Airfoil Tools
Search 1638 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il)
Reynolds number: 500,000
Max Cl/Cd: 81.81 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1212mod-il-500000.txt
Download as CSV file: xf-e1212mod-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E1212MOD 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
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.8374   0.08677   0.08264  -0.0338   1.0000   0.0260
 -15.000  -0.8492   0.08157   0.07739  -0.0366   1.0000   0.0259
 -14.750  -0.8702   0.07521   0.07095  -0.0401   1.0000   0.0259
 -14.500  -0.8949   0.06859   0.06422  -0.0438   1.0000   0.0257
 -14.250  -0.9367   0.05988   0.05536  -0.0490   1.0000   0.0257
 -14.000  -0.9801   0.05101   0.04634  -0.0544   1.0000   0.0255
 -13.750  -1.0235   0.04133   0.03644  -0.0611   1.0000   0.0252
 -13.500  -1.0523   0.03253   0.02737  -0.0693   1.0000   0.0252
 -13.250  -1.0666   0.02872   0.02339  -0.0711   1.0000   0.0253
 -13.000  -1.0725   0.02683   0.02140  -0.0695   1.0000   0.0254
 -12.750  -1.0764   0.02551   0.01999  -0.0665   1.0000   0.0256
 -12.500  -1.0738   0.02437   0.01878  -0.0639   1.0000   0.0258
 -12.250  -1.0664   0.02327   0.01762  -0.0618   1.0000   0.0262
 -12.000  -1.0561   0.02229   0.01659  -0.0598   1.0000   0.0267
 -11.750  -1.0435   0.02141   0.01566  -0.0580   1.0000   0.0273
 -11.500  -1.0293   0.02061   0.01481  -0.0562   1.0000   0.0282
 -11.250  -1.0148   0.01980   0.01399  -0.0545   1.0000   0.0296
 -11.000  -0.9994   0.01904   0.01322  -0.0528   1.0000   0.0318
 -10.750  -0.9842   0.01826   0.01247  -0.0510   1.0000   0.0364
 -10.500  -0.9460   0.01723   0.01149  -0.0538   0.9789   0.0474
 -10.250  -0.8967   0.01633   0.01059  -0.0586   0.9439   0.0567
 -10.000  -0.8485   0.01555   0.00973  -0.0630   0.8881   0.0659
  -9.750  -0.8251   0.01516   0.00917  -0.0622   0.8445   0.0727
  -9.500  -0.8033   0.01478   0.00871  -0.0611   0.8204   0.0800
  -9.000  -0.7565   0.01416   0.00800  -0.0592   0.7872   0.0958
  -8.750  -0.7314   0.01394   0.00775  -0.0585   0.7740   0.1039
  -8.500  -0.7059   0.01380   0.00756  -0.0579   0.7607   0.1114
  -8.250  -0.6797   0.01366   0.00738  -0.0573   0.7471   0.1165
  -8.000  -0.6532   0.01358   0.00722  -0.0567   0.7333   0.1215
  -7.750  -0.6270   0.01348   0.00704  -0.0561   0.7178   0.1256
  -7.500  -0.6001   0.01340   0.00692  -0.0556   0.7007   0.1298
  -7.250  -0.5727   0.01339   0.00679  -0.0551   0.6815   0.1336
  -7.000  -0.5467   0.01324   0.00658  -0.0545   0.6592   0.1371
  -6.750  -0.5203   0.01319   0.00643  -0.0539   0.6341   0.1403
  -6.500  -0.4934   0.01318   0.00628  -0.0533   0.6102   0.1433
  -6.250  -0.4662   0.01321   0.00615  -0.0529   0.5911   0.1457
  -6.000  -0.4400   0.01302   0.00590  -0.0523   0.5765   0.1487
  -5.750  -0.4132   0.01293   0.00576  -0.0518   0.5652   0.1516
  -5.500  -0.3857   0.01290   0.00567  -0.0515   0.5557   0.1545
  -5.250  -0.3581   0.01290   0.00556  -0.0511   0.5476   0.1572
  -5.000  -0.3300   0.01286   0.00545  -0.0508   0.5407   0.1591
  -4.750  -0.3033   0.01264   0.00519  -0.0503   0.5338   0.1618
  -4.500  -0.2765   0.01253   0.00505  -0.0498   0.5271   0.1651
  -4.250  -0.2483   0.01246   0.00499  -0.0496   0.5221   0.1686
  -4.000  -0.2201   0.01245   0.00492  -0.0493   0.5161   0.1721
  -3.750  -0.1922   0.01246   0.00484  -0.0489   0.5099   0.1746
  -3.500  -0.1656   0.01222   0.00462  -0.0485   0.5040   0.1790
  -3.250  -0.1376   0.01209   0.00451  -0.0482   0.4989   0.1823
  -3.000  -0.1097   0.01201   0.00440  -0.0478   0.4933   0.1853
  -2.750  -0.0819   0.01196   0.00428  -0.0475   0.4879   0.1876
  -2.500  -0.0539   0.01194   0.00419  -0.0471   0.4823   0.1893
  -2.250  -0.0263   0.01170   0.00399  -0.0467   0.4776   0.1927
  -2.000   0.0013   0.01155   0.00386  -0.0464   0.4720   0.1962
  -1.750   0.0289   0.01148   0.00375  -0.0460   0.4663   0.1994
  -1.500   0.0567   0.01145   0.00369  -0.0456   0.4607   0.2028
  -1.250   0.0852   0.01136   0.00359  -0.0453   0.4556   0.2060
  -1.000   0.1127   0.01119   0.00348  -0.0450   0.4498   0.2121
  -0.750   0.1403   0.01113   0.00340  -0.0446   0.4438   0.2186
  -0.500   0.1682   0.01105   0.00335  -0.0442   0.4379   0.2272
  -0.250   0.1963   0.01094   0.00331  -0.0439   0.4313   0.2393
   0.000   0.2240   0.01089   0.00328  -0.0436   0.4242   0.2558
   0.250   0.2521   0.01086   0.00330  -0.0433   0.4172   0.2739
   0.500   0.2802   0.01082   0.00330  -0.0430   0.4092   0.2889
   0.750   0.3078   0.01085   0.00328  -0.0426   0.4013   0.3008
   1.000   0.3361   0.01084   0.00329  -0.0423   0.3938   0.3116
   1.250   0.3635   0.01086   0.00329  -0.0419   0.3858   0.3213
   1.500   0.3911   0.01089   0.00332  -0.0416   0.3785   0.3311
   1.750   0.4187   0.01092   0.00334  -0.0412   0.3710   0.3400
   2.000   0.4454   0.01100   0.00340  -0.0407   0.3636   0.3495
   2.250   0.4733   0.01103   0.00345  -0.0404   0.3574   0.3582
   2.500   0.5002   0.01108   0.00352  -0.0399   0.3509   0.3692
   2.750   0.5269   0.01121   0.00361  -0.0395   0.3445   0.3803
   3.000   0.5543   0.01122   0.00370  -0.0391   0.3393   0.3951
   3.250   0.5811   0.01127   0.00380  -0.0386   0.3338   0.4134
   3.500   0.6069   0.01138   0.00392  -0.0381   0.3281   0.4376
   3.750   0.6334   0.01138   0.00404  -0.0376   0.3237   0.4694
   4.000   0.6588   0.01129   0.00416  -0.0369   0.3191   0.5258
   4.250   0.6812   0.01110   0.00431  -0.0357   0.3146   0.6338
   4.500   0.7016   0.01099   0.00451  -0.0339   0.3100   0.7576
   4.750   0.7676   0.01082   0.00483  -0.0410   0.3051   0.9705
   5.000   0.8230   0.01102   0.00501  -0.0464   0.3004   0.9990
   5.250   0.8491   0.01123   0.00516  -0.0459   0.2970   1.0000
   5.500   0.8719   0.01148   0.00535  -0.0447   0.2936   1.0000
   5.750   0.8948   0.01176   0.00559  -0.0436   0.2903   1.0000
   6.000   0.9192   0.01191   0.00575  -0.0427   0.2882   1.0000
   6.250   0.9433   0.01208   0.00592  -0.0418   0.2856   1.0000
   6.500   0.9673   0.01227   0.00610  -0.0408   0.2829   1.0000
   6.750   0.9909   0.01247   0.00627  -0.0399   0.2800   1.0000
   7.000   1.0138   0.01274   0.00649  -0.0388   0.2769   1.0000
   7.250   1.0362   0.01311   0.00680  -0.0377   0.2736   1.0000
   7.500   1.0605   0.01327   0.00700  -0.0368   0.2720   1.0000
   7.750   1.0846   0.01348   0.00723  -0.0360   0.2703   1.0000
   8.000   1.1084   0.01369   0.00745  -0.0351   0.2683   1.0000
   8.250   1.1321   0.01390   0.00767  -0.0342   0.2660   1.0000
   8.500   1.1554   0.01413   0.00790  -0.0332   0.2638   1.0000
   8.750   1.1781   0.01440   0.00814  -0.0322   0.2614   1.0000
   9.000   1.2004   0.01475   0.00847  -0.0312   0.2591   1.0000
   9.250   1.2228   0.01516   0.00886  -0.0302   0.2569   1.0000
   9.500   1.2459   0.01537   0.00913  -0.0293   0.2557   1.0000
   9.750   1.2685   0.01560   0.00941  -0.0283   0.2542   1.0000
  10.000   1.2908   0.01585   0.00969  -0.0273   0.2524   1.0000
  10.250   1.3125   0.01610   0.00997  -0.0262   0.2504   1.0000
  10.500   1.3336   0.01636   0.01025  -0.0250   0.2483   1.0000
  10.750   1.3540   0.01666   0.01056  -0.0238   0.2462   1.0000
  11.000   1.3730   0.01702   0.01090  -0.0223   0.2437   1.0000
  11.250   1.3919   0.01750   0.01136  -0.0210   0.2408   1.0000
  11.500   1.4078   0.01770   0.01164  -0.0190   0.2389   1.0000
  11.750   1.4233   0.01799   0.01199  -0.0170   0.2370   1.0000
  12.000   1.4384   0.01831   0.01236  -0.0150   0.2349   1.0000
  12.250   1.4536   0.01868   0.01278  -0.0132   0.2329   1.0000
  12.500   1.4680   0.01911   0.01323  -0.0114   0.2309   1.0000
  12.750   1.4816   0.01963   0.01375  -0.0096   0.2287   1.0000
  13.000   1.4949   0.02028   0.01439  -0.0080   0.2261   1.0000
  13.250   1.5084   0.02085   0.01504  -0.0065   0.2242   1.0000
  13.500   1.5214   0.02145   0.01574  -0.0051   0.2220   1.0000
  13.750   1.5339   0.02215   0.01651  -0.0039   0.2193   1.0000
  14.000   1.5457   0.02297   0.01738  -0.0028   0.2164   1.0000
  14.250   1.5554   0.02399   0.01842  -0.0017   0.2135   1.0000
  14.500   1.5641   0.02518   0.01960  -0.0007   0.2103   1.0000
  14.750   1.5759   0.02623   0.02077  -0.0001   0.2078   1.0000
  15.000   1.5865   0.02741   0.02205   0.0005   0.2043   1.0000
  15.250   1.5943   0.02885   0.02353   0.0010   0.2006   1.0000
  15.500   1.5965   0.03078   0.02545   0.0015   0.1964   1.0000
  15.750   1.6055   0.03230   0.02710   0.0017   0.1919   1.0000
  16.000   1.6078   0.03445   0.02930   0.0018   0.1862   1.0000
  16.250   1.6065   0.03699   0.03188   0.0018   0.1805   1.0000
  16.500   1.6024   0.03997   0.03491   0.0015   0.1725   1.0000
  16.750   1.5934   0.04352   0.03850   0.0011   0.1643   1.0000
  17.000   1.5751   0.04821   0.04320   0.0002   0.1555   1.0000
  17.250   1.5546   0.05325   0.04826  -0.0009   0.1480   1.0000
  17.500   1.5349   0.05827   0.05331  -0.0020   0.1424   1.0000
  17.750   1.5138   0.06351   0.05858  -0.0032   0.1379   1.0000
  18.000   1.4944   0.06868   0.06379  -0.0044   0.1341   1.0000
  18.250   1.4806   0.07324   0.06840  -0.0055   0.1309   1.0000
  18.500   1.4652   0.07810   0.07329  -0.0068   0.1279   1.0000
  18.750   1.4519   0.08271   0.07791  -0.0080   0.1253   1.0000
  19.000   1.4441   0.08675   0.08203  -0.0091   0.1230   1.0000
  19.250   1.4390   0.09045   0.08579  -0.0101   0.1210   1.0000
<< Back to EPPLER E1212MOD AIRFOIL (e1212mod-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER E1212MOD AIRFOIL (e1212mod-il)