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ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 10% AIRFOIL (arad10-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.58 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad10-il-1000000.txt
Download as CSV file: xf-arad10-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 10% 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7746   0.04125   0.03882  -0.0658   1.0000   0.0133
 -10.750  -0.7708   0.03023   0.02715  -0.0728   1.0000   0.0133
 -10.500  -0.7561   0.02585   0.02234  -0.0743   1.0000   0.0134
 -10.250  -0.7355   0.02333   0.01957  -0.0749   1.0000   0.0136
 -10.000  -0.7123   0.02167   0.01774  -0.0751   1.0000   0.0138
  -9.750  -0.6882   0.02045   0.01639  -0.0751   1.0000   0.0139
  -9.500  -0.6646   0.01944   0.01528  -0.0748   1.0000   0.0141
  -9.250  -0.6423   0.01858   0.01433  -0.0741   1.0000   0.0143
  -9.000  -0.6221   0.01784   0.01350  -0.0729   1.0000   0.0145
  -8.750  -0.5936   0.01703   0.01258  -0.0733   0.9991   0.0147
  -8.500  -0.5606   0.01620   0.01165  -0.0747   0.9977   0.0150
  -8.250  -0.5272   0.01544   0.01078  -0.0760   0.9963   0.0153
  -8.000  -0.4933   0.01479   0.01004  -0.0774   0.9950   0.0157
  -7.750  -0.4589   0.01429   0.00945  -0.0788   0.9940   0.0160
  -7.500  -0.4262   0.01338   0.00843  -0.0801   0.9916   0.0164
  -7.250  -0.3935   0.01272   0.00771  -0.0812   0.9883   0.0169
  -7.000  -0.3602   0.01227   0.00722  -0.0823   0.9849   0.0174
  -6.750  -0.3285   0.01187   0.00678  -0.0830   0.9799   0.0179
  -6.500  -0.2985   0.01152   0.00638  -0.0833   0.9733   0.0185
  -6.250  -0.2699   0.01123   0.00603  -0.0832   0.9658   0.0190
  -6.000  -0.2426   0.01080   0.00555  -0.0828   0.9575   0.0198
  -5.750  -0.2152   0.01050   0.00522  -0.0824   0.9487   0.0208
  -5.500  -0.1882   0.01028   0.00496  -0.0819   0.9401   0.0219
  -5.250  -0.1602   0.00998   0.00462  -0.0817   0.9305   0.0234
  -5.000  -0.1325   0.00976   0.00437  -0.0814   0.9214   0.0255
  -4.750  -0.1043   0.00952   0.00412  -0.0812   0.9112   0.0284
  -4.500  -0.0758   0.00933   0.00392  -0.0810   0.9010   0.0321
  -4.250  -0.0476   0.00922   0.00376  -0.0808   0.8904   0.0356
  -4.000  -0.0188   0.00903   0.00358  -0.0807   0.8787   0.0398
  -3.750   0.0100   0.00889   0.00341  -0.0807   0.8671   0.0436
  -3.500   0.0387   0.00880   0.00328  -0.0806   0.8547   0.0472
  -3.250   0.0675   0.00868   0.00312  -0.0805   0.8394   0.0514
  -3.000   0.0961   0.00864   0.00300  -0.0804   0.8191   0.0552
  -2.750   0.1248   0.00855   0.00286  -0.0803   0.7965   0.0608
  -2.500   0.1537   0.00851   0.00275  -0.0803   0.7762   0.0661
  -2.250   0.1827   0.00848   0.00267  -0.0803   0.7572   0.0730
  -2.000   0.2118   0.00843   0.00259  -0.0804   0.7385   0.0819
  -1.750   0.2411   0.00839   0.00252  -0.0805   0.7213   0.0909
  -1.250   0.2996   0.00836   0.00242  -0.0807   0.6880   0.1094
  -1.000   0.3288   0.00835   0.00239  -0.0809   0.6707   0.1204
  -0.750   0.3581   0.00836   0.00236  -0.0810   0.6544   0.1300
  -0.500   0.3873   0.00838   0.00235  -0.0811   0.6375   0.1408
  -0.250   0.4166   0.00839   0.00234  -0.0813   0.6190   0.1532
   0.000   0.4458   0.00842   0.00233  -0.0814   0.6001   0.1659
   0.250   0.4750   0.00845   0.00234  -0.0816   0.5819   0.1816
   0.500   0.5041   0.00848   0.00236  -0.0818   0.5613   0.2022
   0.750   0.5330   0.00852   0.00239  -0.0819   0.5382   0.2356
   1.000   0.5621   0.00845   0.00244  -0.0822   0.5159   0.3097
   1.250   0.5825   0.00673   0.00241  -0.0808   0.4944   1.0000
   1.500   0.6113   0.00694   0.00247  -0.0809   0.4669   1.0000
   1.750   0.6398   0.00719   0.00255  -0.0810   0.4359   1.0000
   2.000   0.6683   0.00745   0.00264  -0.0811   0.4044   1.0000
   2.250   0.6966   0.00775   0.00275  -0.0812   0.3701   1.0000
   2.500   0.7247   0.00807   0.00289  -0.0813   0.3337   1.0000
   2.750   0.7528   0.00839   0.00303  -0.0813   0.3033   1.0000
   3.000   0.7811   0.00866   0.00317  -0.0814   0.2797   1.0000
   3.250   0.8093   0.00893   0.00332  -0.0815   0.2600   1.0000
   3.500   0.8376   0.00917   0.00346  -0.0816   0.2447   1.0000
   3.750   0.8659   0.00939   0.00361  -0.0817   0.2318   1.0000
   4.000   0.8941   0.00961   0.00376  -0.0818   0.2198   1.0000
   4.250   0.9222   0.00986   0.00392  -0.0818   0.2088   1.0000
   4.500   0.9505   0.01004   0.00407  -0.0819   0.2011   1.0000
   4.750   0.9785   0.01028   0.00425  -0.0820   0.1923   1.0000
   5.000   1.0066   0.01046   0.00440  -0.0820   0.1859   1.0000
   5.250   1.0343   0.01072   0.00459  -0.0820   0.1779   1.0000
   5.500   1.0624   0.01089   0.00476  -0.0821   0.1735   1.0000
   5.750   1.0901   0.01111   0.00495  -0.0821   0.1678   1.0000
   6.000   1.1175   0.01136   0.00516  -0.0821   0.1617   1.0000
   6.250   1.1453   0.01154   0.00535  -0.0821   0.1576   1.0000
   6.500   1.1726   0.01179   0.00556  -0.0821   0.1525   1.0000
   6.750   1.1996   0.01205   0.00580  -0.0820   0.1473   1.0000
   7.000   1.2271   0.01224   0.00600  -0.0820   0.1436   1.0000
   7.250   1.2540   0.01250   0.00623  -0.0819   0.1391   1.0000
   7.500   1.2804   0.01281   0.00651  -0.0818   0.1338   1.0000
   7.750   1.3075   0.01300   0.00672  -0.0817   0.1306   1.0000
   8.000   1.3339   0.01327   0.00697  -0.0816   0.1266   1.0000
   8.250   1.3595   0.01363   0.00730  -0.0813   0.1212   1.0000
   8.500   1.3861   0.01384   0.00755  -0.0812   0.1185   1.0000
   8.750   1.4120   0.01412   0.00782  -0.0810   0.1148   1.0000
   9.000   1.4371   0.01449   0.00816  -0.0806   0.1102   1.0000
   9.250   1.4625   0.01479   0.00848  -0.0804   0.1070   1.0000
   9.500   1.4878   0.01507   0.00878  -0.0801   0.1038   1.0000
   9.750   1.5122   0.01545   0.00913  -0.0796   0.0999   1.0000
  10.000   1.5361   0.01586   0.00955  -0.0791   0.0961   1.0000
  10.250   1.5608   0.01615   0.00987  -0.0787   0.0937   1.0000
  10.500   1.5844   0.01652   0.01025  -0.0782   0.0906   1.0000
  10.750   1.6067   0.01700   0.01071  -0.0775   0.0870   1.0000
  11.000   1.6296   0.01739   0.01114  -0.0768   0.0847   1.0000
  11.250   1.6525   0.01775   0.01154  -0.0762   0.0825   1.0000
  11.500   1.6740   0.01819   0.01199  -0.0753   0.0798   1.0000
  11.750   1.6936   0.01877   0.01256  -0.0742   0.0764   1.0000
  12.000   1.7143   0.01920   0.01304  -0.0732   0.0746   1.0000
  12.250   1.7348   0.01962   0.01351  -0.0722   0.0725   1.0000
  12.500   1.7533   0.02015   0.01405  -0.0709   0.0698   1.0000
  12.750   1.7687   0.02086   0.01476  -0.0691   0.0667   1.0000
  13.000   1.7865   0.02135   0.01531  -0.0677   0.0652   1.0000
  13.250   1.8026   0.02189   0.01590  -0.0661   0.0633   1.0000
  13.500   1.8133   0.02259   0.01662  -0.0635   0.0613   1.0000
  13.750   1.8216   0.02348   0.01754  -0.0607   0.0589   1.0000
  14.000   1.8323   0.02432   0.01844  -0.0584   0.0573   1.0000
  14.250   1.8446   0.02510   0.01929  -0.0566   0.0559   1.0000
  14.500   1.8552   0.02605   0.02028  -0.0546   0.0542   1.0000
  14.750   1.8640   0.02718   0.02145  -0.0526   0.0524   1.0000
  15.000   1.8695   0.02860   0.02292  -0.0505   0.0505   1.0000
  15.250   1.8801   0.02968   0.02409  -0.0490   0.0495   1.0000
  15.500   1.8893   0.03094   0.02541  -0.0475   0.0482   1.0000
  15.750   1.8963   0.03242   0.02696  -0.0460   0.0467   1.0000
  16.000   1.9007   0.03419   0.02877  -0.0445   0.0452   1.0000
  16.250   1.9018   0.03635   0.03099  -0.0430   0.0435   1.0000
  16.500   1.9092   0.03800   0.03274  -0.0421   0.0427   1.0000
  16.750   1.9136   0.04000   0.03482  -0.0412   0.0417   1.0000
  17.000   1.9156   0.04231   0.03721  -0.0404   0.0406   1.0000
  17.250   1.9150   0.04499   0.03996  -0.0398   0.0396   1.0000
  17.500   1.9116   0.04809   0.04313  -0.0393   0.0384   1.0000
  17.750   1.9056   0.05161   0.04676  -0.0391   0.0374   1.0000
  18.000   1.9054   0.05453   0.04979  -0.0391   0.0368   1.0000
  18.250   1.9017   0.05801   0.05337  -0.0393   0.0360   1.0000
  18.500   1.8953   0.06193   0.05740  -0.0398   0.0353   1.0000
  18.750   1.8856   0.06643   0.06200  -0.0406   0.0347   1.0000
  19.000   1.8728   0.07146   0.06714  -0.0418   0.0340   1.0000
  19.250   1.8567   0.07714   0.07294  -0.0433   0.0334   1.0000
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