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GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 374 AIRFOIL (goe374-il)
Reynolds number: 200,000
Max Cl/Cd: 72.43 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe374-il-200000.txt
Download as CSV file: xf-goe374-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 374 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3385   0.09029   0.08694  -0.0164   1.0000   0.0213
  -7.250  -0.3386   0.08795   0.08466  -0.0166   1.0000   0.0217
  -7.000  -0.3363   0.08545   0.08221  -0.0177   1.0000   0.0220
  -6.750  -0.3306   0.08294   0.07975  -0.0199   1.0000   0.0225
  -6.500  -0.3224   0.08050   0.07733  -0.0229   1.0000   0.0228
  -6.250  -0.3116   0.07808   0.07491  -0.0266   1.0000   0.0230
  -6.000  -0.3000   0.07558   0.07239  -0.0292   1.0000   0.0231
  -5.750  -0.2883   0.07306   0.06984  -0.0311   1.0000   0.0232
  -5.500  -0.2777   0.07051   0.06724  -0.0318   1.0000   0.0233
  -5.250  -0.2672   0.06795   0.06462  -0.0321   1.0000   0.0233
  -5.000  -0.2567   0.06542   0.06201  -0.0320   1.0000   0.0234
  -4.750  -0.2566   0.06061   0.05730  -0.0304   1.0000   0.0237
  -4.500  -0.2544   0.05724   0.05398  -0.0286   1.0000   0.0240
  -4.250  -0.2263   0.05303   0.04972  -0.0323   0.9961   0.0248
  -4.000  -0.1878   0.04895   0.04553  -0.0377   0.9906   0.0259
  -3.750  -0.1440   0.04495   0.04135  -0.0435   0.9850   0.0279
  -3.500  -0.0822   0.04382   0.03959  -0.0489   0.9782   0.0312
  -3.250  -0.0522   0.03749   0.03328  -0.0530   0.9723   0.0324
  -3.000  -0.0168   0.03417   0.02987  -0.0564   0.9658   0.0341
  -2.750   0.0236   0.03139   0.02686  -0.0596   0.9589   0.0371
  -2.500   0.0709   0.02905   0.02397  -0.0623   0.9528   0.0422
  -2.250   0.1054   0.02601   0.02093  -0.0651   0.9447   0.0468
  -2.000   0.1425   0.02393   0.01859  -0.0670   0.9355   0.0584
  -1.750   0.1806   0.02201   0.01642  -0.0690   0.9265   0.0719
  -1.500   0.2139   0.02097   0.01502  -0.0696   0.9129   0.0954
  -1.250   0.2413   0.01908   0.01309  -0.0701   0.8961   0.1240
  -1.000   0.2661   0.01820   0.01214  -0.0699   0.8760   0.1792
  -0.750   0.2895   0.01614   0.01020  -0.0696   0.8558   0.2302
  -0.500   0.3167   0.01524   0.00906  -0.0685   0.8315   0.2482
  -0.250   0.3585   0.01496   0.00783  -0.0661   0.8088   0.1065
   0.000   0.3861   0.01387   0.00652  -0.0648   0.7822   0.0868
   0.250   0.4127   0.01329   0.00569  -0.0634   0.7527   0.0746
   0.500   0.4384   0.01289   0.00503  -0.0621   0.7216   0.0685
   0.750   0.4635   0.01275   0.00469  -0.0609   0.6906   0.0669
   1.000   0.4871   0.01222   0.00406  -0.0598   0.6625   0.0696
   1.250   0.5112   0.01209   0.00379  -0.0588   0.6362   0.0691
   1.500   0.5355   0.01205   0.00359  -0.0578   0.6127   0.0687
   1.750   0.5601   0.01203   0.00345  -0.0570   0.5897   0.0692
   2.000   0.5850   0.01208   0.00335  -0.0563   0.5700   0.0712
   2.250   0.6103   0.01213   0.00330  -0.0556   0.5495   0.0754
   2.500   0.6354   0.01219   0.00327  -0.0548   0.5300   0.0875
   2.750   0.6841   0.01053   0.00337  -0.0597   0.5073   1.0000
   3.000   0.7088   0.01076   0.00343  -0.0589   0.4901   1.0000
   3.250   0.7334   0.01100   0.00353  -0.0582   0.4739   1.0000
   3.500   0.7581   0.01127   0.00367  -0.0576   0.4591   1.0000
   3.750   0.7829   0.01155   0.00387  -0.0569   0.4452   1.0000
   4.000   0.8078   0.01182   0.00408  -0.0564   0.4328   1.0000
   4.250   0.8326   0.01212   0.00431  -0.0558   0.4207   1.0000
   4.500   0.8574   0.01241   0.00455  -0.0552   0.4085   1.0000
   4.750   0.8820   0.01271   0.00480  -0.0546   0.3962   1.0000
   5.000   0.9066   0.01300   0.00509  -0.0540   0.3839   1.0000
   5.250   0.9311   0.01325   0.00537  -0.0534   0.3713   1.0000
   5.500   0.9556   0.01350   0.00566  -0.0528   0.3585   1.0000
   5.750   0.9799   0.01376   0.00595  -0.0522   0.3452   1.0000
   6.000   1.0039   0.01403   0.00628  -0.0515   0.3310   1.0000
   6.250   1.0271   0.01429   0.00652  -0.0507   0.3133   1.0000
   6.500   1.0502   0.01450   0.00678  -0.0500   0.2903   1.0000
   6.750   1.0727   0.01484   0.00710  -0.0491   0.2674   1.0000
   7.000   1.0945   0.01524   0.00742  -0.0483   0.2384   1.0000
   7.250   1.1160   0.01575   0.00790  -0.0474   0.2151   1.0000
   7.500   1.1378   0.01626   0.00838  -0.0466   0.1916   1.0000
   7.750   1.1589   0.01684   0.00889  -0.0457   0.1658   1.0000
   8.000   1.1790   0.01755   0.00949  -0.0447   0.1394   1.0000
   8.250   1.1990   0.01830   0.01022  -0.0436   0.1174   1.0000
   8.500   1.2160   0.01943   0.01109  -0.0422   0.0678   1.0000
   8.750   1.2246   0.02146   0.01273  -0.0398   0.0284   1.0000
   9.000   1.2405   0.02262   0.01404  -0.0381   0.0252   1.0000
   9.250   1.2547   0.02388   0.01548  -0.0362   0.0233   1.0000
   9.500   1.2656   0.02535   0.01717  -0.0339   0.0222   1.0000
   9.750   1.2718   0.02704   0.01908  -0.0311   0.0215   1.0000
  10.000   1.2770   0.02865   0.02086  -0.0283   0.0212   1.0000
  10.250   1.2798   0.03018   0.02253  -0.0251   0.0209   1.0000
  10.500   1.2816   0.03179   0.02428  -0.0221   0.0200   1.0000
  10.750   1.2828   0.03357   0.02618  -0.0195   0.0195   1.0000
  11.000   1.2838   0.03559   0.02833  -0.0171   0.0191   1.0000
  11.250   1.2854   0.03782   0.03069  -0.0150   0.0189   1.0000
  11.500   1.2886   0.04016   0.03317  -0.0133   0.0189   1.0000
  11.750   1.2926   0.04267   0.03583  -0.0118   0.0188   1.0000
  12.000   1.2963   0.04545   0.03879  -0.0104   0.0188   1.0000
  12.250   1.2995   0.04831   0.04187  -0.0092   0.0191   1.0000
  12.500   1.2994   0.05168   0.04546  -0.0082   0.0193   1.0000
  12.750   1.2964   0.05532   0.04938  -0.0076   0.0196   1.0000
  13.000   1.2907   0.05932   0.05361  -0.0075   0.0200   1.0000
  13.250   1.2810   0.06396   0.05849  -0.0079   0.0203   1.0000
  13.500   1.2701   0.06880   0.06355  -0.0090   0.0206   1.0000
  13.750   1.2557   0.07443   0.06941  -0.0107   0.0208   1.0000
  14.000   1.2406   0.08054   0.07571  -0.0128   0.0212   1.0000
  14.250   1.2406   0.08440   0.07972  -0.0137   0.0218   1.0000
  14.500   1.2292   0.08957   0.08506  -0.0167   0.0220   1.0000
  14.750   1.2147   0.09559   0.09128  -0.0204   0.0223   1.0000
  15.000   1.1966   0.10277   0.09867  -0.0251   0.0225   1.0000
  15.250   1.1780   0.11057   0.10665  -0.0303   0.0227   1.0000
  15.500   1.1577   0.11930   0.11555  -0.0362   0.0228   1.0000
  15.750   1.1384   0.12834   0.12473  -0.0422   0.0228   1.0000
  16.000   1.1177   0.13841   0.13490  -0.0490   0.0229   1.0000
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