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GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 622 AIRFOIL (goe622-il)
Reynolds number: 200,000
Max Cl/Cd: 69.82 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe622-il-200000.txt
Download as CSV file: xf-goe622-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 622 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3870   0.10179   0.09839  -0.0158   1.0000   0.0465
  -9.500  -0.3864   0.09802   0.09464  -0.0168   1.0000   0.0481
  -9.250  -0.5084   0.10317   0.09967  -0.0116   1.0000   0.0425
  -9.000  -0.4971   0.10070   0.09717  -0.0100   1.0000   0.0446
  -8.750  -0.4927   0.09733   0.09382  -0.0112   1.0000   0.0463
  -8.500  -0.4902   0.09364   0.09016  -0.0131   1.0000   0.0478
  -8.250  -0.4894   0.08972   0.08629  -0.0158   1.0000   0.0496
  -8.000  -0.4936   0.08535   0.08198  -0.0211   1.0000   0.0515
  -7.750  -0.4940   0.07860   0.07521  -0.0350   1.0000   0.0527
  -7.500  -0.4895   0.07322   0.06972  -0.0404   1.0000   0.0530
  -7.250  -0.4897   0.06719   0.06377  -0.0397   1.0000   0.0541
  -7.000  -0.4807   0.06464   0.06125  -0.0382   1.0000   0.0553
  -6.750  -0.4715   0.06167   0.05827  -0.0381   1.0000   0.0568
  -6.500  -0.4625   0.05802   0.05456  -0.0392   1.0000   0.0591
  -6.250  -0.4525   0.05333   0.04914  -0.0439   1.0000   0.0655
  -6.000  -0.4470   0.04719   0.04319  -0.0433   1.0000   0.0672
  -5.750  -0.4409   0.03413   0.02933  -0.0428   1.0000   0.0379
  -5.500  -0.4283   0.02890   0.02353  -0.0415   1.0000   0.0362
  -5.250  -0.4111   0.02586   0.02001  -0.0401   1.0000   0.0378
  -5.000  -0.3915   0.02281   0.01642  -0.0388   1.0000   0.0383
  -4.750  -0.3696   0.02053   0.01367  -0.0377   1.0000   0.0393
  -4.500  -0.3465   0.01917   0.01194  -0.0366   1.0000   0.0408
  -4.250  -0.3229   0.01729   0.00994  -0.0362   1.0000   0.0457
  -4.000  -0.2987   0.01638   0.00886  -0.0355   1.0000   0.0505
  -3.750  -0.2732   0.01516   0.00754  -0.0350   1.0000   0.0565
  -3.500  -0.2488   0.01479   0.00708  -0.0345   1.0000   0.0658
  -3.250  -0.2234   0.01425   0.00656  -0.0342   1.0000   0.0773
  -3.000  -0.1985   0.01396   0.00624  -0.0339   1.0000   0.0918
  -2.750  -0.1635   0.01340   0.00579  -0.0358   0.9974   0.1164
  -2.500  -0.1227   0.01285   0.00532  -0.0387   0.9934   0.1493
  -2.250  -0.0831   0.01242   0.00500  -0.0415   0.9879   0.1800
  -2.000  -0.0411   0.01199   0.00475  -0.0448   0.9835   0.2191
  -1.750  -0.0048   0.01110   0.00455  -0.0472   0.9770   0.3637
  -1.500   0.0211   0.00942   0.00470  -0.0460   0.9734   0.8408
  -1.250   0.0778   0.00927   0.00451  -0.0514   0.9710   1.0000
  -1.000   0.1180   0.00923   0.00433  -0.0540   0.9625   1.0000
  -0.750   0.1649   0.00915   0.00412  -0.0579   0.9574   1.0000
  -0.500   0.2030   0.00907   0.00395  -0.0600   0.9476   1.0000
  -0.250   0.2423   0.00896   0.00378  -0.0622   0.9385   1.0000
   0.000   0.2809   0.00884   0.00358  -0.0641   0.9291   1.0000
   0.250   0.3132   0.00873   0.00342  -0.0645   0.9152   1.0000
   0.500   0.3402   0.00864   0.00326  -0.0636   0.8950   1.0000
   0.750   0.3658   0.00857   0.00310  -0.0624   0.8738   1.0000
   1.000   0.3900   0.00857   0.00303  -0.0611   0.8519   1.0000
   1.250   0.4147   0.00859   0.00296  -0.0599   0.8310   1.0000
   1.500   0.4394   0.00862   0.00293  -0.0588   0.8085   1.0000
   1.750   0.4648   0.00868   0.00290  -0.0579   0.7879   1.0000
   2.000   0.4902   0.00876   0.00293  -0.0571   0.7659   1.0000
   2.250   0.5156   0.00885   0.00293  -0.0563   0.7435   1.0000
   2.500   0.5411   0.00897   0.00298  -0.0556   0.7198   1.0000
   2.750   0.5668   0.00911   0.00307  -0.0549   0.6981   1.0000
   3.000   0.5922   0.00928   0.00316  -0.0542   0.6749   1.0000
   3.250   0.6176   0.00948   0.00328  -0.0535   0.6513   1.0000
   3.500   0.6431   0.00970   0.00343  -0.0528   0.6289   1.0000
   3.750   0.6682   0.00994   0.00362  -0.0521   0.6042   1.0000
   4.000   0.6932   0.01018   0.00381  -0.0514   0.5775   1.0000
   4.250   0.7181   0.01044   0.00402  -0.0507   0.5504   1.0000
   4.500   0.7430   0.01069   0.00425  -0.0500   0.5225   1.0000
   4.750   0.7673   0.01099   0.00451  -0.0492   0.4886   1.0000
   5.000   0.7902   0.01134   0.00472  -0.0482   0.4324   1.0000
   5.250   0.8110   0.01197   0.00499  -0.0470   0.3532   1.0000
   5.500   0.8315   0.01277   0.00544  -0.0460   0.2868   1.0000
   5.750   0.8533   0.01350   0.00595  -0.0451   0.2375   1.0000
   6.000   0.8762   0.01413   0.00649  -0.0445   0.2005   1.0000
   6.250   0.8989   0.01479   0.00701  -0.0438   0.1622   1.0000
   6.500   0.9201   0.01567   0.00765  -0.0430   0.1183   1.0000
   6.750   0.9365   0.01737   0.00885  -0.0414   0.0474   1.0000
   7.000   0.9555   0.01869   0.01020  -0.0399   0.0372   1.0000
   7.250   0.9766   0.01965   0.01131  -0.0387   0.0332   1.0000
   7.500   0.9953   0.02086   0.01255  -0.0374   0.0294   1.0000
   7.750   1.0124   0.02240   0.01418  -0.0357   0.0276   1.0000
   8.000   1.0314   0.02381   0.01571  -0.0343   0.0266   1.0000
   8.250   1.0507   0.02544   0.01746  -0.0329   0.0257   1.0000
   8.500   1.0707   0.02732   0.01947  -0.0316   0.0251   1.0000
   8.750   1.0910   0.02949   0.02186  -0.0303   0.0248   1.0000
   9.000   1.1103   0.03160   0.02421  -0.0290   0.0240   1.0000
   9.250   1.1276   0.03345   0.02625  -0.0278   0.0228   1.0000
   9.500   1.1431   0.03590   0.02894  -0.0264   0.0222   1.0000
   9.750   1.1550   0.03920   0.03267  -0.0244   0.0225   1.0000
  10.000   1.1580   0.04372   0.03780  -0.0215   0.0235   1.0000
  10.250   1.1516   0.04881   0.04348  -0.0183   0.0248   1.0000
  10.500   1.1415   0.05351   0.04857  -0.0154   0.0258   1.0000
  10.750   1.1267   0.05767   0.05301  -0.0124   0.0266   1.0000
  11.000   1.1085   0.06184   0.05739  -0.0100   0.0271   1.0000
  11.250   1.0892   0.06663   0.06236  -0.0090   0.0276   1.0000
  11.500   0.9786   0.05968   0.05570   0.0004   0.0263   1.0000
  11.750   0.9529   0.06537   0.06156  -0.0006   0.0264   1.0000
  12.000   0.9260   0.07182   0.06817  -0.0027   0.0265   1.0000
  12.250   0.8984   0.07894   0.07544  -0.0058   0.0265   1.0000
  12.500   0.8704   0.08673   0.08335  -0.0097   0.0266   1.0000
  12.750   0.8402   0.09545   0.09218  -0.0146   0.0267   1.0000
  13.000   0.8085   0.10517   0.10198  -0.0201   0.0270   1.0000
  13.250   0.7784   0.11467   0.11148  -0.0249   0.0276   1.0000
  13.500   0.7154   0.13176   0.12857  -0.0314   0.0374   1.0000
  15.250   0.8921   0.19338   0.18985  -0.0779   0.0460   1.0000
  15.500   0.8960   0.19774   0.19420  -0.0806   0.0440   1.0000
  15.750   0.6848   0.17357   0.17035  -0.0444   0.0489   1.0000
  16.000   0.6816   0.17691   0.17369  -0.0465   0.0487   1.0000
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