2142   0.00797   0.00210  -0.0472   0.8759   0.0271
  -3.750  -0.1880   0.00779   0.00191  -0.0468   0.8609   0.0359
  -3.500  -0.1619   0.00763   0.00176  -0.0464   0.8455   0.0503
  -3.250  -0.1357   0.00751   0.00162  -0.0460   0.8294   0.0617
  -3.000  -0.1096   0.00740   0.00150  -0.0456   0.8123   0.0758
  -2.750  -0.0834   0.00730   0.00139  -0.0452   0.7948   0.0914
  -2.500  -0.0574   0.00717   0.00128  -0.0448   0.7766   0.1139
  -2.250  -0.0315   0.00703   0.00119  -0.0444   0.7584   0.1449
  -2.000  -0.0054   0.00693   0.00110  -0.0440   0.7405   0.1715
  -1.750   0.0201   0.00675   0.00103  -0.0436   0.7219   0.2214
  -1.500   0.0455   0.00654   0.00096  -0.0432   0.7029   0.2818
  -1.250   0.0710   0.00644   0.00091  -0.0427   0.6797   0.3272
  -1.000   0.0967   0.00638   0.00087  -0.0423   0.6532   0.3670
  -0.750   0.1220   0.00624   0.00084  -0.0418   0.6291   0.4297
  -0.500   0.1470   0.00605   0.00082  -0.0413   0.6066   0.5079
  -0.250   0.1721   0.00590   0.00081  -0.0409   0.5834   0.5797
   0.000   0.1973   0.00576   0.00081  -0.0403   0.5638   0.6485
   0.250   0.2221   0.00562   0.00085  -0.0397   0.5438   0.7224
   0.500   0.2477   0.00563   0.00090  -0.0391   0.5228   0.7684
   0.750   0.2739   0.00569   0.00096  -0.0387   0.5033   0.7967
   1.000   0.3003   0.00577   0.00101  -0.0383   0.4816   0.8143
   1.250   0.3269   0.00587   0.00107  -0.0379   0.4623   0.8270
   1.500   0.3535   0.00598   0.00113  -0.0376   0.4419   0.8385
   1.750   0.3795   0.00611   0.00120  -0.0372   0.4175   0.8503
   2.000   0.4056   0.00625   0.00128  -0.0368   0.3927   0.8613
   2.250   0.4314   0.00644   0.00137  -0.0363   0.3626   0.8706
   2.500   0.4566   0.00666   0.00147  -0.0358   0.3284   0.8794
   2.750   0.4819   0.00686   0.00159  -0.0353   0.2998   0.8893
   3.000   0.5074   0.00703   0.00170  -0.0347   0.2764   0.9002
   3.250   0.5323   0.00721   0.00182  -0.0341   0.2541   0.9116
   3.500   0.5564   0.00743   0.00197  -0.0333   0.2263   0.9235
   3.750   0.5802   0.00769   0.00213  -0.0325   0.1937   0.9345
   4.000   0.6050   0.00794   0.00229  -0.0318   0.1688   0.9437
   4.250   0.6306   0.00817   0.00246  -0.0314   0.1515   0.9526
   4.500   0.6581   0.00836   0.00262  -0.0314   0.1404   0.9610
   4.750   0.6864   0.00857   0.00280  -0.0316   0.1286   0.9697
   5.000   0.7171   0.00881   0.00298  -0.0324   0.1141   0.9768
   5.250   0.7476   0.00907   0.00318  -0.0331   0.0993   0.9842
   5.500   0.7788   0.00936   0.00341  -0.0341   0.0847   0.9905
   5.750   0.8095   0.00965   0.00364  -0.0349   0.0743   0.9976
   6.000   0.8356   0.00992   0.00388  -0.0347   0.0664   1.0000
   6.250   0.8599   0.01014   0.00409  -0.0341   0.0613   1.0000
   6.500   0.8840   0.01042   0.00436  -0.0335   0.0553   1.0000
   6.750   0.9084   0.01069   0.00461  -0.0329   0.0495   1.0000
   7.000   0.9322   0.01101   0.00490  -0.0323   0.0427   1.0000
   7.250   0.9565   0.01130   0.00518  -0.0317   0.0379   1.0000
   7.500   0.9802   0.01165   0.00551  -0.0311   0.0323   1.0000
   7.750   1.0044   0.01195   0.00581  -0.0305   0.0295   1.0000
   8.000   1.0279   0.01232   0.00616  -0.0299   0.0258   1.0000
   8.250   1.0517   0.01265   0.00651  -0.0293   0.0231   1.0000
   8.500   1.0751   0.01301   0.00687  -0.0286   0.0208   1.0000
   8.750   1.0982   0.01340   0.00728  -0.0279   0.0184   1.0000
   9.000   1.1215   0.01377   0.00766  -0.0273   0.0166   1.0000
   9.250   1.1437   0.01422   0.00811  -0.0265   0.0141   1.0000
   9.500   1.1662   0.01462   0.00855  -0.0258   0.0123   1.0000
   9.750   1.1875   0.01514   0.00906  -0.0248   0.0097   1.0000
  10.000   1.2086   0.01565   0.00959  -0.0239   0.0081   1.0000
  10.250   1.2289   0.01622   0.01019  -0.0229   0.0068   1.0000
  10.500   1.2496   0.01672   0.01075  -0.0219   0.0062   1.0000
  10.750   1.2697   0.01726   0.01134  -0.0208   0.0059   1.0000
  11.000   1.2887   0.01786   0.01199  -0.0196   0.0054   1.0000
  11.250   1.3070   0.01848   0.01266  -0.0183   0.0051   1.0000
  11.500   1.3233   0.01924   0.01350  -0.0168   0.0046   1.0000
  11.750   1.3403   0.01988   0.01420  -0.0153   0.0045   1.0000
  12.000   1.3562   0.02053   0.01494  -0.0137   0.0043   1.0000
  12.250   1.3693   0.02118   0.01566  -0.0116   0.0042   1.0000
  12.500   1.3808   0.02189   0.01645  -0.0094   0.0040   1.0000
  12.750   1.3912   0.02267   0.01731  -0.0070   0.0039   1.0000
  13.000   1.4009   0.02350   0.01823  -0.0047   0.0038   1.0000
  13.250   1.4095   0.02443   0.01924  -0.0025   0.0037   1.0000
  13.500   1.4174   0.02541   0.02030  -0.0003   0.0036   1.0000
  13.750   1.4242   0.02651   0.02148   0.0017   0.0035   1.0000
  14.000   1.4289   0.02780   0.02287   0.0038   0.0034   1.0000
  14.250   1.4324   0.02925   0.02441   0.0056   0.0032   1.0000
  14.500   1.4337   0.03097   0.02625   0.0074   0.0031   1.0000
  14.750   1.4337   0.03292   0.02830   0.0088   0.0031   1.0000
  15.000   1.4313   0.03523   0.03073   0.0099   0.0030   1.0000
  15.250   1.4289   0.03773   0.03335   0.0105   0.0029   1.0000
  15.500   1.4164   0.04153   0.03731   0.0107   0.0028   1.0000
  15.750   1.4155   0.04434   0.04022   0.0103   0.0028   1.0000
  16.000   1.4021   0.04893   0.04497   0.0092   0.0028   1.0000
  16.250   1.3956   0.05297   0.04913   0.0077   0.0028   1.0000
  16.500   1.3883   0.05733   0.05362   0.0059   0.0027   1.0000
  16.750   1.3700   0.06372   0.06017   0.0028   0.0027   1.0000
  17.000   1.3550   0.06996   0.06654  -0.0005   0.0027   1.0000
  17.250   1.3287   0.07856   0.07531  -0.0053   0.0027   1.0000
  17.500   1.2973   0.08863   0.08556  -0.0110   0.0027   1.0000
  17.750   1.2592   0.10056   0.09768  -0.0179   0.0028   1.0000
<< Back to RG 14 9.5% AIRFOIL (rg1495-il)

Polar data table (+)

Polar graphs


<< Back to RG 14 9.5% AIRFOIL (rg1495-il)