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

USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 31 AIRFOIL (usa31-il)
Reynolds number: 1,000,000
Max Cl/Cd: 79.88 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa31-il-1000000-n5.txt
Download as CSV file: xf-usa31-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 31 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500   0.2808   0.09346   0.09106  -0.1824   0.9285   0.0165
 -12.250   0.2904   0.09257   0.09018  -0.1818   0.9248   0.0167
 -12.000   0.2981   0.09034   0.08795  -0.1825   0.9214   0.0167
 -11.750   0.3134   0.08876   0.08636  -0.1840   0.9188   0.0169
 -11.500   0.3224   0.08661   0.08420  -0.1849   0.9159   0.0170
 -11.250   0.3263   0.08492   0.08254  -0.1841   0.9112   0.0173
 -11.000   0.3338   0.08290   0.08050  -0.1845   0.9064   0.0174
 -10.750   0.3429   0.08058   0.07817  -0.1856   0.9022   0.0177
 -10.500   0.3468   0.07851   0.07611  -0.1854   0.8957   0.0178
 -10.250   0.3544   0.07619   0.07375  -0.1862   0.8887   0.0180
 -10.000   0.3595   0.07392   0.07147  -0.1865   0.8803   0.0181
  -9.750   0.3656   0.07144   0.06894  -0.1874   0.8710   0.0183
  -9.500   0.3700   0.06892   0.06636  -0.1880   0.8588   0.0185
  -9.250   0.3542   0.06324   0.06061  -0.1894   0.8450   0.0195
  -9.000   0.3554   0.06093   0.05823  -0.1893   0.8317   0.0195
  -8.750   0.3593   0.05936   0.05660  -0.1888   0.8188   0.0196
  -8.500   0.3543   0.05675   0.05393  -0.1883   0.8075   0.0196
  -8.250   0.3540   0.05497   0.05213  -0.1875   0.7966   0.0197
  -8.000   0.3506   0.05323   0.05036  -0.1862   0.7866   0.0198
  -7.500   0.2008   0.02697   0.02361  -0.1938   0.7634   0.0203
  -7.250   0.2043   0.02299   0.01929  -0.1944   0.7534   0.0204
  -7.000   0.2153   0.02064   0.01667  -0.1936   0.7433   0.0206
  -6.750   0.2273   0.01924   0.01505  -0.1917   0.7338   0.0207
  -6.500   0.2397   0.01820   0.01381  -0.1894   0.7223   0.0209
  -6.250   0.2522   0.01728   0.01269  -0.1868   0.7109   0.0210
  -6.000   0.2629   0.01650   0.01172  -0.1837   0.6982   0.0211
  -5.500   0.2787   0.01528   0.01016  -0.1759   0.6720   0.0214
  -5.250   0.2890   0.01481   0.00954  -0.1724   0.6611   0.0215
  -5.000   0.2995   0.01429   0.00887  -0.1689   0.6505   0.0216
  -4.750   0.3143   0.01387   0.00832  -0.1663   0.6417   0.0217
  -4.500   0.3282   0.01348   0.00779  -0.1634   0.6327   0.0218
  -4.250   0.3453   0.01311   0.00732  -0.1612   0.6257   0.0219
  -4.000   0.3632   0.01279   0.00690  -0.1592   0.6192   0.0221
  -3.500   0.4005   0.01232   0.00626  -0.1553   0.6068   0.0223
  -3.250   0.4202   0.01215   0.00602  -0.1536   0.6004   0.0224
  -3.000   0.4390   0.01209   0.00587  -0.1517   0.5942   0.0226
  -2.750   0.4591   0.01178   0.00551  -0.1500   0.5897   0.0227
  -2.500   0.4794   0.01157   0.00526  -0.1484   0.5838   0.0230
  -2.250   0.4994   0.01147   0.00512  -0.1468   0.5781   0.0230
  -2.000   0.5194   0.01139   0.00500  -0.1451   0.5727   0.0232
  -1.750   0.5411   0.01131   0.00490  -0.1438   0.5671   0.0235
  -1.500   0.5617   0.01126   0.00482  -0.1422   0.5613   0.0237
  -1.250   0.5812   0.01123   0.00473  -0.1405   0.5556   0.0237
  -1.000   0.6039   0.01118   0.00465  -0.1394   0.5503   0.0241
  -0.750   0.6245   0.01117   0.00460  -0.1379   0.5429   0.0243
  -0.500   0.6443   0.01119   0.00458  -0.1362   0.5367   0.0246
  -0.250   0.6662   0.01116   0.00453  -0.1350   0.5308   0.0247
   0.000   0.6859   0.01120   0.00452  -0.1333   0.5231   0.0250
   0.250   0.7063   0.01123   0.00451  -0.1318   0.5164   0.0253
   0.500   0.7279   0.01127   0.00451  -0.1305   0.5094   0.0256
   0.750   0.7470   0.01136   0.00455  -0.1288   0.5013   0.0257
   1.000   0.7691   0.01140   0.00457  -0.1276   0.4947   0.0259
   1.250   0.7883   0.01151   0.00464  -0.1260   0.4864   0.0261
   1.500   0.8081   0.01158   0.00466  -0.1244   0.4787   0.0265
   1.750   0.8283   0.01167   0.00473  -0.1230   0.4712   0.0272
   2.000   0.8480   0.01180   0.00482  -0.1214   0.4639   0.0277
   2.250   0.8692   0.01190   0.00490  -0.1202   0.4572   0.0282
   2.500   0.8885   0.01207   0.00503  -0.1187   0.4497   0.0288
   2.750   0.9094   0.01220   0.00514  -0.1174   0.4441   0.0294
   3.000   0.9292   0.01236   0.00528  -0.1160   0.4373   0.0299
   3.250   0.9480   0.01257   0.00545  -0.1144   0.4311   0.0305
   3.500   0.9695   0.01270   0.00557  -0.1133   0.4267   0.0315
   3.750   0.9900   0.01287   0.00573  -0.1120   0.4205   0.0330
   4.250   1.0294   0.01327   0.00612  -0.1093   0.4101   0.0425
   4.500   1.0496   0.01314   0.00642  -0.1082   0.4055   0.2515
   4.750   1.0689   0.01340   0.00669  -0.1069   0.4000   0.2604
   5.000   1.0878   0.01369   0.00696  -0.1054   0.3951   0.2679
   5.250   1.1090   0.01391   0.00720  -0.1044   0.3908   0.2746
   5.500   1.1281   0.01421   0.00750  -0.1031   0.3838   0.2824
   5.750   1.1445   0.01462   0.00786  -0.1014   0.3763   0.2856
   6.000   1.1647   0.01488   0.00812  -0.1003   0.3711   0.2879
   6.250   1.1831   0.01522   0.00844  -0.0989   0.3644   0.2908
   6.500   1.2009   0.01559   0.00880  -0.0975   0.3589   0.2928
   6.750   1.2196   0.01594   0.00915  -0.0963   0.3518   0.2961
   7.000   1.2379   0.01630   0.00951  -0.0950   0.3470   0.2978
   7.250   1.2558   0.01670   0.00990  -0.0937   0.3428   0.2993
   7.500   1.2753   0.01703   0.01024  -0.0927   0.3385   0.3005
   7.750   1.2942   0.01739   0.01061  -0.0916   0.3342   0.3023
   8.000   1.3109   0.01786   0.01107  -0.0902   0.3285   0.3034
   8.250   1.3275   0.01835   0.01154  -0.0888   0.3227   0.3047
   8.500   1.3458   0.01877   0.01197  -0.0877   0.3170   0.3059
   8.750   1.3609   0.01936   0.01254  -0.0862   0.3105   0.3068
   9.000   1.3775   0.01988   0.01307  -0.0850   0.3052   0.3087
   9.250   1.3930   0.02048   0.01365  -0.0836   0.2966   0.3105
   9.500   1.4074   0.02114   0.01431  -0.0822   0.2906   0.3118
   9.750   1.4243   0.02169   0.01489  -0.0811   0.2859   0.3135
  10.000   1.4396   0.02234   0.01553  -0.0799   0.2797   0.3150
  10.250   1.4537   0.02307   0.01626  -0.0785   0.2741   0.3167
  10.500   1.4655   0.02395   0.01712  -0.0769   0.2636   0.3183
  10.750   1.4785   0.02477   0.01793  -0.0755   0.2574   0.3199
  11.000   1.4909   0.02565   0.01881  -0.0741   0.2490   0.3213
  11.250   1.5019   0.02664   0.01979  -0.0726   0.2424   0.3228
  11.500   1.5111   0.02776   0.02087  -0.0710   0.2306   0.3239
  11.750   1.5167   0.02916   0.02222  -0.0690   0.2177   0.3248
  12.000   1.5261   0.03033   0.02338  -0.0676   0.2102   0.3263
  12.250   1.5341   0.03166   0.02470  -0.0661   0.2011   0.3285
  12.500   1.5401   0.03313   0.02614  -0.0644   0.1907   0.3301
  12.750   1.5486   0.03448   0.02751  -0.0631   0.1851   0.3319
  13.000   1.5548   0.03602   0.02904  -0.0617   0.1763   0.3340
  13.250   1.5590   0.03776   0.03076  -0.0602   0.1686   0.3352
  13.500   1.5657   0.03932   0.03233  -0.0590   0.1618   0.3369
  13.750   1.5695   0.04117   0.03418  -0.0576   0.1547   0.3383
  14.000   1.5738   0.04302   0.03604  -0.0564   0.1475   0.3397
  14.250   1.5798   0.04475   0.03778  -0.0553   0.1425   0.3406
  14.500   1.5780   0.04720   0.04020  -0.0539   0.1321   0.3418
  14.750   1.5836   0.04904   0.04208  -0.0530   0.1287   0.3433
  15.000   1.5821   0.05157   0.04460  -0.0518   0.1190   0.3444
  15.250   1.5731   0.05485   0.04784  -0.0503   0.1059   0.3457
  15.500   1.5669   0.05793   0.05091  -0.0491   0.0969   0.3469
  15.750   1.5627   0.06085   0.05383  -0.0481   0.0906   0.3484
  16.000   1.5615   0.06351   0.05652  -0.0473   0.0858   0.3500
  16.500   1.5580   0.06910   0.06218  -0.0459   0.0784   0.3539
  16.750   1.5579   0.07175   0.06488  -0.0454   0.0758   0.3549
  17.000   1.5531   0.07491   0.06807  -0.0448   0.0724   0.3570
  17.250   1.5536   0.07753   0.07074  -0.0444   0.0702   0.3584
  17.500   1.5507   0.08062   0.07388  -0.0441   0.0663   0.3599
  17.750   1.5428   0.08427   0.07755  -0.0437   0.0615   0.3611
  18.000   1.5370   0.08770   0.08101  -0.0435   0.0556   0.3625
  18.250   1.5034   0.09450   0.08773  -0.0431   0.0372   0.3628
  18.500   1.4776   0.10061   0.09383  -0.0431   0.0235   0.3630
<< Back to USA 31 AIRFOIL (usa31-il)

Polar data table (+)

Polar graphs


<< Back to USA 31 AIRFOIL (usa31-il)