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

ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 20% AIRFOIL (arad20-il)
Reynolds number: 200,000
Max Cl/Cd: 56.67 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad20-il-200000-n5.txt
Download as CSV file: xf-arad20-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 20% AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.8718   0.11443   0.10942  -0.0062   1.0000   0.0271
 -16.750  -0.9123   0.10217   0.09687  -0.0139   1.0000   0.0272
 -16.500  -0.9390   0.09309   0.08754  -0.0195   1.0000   0.0273
 -16.250  -0.9599   0.08544   0.07968  -0.0241   1.0000   0.0275
 -16.000  -0.9750   0.07912   0.07319  -0.0276   1.0000   0.0277
 -15.750  -0.9831   0.07419   0.06817  -0.0302   1.0000   0.0278
 -15.500  -0.9904   0.06947   0.06335  -0.0327   1.0000   0.0280
 -15.250  -0.9964   0.06498   0.05877  -0.0349   1.0000   0.0282
 -15.000  -1.0013   0.06080   0.05449  -0.0369   1.0000   0.0285
 -14.750  -1.0048   0.05692   0.05050  -0.0386   1.0000   0.0287
 -14.500  -1.0069   0.05334   0.04682  -0.0400   1.0000   0.0291
 -14.250  -1.0077   0.05008   0.04344  -0.0411   1.0000   0.0294
 -14.000  -1.0073   0.04709   0.04033  -0.0418   1.0000   0.0298
 -13.750  -1.0059   0.04435   0.03747  -0.0421   1.0000   0.0303
 -13.500  -1.0033   0.04188   0.03486  -0.0420   1.0000   0.0308
 -13.250  -0.9998   0.03965   0.03250  -0.0416   1.0000   0.0313
 -13.000  -0.9955   0.03773   0.03054  -0.0408   1.0000   0.0317
 -12.750  -0.9906   0.03605   0.02881  -0.0396   1.0000   0.0321
 -12.500  -0.9862   0.03457   0.02728  -0.0378   1.0000   0.0327
 -12.250  -0.9797   0.03330   0.02594  -0.0358   1.0000   0.0334
 -12.000  -0.9677   0.03213   0.02467  -0.0344   1.0000   0.0343
 -11.750  -0.9534   0.03102   0.02347  -0.0331   1.0000   0.0353
 -11.500  -0.9374   0.03003   0.02249  -0.0320   1.0000   0.0361
 -11.250  -0.9193   0.02911   0.02154  -0.0311   1.0000   0.0371
 -11.000  -0.8997   0.02821   0.02058  -0.0302   1.0000   0.0384
 -10.750  -0.8793   0.02732   0.01965  -0.0295   1.0000   0.0396
 -10.500  -0.8520   0.02654   0.01884  -0.0301   0.9299   0.0409
 -10.250  -0.8297   0.02601   0.01805  -0.0290   0.8251   0.0423
 -10.000  -0.8110   0.02558   0.01727  -0.0271   0.7456   0.0439
  -9.750  -0.7898   0.02512   0.01659  -0.0260   0.6911   0.0453
  -9.250  -0.7418   0.02416   0.01524  -0.0249   0.6299   0.0493
  -9.000  -0.7165   0.02369   0.01465  -0.0246   0.6098   0.0514
  -8.750  -0.6905   0.02322   0.01406  -0.0243   0.5939   0.0539
  -8.500  -0.6643   0.02278   0.01352  -0.0242   0.5809   0.0565
  -8.250  -0.6373   0.02233   0.01299  -0.0241   0.5698   0.0594
  -8.000  -0.6103   0.02193   0.01250  -0.0240   0.5604   0.0625
  -7.750  -0.5826   0.02150   0.01203  -0.0240   0.5516   0.0660
  -7.500  -0.5547   0.02113   0.01158  -0.0240   0.5432   0.0699
  -7.250  -0.5268   0.02076   0.01116  -0.0241   0.5363   0.0741
  -7.000  -0.4982   0.02039   0.01076  -0.0242   0.5296   0.0789
  -6.750  -0.4695   0.02006   0.01038  -0.0243   0.5228   0.0845
  -6.500  -0.4409   0.01973   0.01002  -0.0245   0.5167   0.0907
  -6.250  -0.4118   0.01941   0.00969  -0.0247   0.5112   0.0980
  -6.000  -0.3825   0.01908   0.00938  -0.0249   0.5055   0.1065
  -5.750  -0.3531   0.01879   0.00908  -0.0252   0.4998   0.1163
  -5.500  -0.3238   0.01853   0.00880  -0.0254   0.4945   0.1278
  -5.250  -0.2941   0.01827   0.00855  -0.0257   0.4897   0.1411
  -5.000  -0.2642   0.01799   0.00833  -0.0261   0.4847   0.1567
  -4.750  -0.2343   0.01772   0.00811  -0.0264   0.4794   0.1743
  -4.500  -0.2044   0.01747   0.00790  -0.0268   0.4745   0.1951
  -4.250  -0.1746   0.01728   0.00772  -0.0272   0.4701   0.2187
  -4.000  -0.1443   0.01700   0.00757  -0.0276   0.4655   0.2453
  -3.750  -0.1140   0.01677   0.00744  -0.0281   0.4604   0.2758
  -3.500  -0.0838   0.01653   0.00732  -0.0285   0.4556   0.3096
  -3.250  -0.0537   0.01634   0.00721  -0.0290   0.4512   0.3451
  -3.000  -0.0234   0.01619   0.00714  -0.0294   0.4470   0.3806
  -2.750   0.0071   0.01601   0.00710  -0.0298   0.4422   0.4156
  -2.500   0.0376   0.01587   0.00707  -0.0302   0.4374   0.4491
  -2.250   0.0679   0.01577   0.00704  -0.0305   0.4329   0.4822
  -2.000   0.0981   0.01572   0.00702  -0.0308   0.4287   0.5132
  -1.750   0.1285   0.01565   0.00705  -0.0311   0.4242   0.5438
  -1.500   0.1589   0.01560   0.00708  -0.0314   0.4194   0.5738
  -1.250   0.1891   0.01556   0.00711  -0.0316   0.4146   0.6014
  -1.000   0.2191   0.01556   0.00712  -0.0318   0.4103   0.6268
  -0.750   0.2490   0.01558   0.00717  -0.0319   0.4061   0.6511
  -0.500   0.2790   0.01559   0.00725  -0.0321   0.4013   0.6741
  -0.250   0.3089   0.01561   0.00731  -0.0322   0.3964   0.6957
   0.000   0.3386   0.01565   0.00735  -0.0323   0.3918   0.7165
   0.250   0.3679   0.01572   0.00739  -0.0324   0.3878   0.7362
   0.500   0.3972   0.01576   0.00751  -0.0324   0.3830   0.7546
   0.750   0.4263   0.01581   0.00759  -0.0323   0.3781   0.7723
   1.000   0.4553   0.01588   0.00764  -0.0323   0.3735   0.7894
   1.250   0.4840   0.01598   0.00769  -0.0323   0.3694   0.8066
   1.500   0.5121   0.01604   0.00782  -0.0320   0.3647   0.8225
   1.750   0.5402   0.01611   0.00792  -0.0318   0.3598   0.8383
   2.000   0.5680   0.01619   0.00797  -0.0315   0.3552   0.8543
   2.250   0.5950   0.01630   0.00802  -0.0311   0.3511   0.8704
   2.500   0.6217   0.01636   0.00814  -0.0306   0.3464   0.8862
   2.750   0.6484   0.01643   0.00822  -0.0301   0.3417   0.9026
   3.000   0.6753   0.01651   0.00826  -0.0297   0.3373   0.9198
   3.250   0.7029   0.01660   0.00829  -0.0295   0.3332   0.9382
   3.500   0.7332   0.01667   0.00841  -0.0299   0.3283   0.9579
   4.000   0.7994   0.01687   0.00852  -0.0323   0.3190   1.0000
   4.250   0.8296   0.01712   0.00871  -0.0331   0.3148   1.0000
   4.500   0.8598   0.01736   0.00895  -0.0338   0.3100   1.0000
   4.750   0.8896   0.01761   0.00916  -0.0344   0.3056   1.0000
   5.000   0.9190   0.01790   0.00937  -0.0350   0.3016   1.0000
   5.250   0.9483   0.01819   0.00964  -0.0355   0.2976   1.0000
   5.500   0.9777   0.01846   0.00993  -0.0361   0.2931   1.0000
   5.750   1.0065   0.01876   0.01020  -0.0366   0.2889   1.0000
   6.000   1.0348   0.01909   0.01046  -0.0370   0.2853   1.0000
   6.250   1.0631   0.01943   0.01079  -0.0374   0.2816   1.0000
   6.500   1.0914   0.01976   0.01115  -0.0378   0.2774   1.0000
   6.750   1.1190   0.02010   0.01148  -0.0381   0.2734   1.0000
   7.000   1.1461   0.02048   0.01181  -0.0383   0.2699   1.0000
   7.250   1.1730   0.02088   0.01220  -0.0385   0.2667   1.0000
   7.500   1.2000   0.02126   0.01263  -0.0388   0.2629   1.0000
   7.750   1.2263   0.02166   0.01305  -0.0389   0.2591   1.0000
   8.000   1.2519   0.02209   0.01346  -0.0389   0.2557   1.0000
   8.250   1.2767   0.02258   0.01389  -0.0389   0.2528   1.0000
   8.500   1.3019   0.02302   0.01441  -0.0389   0.2495   1.0000
   8.750   1.3264   0.02349   0.01494  -0.0388   0.2460   1.0000
   9.000   1.3498   0.02399   0.01545  -0.0386   0.2427   1.0000
   9.250   1.3721   0.02453   0.01598  -0.0382   0.2398   1.0000
   9.500   1.3937   0.02512   0.01655  -0.0378   0.2372   1.0000
   9.750   1.4151   0.02569   0.01722  -0.0373   0.2341   1.0000
  10.000   1.4351   0.02631   0.01790  -0.0367   0.2310   1.0000
  10.250   1.4534   0.02696   0.01859  -0.0358   0.2281   1.0000
  10.500   1.4698   0.02769   0.01931  -0.0347   0.2256   1.0000
  10.750   1.4846   0.02849   0.02009  -0.0335   0.2232   1.0000
  11.000   1.4962   0.02935   0.02108  -0.0318   0.2206   1.0000
  11.250   1.5042   0.03038   0.02221  -0.0298   0.2180   1.0000
  11.500   1.5120   0.03157   0.02347  -0.0281   0.2155   1.0000
  11.750   1.5194   0.03290   0.02485  -0.0267   0.2131   1.0000
  12.000   1.5267   0.03437   0.02633  -0.0257   0.2110   1.0000
  12.250   1.5336   0.03602   0.02803  -0.0249   0.2088   1.0000
  12.500   1.5383   0.03801   0.03016  -0.0244   0.2063   1.0000
  12.750   1.5421   0.04021   0.03249  -0.0243   0.2038   1.0000
  13.000   1.5454   0.04257   0.03493  -0.0243   0.2013   1.0000
  13.250   1.5486   0.04501   0.03741  -0.0245   0.1991   1.0000
  13.500   1.5528   0.04733   0.03973  -0.0246   0.1970   1.0000
  13.750   1.5518   0.05040   0.04294  -0.0251   0.1947   1.0000
  14.000   1.5477   0.05393   0.04662  -0.0259   0.1922   1.0000
  14.250   1.5432   0.05748   0.05028  -0.0266   0.1897   1.0000
  14.500   1.5405   0.06079   0.05366  -0.0273   0.1874   1.0000
  14.750   1.5407   0.06367   0.05655  -0.0278   0.1853   1.0000
  15.000   1.5405   0.06659   0.05950  -0.0282   0.1833   1.0000
  15.250   1.5251   0.07169   0.06480  -0.0296   0.1807   1.0000
  15.500   1.5126   0.07651   0.06976  -0.0309   0.1780   1.0000
  15.750   1.5047   0.08076   0.07409  -0.0321   0.1756   1.0000
  16.000   1.5056   0.08378   0.07713  -0.0329   0.1736   1.0000
  16.250   1.5156   0.08546   0.07877  -0.0332   0.1717   1.0000
  16.500   1.4837   0.09347   0.08704  -0.0360   0.1687   1.0000
  16.750   1.4622   0.10002   0.09375  -0.0383   0.1657   1.0000
  17.000   1.4546   0.10456   0.09836  -0.0399   0.1633   1.0000
  17.250   1.4624   0.10671   0.10050  -0.0406   0.1615   1.0000
  17.500   1.4656   0.10956   0.10336  -0.0416   0.1596   1.0000
  17.750   1.3928   0.12477   0.11893  -0.0480   0.1544   1.0000
  18.000   1.3880   0.12913   0.12335  -0.0500   0.1519   1.0000
  18.250   1.4038   0.13004   0.12423  -0.0505   0.1504   1.0000
  18.500   1.4268   0.12969   0.12383  -0.0503   0.1494   1.0000
<< Back to ARA-D 20% AIRFOIL (arad20-il)

Polar data table (+)

Polar graphs


<< Back to ARA-D 20% AIRFOIL (arad20-il)