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GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il)
Reynolds number: 50,000
Max Cl/Cd: 40.42 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe610bm-il-50000.txt
Download as CSV file: xf-goe610bm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610-B MOD. AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3092   0.10742   0.10094  -0.0243   1.0000   0.1247
  -7.500  -0.3141   0.10644   0.10008  -0.0254   1.0000   0.1286
  -7.250  -0.3234   0.10687   0.10068  -0.0290   1.0000   0.1301
  -7.000  -0.3063   0.10018   0.09400  -0.0246   1.0000   0.1366
  -6.750  -0.3093   0.09887   0.09281  -0.0255   1.0000   0.1424
  -6.500  -0.3177   0.09959   0.09367  -0.0307   1.0000   0.1445
  -6.250  -0.3074   0.09370   0.08783  -0.0239   1.0000   0.1534
  -6.000  -0.3137   0.09398   0.08822  -0.0286   1.0000   0.1583
  -5.750  -0.3097   0.08940   0.08372  -0.0229   1.0000   0.1649
  -5.500  -0.3105   0.08921   0.08358  -0.0282   1.0000   0.1726
  -5.250  -0.3096   0.08509   0.07957  -0.0227   1.0000   0.1780
  -5.000  -0.3033   0.08414   0.07860  -0.0288   1.0000   0.1876
  -4.750  -0.3038   0.08040   0.07496  -0.0228   1.0000   0.1939
  -4.500  -0.2966   0.07803   0.07262  -0.0252   1.0000   0.2041
  -3.750  -0.2684   0.07018   0.06483  -0.0282   1.0000   0.2459
  -3.500  -0.2523   0.06806   0.06268  -0.0311   1.0000   0.2728
  -3.250  -0.2430   0.06562   0.06026  -0.0303   1.0000   0.3016
  -3.000  -0.2423   0.06255   0.05732  -0.0254   1.0000   0.3220
  -2.750  -0.2321   0.06026   0.05505  -0.0249   1.0000   0.3622
  -2.500  -0.2265   0.05798   0.05284  -0.0220   1.0000   0.4052
  -2.250  -0.2263   0.05566   0.05064  -0.0167   1.0000   0.4515
  -1.750  -0.2335   0.05138   0.04661  -0.0033   1.0000   0.5670
  -1.500  -0.2371   0.04918   0.04452   0.0032   1.0000   0.6232
  -1.250  -0.2279   0.04622   0.04164   0.0084   0.9942   0.6929
  -1.000   0.1526   0.03899   0.03076  -0.0913   0.9773   0.1955
  -0.750   0.2226   0.03675   0.02760  -0.0993   0.9665   0.1707
  -0.500   0.2853   0.03505   0.02529  -0.1060   0.9554   0.1629
  -0.250   0.3382   0.03409   0.02393  -0.1109   0.9419   0.1660
   0.000   0.3887   0.03345   0.02288  -0.1150   0.9280   0.1738
   0.250   0.4352   0.03287   0.02206  -0.1183   0.9144   0.1816
   0.500   0.4796   0.03241   0.02149  -0.1212   0.9007   0.1972
   0.750   0.5230   0.03186   0.02107  -0.1241   0.8875   0.2404
   1.000   0.5584   0.02992   0.02054  -0.1247   0.8751   1.0000
   1.250   0.5955   0.03048   0.02064  -0.1265   0.8613   1.0000
   1.500   0.6305   0.03106   0.02096  -0.1280   0.8481   1.0000
   1.750   0.6634   0.03166   0.02136  -0.1291   0.8355   1.0000
   2.000   0.6980   0.03215   0.02171  -0.1303   0.8240   1.0000
   2.250   0.7315   0.03264   0.02208  -0.1312   0.8130   1.0000
   2.500   0.7554   0.03353   0.02291  -0.1311   0.8004   1.0000
   2.750   0.7782   0.03454   0.02387  -0.1308   0.7883   1.0000
   3.000   0.8021   0.03553   0.02485  -0.1307   0.7771   1.0000
   3.250   0.8355   0.03596   0.02526  -0.1313   0.7683   1.0000
   3.500   0.8575   0.03707   0.02638  -0.1310   0.7574   1.0000
   3.750   0.8742   0.03857   0.02791  -0.1303   0.7459   1.0000
   4.000   0.8954   0.03984   0.02925  -0.1300   0.7359   1.0000
   4.250   0.9279   0.04028   0.02975  -0.1303   0.7276   1.0000
   4.500   0.9379   0.04238   0.03192  -0.1293   0.7160   1.0000
   4.750   0.9522   0.04421   0.03383  -0.1285   0.7053   1.0000
   5.000   0.9916   0.04409   0.03382  -0.1289   0.6980   1.0000
   5.250   0.9980   0.04653   0.03640  -0.1277   0.6857   1.0000
   5.500   1.0090   0.04854   0.03852  -0.1265   0.6734   1.0000
   5.750   1.0386   0.04850   0.03862  -0.1252   0.6589   1.0000
   6.000   1.0849   0.04623   0.03653  -0.1235   0.6426   1.0000
   6.250   1.1308   0.04369   0.03422  -0.1214   0.6266   1.0000
   6.500   1.1557   0.04357   0.03428  -0.1194   0.6105   1.0000
   6.750   1.1775   0.04377   0.03468  -0.1174   0.5935   1.0000
   7.000   1.2070   0.04305   0.03419  -0.1153   0.5764   1.0000
   7.250   1.2450   0.04127   0.03267  -0.1132   0.5586   1.0000
   7.500   1.2767   0.03996   0.03154  -0.1107   0.5366   1.0000
   7.750   1.3124   0.03696   0.02856  -0.1070   0.5035   1.0000
   8.000   1.3422   0.03474   0.02628  -0.1036   0.4680   1.0000
   8.250   1.3589   0.03454   0.02625  -0.1006   0.4358   1.0000
   8.500   1.3752   0.03449   0.02635  -0.0978   0.4044   1.0000
   8.750   1.3887   0.03436   0.02629  -0.0947   0.3712   1.0000
   9.000   1.3988   0.03474   0.02676  -0.0915   0.3388   1.0000
   9.250   1.4038   0.03551   0.02759  -0.0880   0.3035   1.0000
   9.500   1.4003   0.03672   0.02868  -0.0839   0.2618   1.0000
   9.750   1.3919   0.03875   0.03045  -0.0798   0.2221   1.0000
  10.000   1.3789   0.04141   0.03287  -0.0756   0.1911   1.0000
  10.250   1.3631   0.04492   0.03612  -0.0720   0.1625   1.0000
  10.500   1.3470   0.04900   0.03999  -0.0691   0.1363   1.0000
  10.750   1.3358   0.05303   0.04386  -0.0667   0.1159   1.0000
  11.000   1.3333   0.05644   0.04719  -0.0644   0.1013   1.0000
  11.250   1.3399   0.05917   0.04989  -0.0621   0.0907   1.0000
  11.500   1.3513   0.06148   0.05207  -0.0601   0.0821   1.0000
  11.750   1.3646   0.06412   0.05505  -0.0582   0.0755   1.0000
  12.000   1.3892   0.06634   0.05713  -0.0564   0.0699   1.0000
  12.250   1.4042   0.07010   0.06139  -0.0548   0.0679   1.0000
  12.500   1.4073   0.07446   0.06622  -0.0535   0.0670   1.0000
  12.750   1.4014   0.07920   0.07135  -0.0526   0.0666   1.0000
  13.000   1.3894   0.08434   0.07684  -0.0521   0.0665   1.0000
  13.250   1.3728   0.08993   0.08274  -0.0524   0.0667   1.0000
  13.500   1.3528   0.09602   0.08912  -0.0536   0.0671   1.0000
  13.750   1.3305   0.10269   0.09604  -0.0557   0.0675   1.0000
  14.000   1.3071   0.10995   0.10351  -0.0588   0.0681   1.0000
  14.250   1.2834   0.11783   0.11152  -0.0627   0.0687   1.0000
  14.500   1.2613   0.12616   0.11998  -0.0673   0.0694   1.0000
  14.750   1.2421   0.13466   0.12857  -0.0720   0.0700   1.0000
  15.000   1.1595   0.16415   0.15809  -0.0945   0.0801   1.0000
  15.250   1.1540   0.17258   0.16647  -0.0987   0.0811   1.0000
  15.500   1.1526   0.17983   0.17368  -0.1020   0.0817   1.0000
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