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GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 610 B AIRFOIL (goe610b-il)
Reynolds number: 100,000
Max Cl/Cd: 61.25 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe610b-il-100000.txt
Download as CSV file: xf-goe610b-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610 B AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3110   0.10990   0.10513  -0.0374   1.0000   0.0575
  -8.500  -0.3222   0.10931   0.10467  -0.0370   1.0000   0.0576
  -8.250  -0.3355   0.10871   0.10421  -0.0360   1.0000   0.0577
  -8.000  -0.3044   0.09924   0.09466  -0.0336   1.0000   0.0593
  -7.750  -0.3047   0.09668   0.09217  -0.0314   1.0000   0.0606
  -7.500  -0.3155   0.09549   0.09108  -0.0283   1.0000   0.0614
  -7.250  -0.3336   0.09496   0.09067  -0.0242   1.0000   0.0617
  -7.000  -0.3488   0.09414   0.08994  -0.0209   1.0000   0.0625
  -6.750  -0.3601   0.09294   0.08881  -0.0188   1.0000   0.0634
  -6.500  -0.3696   0.09152   0.08746  -0.0172   1.0000   0.0647
  -6.250  -0.3773   0.09000   0.08600  -0.0167   1.0000   0.0665
  -6.000  -0.3378   0.08757   0.08338  -0.0376   0.9912   0.0700
  -5.750  -0.3289   0.08146   0.07738  -0.0323   0.9875   0.0718
  -5.500  -0.3011   0.07729   0.07317  -0.0362   0.9810   0.0757
  -5.250  -0.2439   0.07283   0.06839  -0.0549   0.9706   0.0831
  -5.000  -0.2324   0.06837   0.06403  -0.0521   0.9630   0.0859
  -4.500  -0.1627   0.06042   0.05585  -0.0642   0.9461   0.1003
  -4.250  -0.1166   0.05691   0.05200  -0.0732   0.9370   0.1112
  -4.000  -0.0909   0.05326   0.04839  -0.0744   0.9299   0.1182
  -3.750  -0.0579   0.05003   0.04500  -0.0784   0.9210   0.1299
  -3.500  -0.0179   0.04671   0.04147  -0.0834   0.9144   0.1433
  -3.250   0.0130   0.04410   0.03870  -0.0860   0.9050   0.1574
  -3.000   0.0549   0.04153   0.03586  -0.0905   0.8995   0.1844
  -2.750   0.0822   0.03909   0.03337  -0.0916   0.8904   0.2017
  -2.500   0.1190   0.03665   0.03081  -0.0942   0.8849   0.2319
  -2.250   0.1424   0.03506   0.02916  -0.0942   0.8754   0.2750
  -1.750   0.1928   0.01418   0.00882  -0.0894   0.8404   0.3951
  -1.500   0.2087   0.01286   0.00756  -0.0874   0.8324   0.4315
  -1.250   0.3017   0.02792   0.02001  -0.1016   0.8475   0.1669
  -1.000   0.3379   0.02623   0.01778  -0.1019   0.8411   0.1375
  -0.750   0.3695   0.02490   0.01628  -0.1023   0.8348   0.1317
  -0.500   0.3974   0.02419   0.01526  -0.1018   0.8268   0.1270
  -0.250   0.4333   0.02333   0.01428  -0.1029   0.8227   0.1299
   0.000   0.4525   0.02326   0.01412  -0.1014   0.8130   0.1319
   0.250   0.4879   0.02250   0.01323  -0.1021   0.8083   0.1320
   0.500   0.5088   0.02238   0.01308  -0.1008   0.7986   0.1335
   0.750   0.5448   0.02166   0.01227  -0.1014   0.7931   0.1368
   1.000   0.5654   0.02148   0.01217  -0.1000   0.7829   0.1410
   1.250   0.6007   0.02091   0.01159  -0.1006   0.7778   0.1537
   1.500   0.6207   0.02102   0.01178  -0.0994   0.7685   0.1645
   1.750   0.6541   0.02050   0.01133  -0.0998   0.7633   0.1949
   2.000   0.7180   0.01880   0.01113  -0.1073   0.7555   1.0000
   2.250   0.7465   0.01881   0.01099  -0.1068   0.7491   1.0000
   2.500   0.7664   0.01919   0.01132  -0.1053   0.7400   1.0000
   2.750   0.7970   0.01899   0.01103  -0.1050   0.7332   1.0000
   3.000   0.8164   0.01931   0.01136  -0.1033   0.7230   1.0000
   3.250   0.8428   0.01925   0.01125  -0.1024   0.7144   1.0000
   3.500   0.8694   0.01914   0.01112  -0.1015   0.7051   1.0000
   3.750   0.8914   0.01928   0.01127  -0.1001   0.6948   1.0000
   4.000   0.9196   0.01914   0.01111  -0.0995   0.6866   1.0000
   4.250   0.9429   0.01929   0.01130  -0.0984   0.6771   1.0000
   4.500   0.9664   0.01945   0.01153  -0.0973   0.6677   1.0000
   4.750   0.9963   0.01928   0.01135  -0.0969   0.6594   1.0000
   5.000   1.0182   0.01943   0.01157  -0.0955   0.6473   1.0000
   5.250   1.0420   0.01947   0.01166  -0.0942   0.6346   1.0000
   5.500   1.0664   0.01949   0.01176  -0.0930   0.6214   1.0000
   5.750   1.0909   0.01957   0.01189  -0.0919   0.6080   1.0000
   6.000   1.1149   0.01967   0.01205  -0.0907   0.5933   1.0000
   6.250   1.1382   0.01978   0.01222  -0.0893   0.5768   1.0000
   6.500   1.1613   0.01987   0.01237  -0.0879   0.5586   1.0000
   6.750   1.1849   0.01992   0.01242  -0.0865   0.5391   1.0000
   7.000   1.2026   0.02017   0.01280  -0.0843   0.5172   1.0000
   7.250   1.2231   0.02028   0.01295  -0.0825   0.4958   1.0000
   7.500   1.2381   0.02040   0.01320  -0.0798   0.4694   1.0000
   7.750   1.2513   0.02043   0.01325  -0.0768   0.4375   1.0000
   8.000   1.2608   0.02063   0.01336  -0.0733   0.3969   1.0000
   8.250   1.2682   0.02126   0.01371  -0.0696   0.3572   1.0000
   8.500   1.2756   0.02222   0.01447  -0.0663   0.3245   1.0000
   8.750   1.2806   0.02332   0.01546  -0.0627   0.2918   1.0000
   9.000   1.2821   0.02441   0.01653  -0.0587   0.2528   1.0000
   9.250   1.2750   0.02574   0.01767  -0.0535   0.1975   1.0000
   9.500   1.2579   0.02808   0.01938  -0.0479   0.1396   1.0000
   9.750   1.2397   0.03113   0.02206  -0.0428   0.1110   1.0000
  10.000   1.2312   0.03383   0.02462  -0.0390   0.0912   1.0000
  10.250   1.2321   0.03587   0.02665  -0.0365   0.0786   1.0000
  10.500   1.2356   0.03778   0.02856  -0.0343   0.0710   1.0000
  10.750   1.2417   0.03976   0.03055  -0.0322   0.0654   1.0000
  11.000   1.2491   0.04159   0.03236  -0.0305   0.0606   1.0000
  11.250   1.2668   0.04358   0.03434  -0.0290   0.0562   1.0000
  11.500   1.2918   0.04552   0.03643  -0.0279   0.0531   1.0000
  11.750   1.3165   0.04778   0.03879  -0.0271   0.0503   1.0000
  12.000   1.3512   0.05177   0.04284  -0.0278   0.0468   1.0000
  12.250   1.3543   0.05431   0.04573  -0.0257   0.0459   1.0000
  12.500   1.3585   0.05753   0.04931  -0.0239   0.0455   1.0000
  12.750   1.3569   0.06100   0.05312  -0.0220   0.0453   1.0000
  13.000   1.3503   0.06470   0.05719  -0.0202   0.0452   1.0000
  13.250   1.3395   0.06866   0.06146  -0.0186   0.0453   1.0000
  13.500   1.3266   0.07285   0.06594  -0.0175   0.0455   1.0000
  13.750   1.3101   0.07740   0.07076  -0.0168   0.0457   1.0000
  14.000   1.2919   0.08233   0.07595  -0.0167   0.0459   1.0000
  14.250   1.2736   0.08757   0.08141  -0.0172   0.0462   1.0000
  14.500   1.2529   0.09332   0.08737  -0.0184   0.0464   1.0000
  14.750   1.2333   0.09946   0.09370  -0.0201   0.0468   1.0000
  15.000   1.2161   0.10626   0.10064  -0.0221   0.0472   1.0000
  15.250   1.1937   0.11214   0.10676  -0.0254   0.0476   1.0000
  15.500   1.1581   0.12090   0.11575  -0.0316   0.0484   1.0000
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