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

GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 407 AIRFOIL (goe407-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.64 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe407-il-1000000.txt
Download as CSV file: xf-goe407-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 407 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2326   0.10871   0.10713  -0.0368   0.9968   0.0177
 -10.500  -0.2319   0.10384   0.10226  -0.0405   0.9959   0.0179
 -10.250  -0.2266   0.09922   0.09763  -0.0438   0.9950   0.0179
 -10.000  -0.2174   0.09430   0.09271  -0.0457   0.9943   0.0181
  -9.750  -0.2034   0.09117   0.08958  -0.0469   0.9933   0.0183
  -9.500  -0.1933   0.08785   0.08626  -0.0486   0.9917   0.0184
  -9.250  -0.1823   0.08457   0.08298  -0.0505   0.9901   0.0188
  -9.000  -0.1721   0.08083   0.07925  -0.0530   0.9885   0.0190
  -8.750  -0.1613   0.07701   0.07543  -0.0558   0.9870   0.0195
  -8.500  -0.1497   0.07299   0.07141  -0.0590   0.9855   0.0201
  -8.250  -0.1469   0.06701   0.06541  -0.0661   0.9838   0.0214
  -8.000  -0.1451   0.06264   0.06105  -0.0694   0.9792   0.0215
  -7.750  -0.1395   0.05786   0.05627  -0.0745   0.9748   0.0216
  -7.500  -0.1280   0.05268   0.05107  -0.0807   0.9715   0.0216
  -7.250  -0.1272   0.04761   0.04598  -0.0827   0.9638   0.0219
  -7.000  -0.1071   0.04428   0.04263  -0.0859   0.9590   0.0221
  -6.750  -0.0895   0.04083   0.03915  -0.0892   0.9501   0.0222
  -6.500  -0.0659   0.03707   0.03533  -0.0939   0.9395   0.0225
  -6.250  -0.0416   0.03335   0.03152  -0.0985   0.9155   0.0230
  -6.000  -0.0150   0.02964   0.02752  -0.1032   0.8596   0.0237
  -5.250   0.0055   0.01744   0.01444  -0.1017   0.7859   0.0261
  -5.000   0.0179   0.01593   0.01280  -0.1002   0.7684   0.0264
  -4.750   0.0326   0.01467   0.01143  -0.0988   0.7512   0.0266
  -4.500   0.0484   0.01346   0.01008  -0.0975   0.7352   0.0269
  -4.250   0.0648   0.01225   0.00873  -0.0962   0.7202   0.0273
  -4.000   0.0818   0.01108   0.00740  -0.0948   0.7074   0.0279
  -3.750   0.0994   0.00976   0.00590  -0.0933   0.6966   0.0287
  -3.500   0.1081   0.00667   0.00217  -0.0895   0.6900   0.0316
  -3.250   0.1289   0.00621   0.00166  -0.0885   0.6805   0.0320
  -3.000   0.1497   0.00579   0.00113  -0.0874   0.6726   0.0324
  -2.750   0.1710   0.00537   0.00060  -0.0863   0.6648   0.0332
  -2.500   0.1926   0.00496   0.00004  -0.0851   0.6581   0.0344
  -2.000   0.2401   0.01383   0.00824  -0.0848   0.6528   0.0383
  -1.750   0.2636   0.01335   0.00771  -0.0839   0.6457   0.0390
  -1.500   0.2884   0.01161   0.00555  -0.0821   0.6401   0.0307
  -0.750   0.3637   0.00989   0.00358  -0.0798   0.6225   0.0306
  -0.500   0.3893   0.00972   0.00336  -0.0792   0.6170   0.0309
   0.000   0.4385   0.00903   0.00263  -0.0776   0.6061   0.0312
   0.250   0.4623   0.00874   0.00232  -0.0766   0.6000   0.0315
   0.500   0.4857   0.00855   0.00210  -0.0755   0.5940   0.0322
   0.750   0.5107   0.00839   0.00195  -0.0748   0.5882   0.0331
   1.000   0.5351   0.00830   0.00184  -0.0739   0.5815   0.0336
   1.250   0.5598   0.00823   0.00176  -0.0731   0.5748   0.0346
   1.500   0.5843   0.00817   0.00169  -0.0722   0.5656   0.0355
   1.750   0.6088   0.00814   0.00163  -0.0714   0.5553   0.0367
   2.000   0.6326   0.00812   0.00158  -0.0704   0.5435   0.0380
   2.250   0.6562   0.00813   0.00155  -0.0694   0.5291   0.0413
   2.500   0.6791   0.00814   0.00157  -0.0683   0.5089   0.0585
   2.750   0.6987   0.00812   0.00166  -0.0665   0.4800   0.1609
   3.000   0.9115   0.00758   0.00260  -0.1097   0.4084   1.0000
   3.250   0.9339   0.00777   0.00270  -0.1085   0.3921   1.0000
   3.500   0.9564   0.00796   0.00281  -0.1074   0.3773   1.0000
   3.750   0.9789   0.00814   0.00293  -0.1063   0.3634   1.0000
   4.000   1.0017   0.00831   0.00304  -0.1053   0.3526   1.0000
   4.250   1.0240   0.00849   0.00317  -0.1042   0.3418   1.0000
   4.500   1.0470   0.00864   0.00329  -0.1032   0.3324   1.0000
   4.750   1.0694   0.00881   0.00343  -0.1021   0.3230   1.0000
   5.000   1.0916   0.00900   0.00357  -0.1009   0.3133   1.0000
   5.250   1.1142   0.00916   0.00371  -0.0999   0.3052   1.0000
   5.500   1.1356   0.00937   0.00388  -0.0986   0.2952   1.0000
   5.750   1.1580   0.00953   0.00403  -0.0975   0.2866   1.0000
   6.000   1.1795   0.00974   0.00420  -0.0963   0.2776   1.0000
   6.250   1.2007   0.00995   0.00438  -0.0950   0.2677   1.0000
   6.500   1.2217   0.01016   0.00457  -0.0937   0.2569   1.0000
   6.750   1.2419   0.01041   0.00477  -0.0922   0.2454   1.0000
   7.000   1.2614   0.01069   0.00499  -0.0906   0.2329   1.0000
   7.250   1.2811   0.01095   0.00522  -0.0891   0.2215   1.0000
   7.500   1.2987   0.01130   0.00550  -0.0871   0.2038   1.0000
   7.750   1.3136   0.01179   0.00584  -0.0848   0.1767   1.0000
   8.000   1.3203   0.01268   0.00644  -0.0809   0.1301   1.0000
   8.250   1.3334   0.01321   0.00690  -0.0782   0.1157   1.0000
   8.500   1.3484   0.01362   0.00729  -0.0758   0.1076   1.0000
   8.750   1.3649   0.01393   0.00762  -0.0737   0.1037   1.0000
   9.000   1.3771   0.01432   0.00798  -0.0707   0.0981   1.0000
   9.250   1.3897   0.01460   0.00829  -0.0678   0.0940   1.0000
   9.500   1.4028   0.01487   0.00858  -0.0651   0.0901   1.0000
   9.750   1.4134   0.01527   0.00897  -0.0619   0.0843   1.0000
  10.000   1.4267   0.01561   0.00932  -0.0593   0.0785   1.0000
  10.250   1.4370   0.01609   0.00975  -0.0563   0.0699   1.0000
  10.500   1.4456   0.01669   0.01028  -0.0531   0.0578   1.0000
  10.750   1.4480   0.01762   0.01107  -0.0489   0.0400   1.0000
  11.000   1.4455   0.01882   0.01216  -0.0442   0.0231   1.0000
  11.250   1.4515   0.01966   0.01301  -0.0410   0.0193   1.0000
  11.500   1.4593   0.02044   0.01383  -0.0381   0.0178   1.0000
  11.750   1.4646   0.02141   0.01483  -0.0350   0.0162   1.0000
  12.000   1.4728   0.02226   0.01575  -0.0325   0.0155   1.0000
  12.250   1.4810   0.02315   0.01669  -0.0302   0.0147   1.0000
  12.500   1.4880   0.02417   0.01778  -0.0278   0.0144   1.0000
  12.750   1.4920   0.02544   0.01912  -0.0254   0.0137   1.0000
  13.000   1.4939   0.02697   0.02072  -0.0230   0.0131   1.0000
  13.250   1.4970   0.02851   0.02235  -0.0209   0.0126   1.0000
  13.500   1.5019   0.02999   0.02390  -0.0193   0.0124   1.0000
  13.750   1.5074   0.03149   0.02548  -0.0178   0.0121   1.0000
  14.000   1.5106   0.03326   0.02733  -0.0163   0.0118   1.0000
  14.250   1.5127   0.03519   0.02934  -0.0150   0.0115   1.0000
  14.500   1.5142   0.03726   0.03148  -0.0139   0.0113   1.0000
  14.750   1.5140   0.03958   0.03389  -0.0129   0.0110   1.0000
  15.000   1.5130   0.04208   0.03648  -0.0121   0.0109   1.0000
  15.250   1.5074   0.04516   0.03965  -0.0113   0.0106   1.0000
  15.500   1.4993   0.04864   0.04323  -0.0108   0.0104   1.0000
  15.750   1.4903   0.05234   0.04704  -0.0105   0.0102   1.0000
  16.000   1.4788   0.05645   0.05127  -0.0105   0.0101   1.0000
  16.250   1.4681   0.06066   0.05559  -0.0107   0.0100   1.0000
  16.500   1.4653   0.06397   0.05898  -0.0109   0.0099   1.0000
  16.750   1.4587   0.06785   0.06297  -0.0113   0.0098   1.0000
  17.000   1.4547   0.07147   0.06669  -0.0119   0.0097   1.0000
  17.250   1.4449   0.07606   0.07138  -0.0128   0.0096   1.0000
  17.500   1.4370   0.08042   0.07584  -0.0138   0.0095   1.0000
  17.750   1.4278   0.08508   0.08059  -0.0149   0.0094   1.0000
  18.000   1.4176   0.08997   0.08559  -0.0162   0.0093   1.0000
  18.250   1.4123   0.09416   0.08986  -0.0174   0.0091   1.0000
  18.500   1.4001   0.09943   0.09523  -0.0190   0.0090   1.0000
  18.750   1.3910   0.10426   0.10015  -0.0205   0.0090   1.0000
<< Back to GOE 407 AIRFOIL (goe407-il)

Polar data table (+)

Polar graphs


<< Back to GOE 407 AIRFOIL (goe407-il)