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GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.67 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe234-il-1000000.txt
Download as CSV file: xf-goe234-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 234 (MVA CA5) 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.1392   0.12921   0.12731  -0.0728   0.9374   0.0208
 -12.500  -0.4304   0.06271   0.06030  -0.1094   0.9193   0.0236
 -12.250  -0.4578   0.05470   0.05207  -0.1165   0.9026   0.0239
 -11.750  -0.4454   0.04802   0.04520  -0.1244   0.8785   0.0244
 -11.500  -0.4298   0.04512   0.04221  -0.1291   0.8695   0.0247
 -11.250  -0.4103   0.04248   0.03949  -0.1338   0.8615   0.0251
 -11.000  -0.3883   0.03954   0.03643  -0.1398   0.8545   0.0254
 -10.750  -0.3624   0.03673   0.03353  -0.1462   0.8486   0.0259
 -10.500  -0.3334   0.03415   0.03082  -0.1526   0.8429   0.0265
 -10.250  -0.3007   0.03153   0.02804  -0.1597   0.8378   0.0270
 -10.000  -0.2653   0.02929   0.02568  -0.1665   0.8337   0.0274
  -9.750  -0.2275   0.02690   0.02312  -0.1737   0.8293   0.0280
  -9.500  -0.1931   0.02563   0.02179  -0.1777   0.8250   0.0287
  -9.250  -0.1572   0.02449   0.02060  -0.1820   0.8207   0.0292
  -9.000  -0.1197   0.02326   0.01932  -0.1866   0.8175   0.0298
  -8.750  -0.0820   0.02208   0.01806  -0.1910   0.8137   0.0305
  -8.500  -0.0454   0.02111   0.01701  -0.1946   0.8098   0.0311
  -8.250  -0.0092   0.02025   0.01604  -0.1979   0.8058   0.0316
  -8.000   0.0282   0.01937   0.01506  -0.2016   0.8021   0.0321
  -7.750   0.0617   0.01880   0.01446  -0.2034   0.7986   0.0330
  -7.500   0.0967   0.01820   0.01384  -0.2058   0.7947   0.0337
  -7.250   0.1319   0.01759   0.01319  -0.2083   0.7907   0.0344
  -7.000   0.1669   0.01705   0.01257  -0.2107   0.7866   0.0351
  -6.750   0.2020   0.01650   0.01198  -0.2130   0.7829   0.0359
  -6.500   0.2371   0.01595   0.01140  -0.2152   0.7788   0.0367
  -6.250   0.2717   0.01544   0.01083  -0.2173   0.7744   0.0374
  -6.000   0.3071   0.01497   0.01029  -0.2195   0.7699   0.0385
  -5.750   0.3430   0.01439   0.00968  -0.2220   0.7657   0.0396
  -5.500   0.3783   0.01383   0.00909  -0.2243   0.7611   0.0407
  -5.250   0.4131   0.01331   0.00851  -0.2264   0.7560   0.0419
  -5.000   0.4469   0.01289   0.00801  -0.2281   0.7506   0.0431
  -4.750   0.4837   0.01217   0.00723  -0.2308   0.7457   0.0449
  -4.500   0.5190   0.01155   0.00656  -0.2330   0.7399   0.0469
  -4.250   0.5523   0.01112   0.00605  -0.2345   0.7338   0.0489
  -4.000   0.5849   0.01077   0.00564  -0.2358   0.7276   0.0505
  -3.750   0.6205   0.01000   0.00479  -0.2381   0.7203   0.0547
  -3.500   0.6521   0.00973   0.00444  -0.2390   0.7130   0.0580
  -3.250   0.6846   0.00935   0.00401  -0.2402   0.7038   0.0636
  -3.000   0.7154   0.00921   0.00378  -0.2408   0.6937   0.0681
  -2.750   0.7470   0.00894   0.00344  -0.2417   0.6833   0.0787
  -2.500   0.7817   0.00814   0.00281  -0.2439   0.6745   0.1827
  -2.250   0.8121   0.00794   0.00271  -0.2446   0.6647   0.2586
  -2.000   0.8414   0.00801   0.00276  -0.2447   0.6552   0.2709
  -1.750   0.8701   0.00814   0.00282  -0.2447   0.6453   0.2786
  -1.500   0.8990   0.00825   0.00287  -0.2447   0.6342   0.2840
  -1.250   0.9275   0.00842   0.00300  -0.2447   0.6230   0.2896
  -0.750   0.9848   0.00871   0.00317  -0.2446   0.6059   0.2961
  -0.500   1.0138   0.00877   0.00321  -0.2447   0.5991   0.2991
  -0.250   1.0424   0.00889   0.00331  -0.2447   0.5929   0.3016
   0.000   1.0713   0.00899   0.00340  -0.2448   0.5868   0.3036
   0.250   1.0996   0.00913   0.00351  -0.2448   0.5803   0.3060
   0.500   1.1281   0.00927   0.00364  -0.2447   0.5745   0.3088
   0.750   1.1567   0.00938   0.00373  -0.2448   0.5683   0.3108
   1.000   1.1848   0.00952   0.00382  -0.2447   0.5618   0.3120
   1.250   1.2137   0.00953   0.00382  -0.2449   0.5560   0.3141
   1.500   1.2422   0.00959   0.00387  -0.2449   0.5495   0.3155
   2.000   1.2985   0.00978   0.00405  -0.2449   0.5367   0.3180
   2.250   1.3263   0.00992   0.00417  -0.2448   0.5295   0.3196
   2.500   1.3539   0.01006   0.00430  -0.2447   0.5224   0.3214
   2.750   1.3816   0.01018   0.00441  -0.2446   0.5144   0.3232
   3.000   1.4088   0.01033   0.00453  -0.2445   0.5062   0.3245
   3.250   1.4363   0.01045   0.00463  -0.2444   0.4974   0.3258
   3.500   1.4630   0.01063   0.00476  -0.2441   0.4869   0.3269
   3.750   1.4890   0.01085   0.00492  -0.2438   0.4741   0.3278
   4.000   1.5157   0.01101   0.00505  -0.2435   0.4622   0.3287
   4.250   1.5413   0.01121   0.00519  -0.2432   0.4462   0.3310
   4.500   1.5655   0.01153   0.00543  -0.2425   0.4263   0.3324
   4.750   1.5892   0.01189   0.00570  -0.2418   0.4070   0.3337
   5.000   1.6121   0.01229   0.00600  -0.2409   0.3856   0.3351
   5.250   1.6338   0.01275   0.00636  -0.2399   0.3621   0.3364
   5.500   1.6539   0.01331   0.00677  -0.2385   0.3384   0.3378
   5.750   1.6743   0.01380   0.00717  -0.2372   0.3181   0.3393
   6.000   1.6942   0.01429   0.00758  -0.2358   0.3009   0.3408
   6.250   1.7135   0.01478   0.00799  -0.2343   0.2861   0.3423
   6.500   1.7313   0.01529   0.00842  -0.2325   0.2723   0.3436
   6.750   1.7501   0.01571   0.00881  -0.2309   0.2622   0.3445
   7.000   1.7677   0.01614   0.00921  -0.2291   0.2535   0.3459
   7.250   1.7844   0.01652   0.00960  -0.2271   0.2465   0.3479
   7.500   1.7953   0.01704   0.01011  -0.2240   0.2395   0.3492
   7.750   1.8122   0.01748   0.01057  -0.2221   0.2339   0.3506
   8.000   1.8270   0.01807   0.01116  -0.2199   0.2273   0.3520
   8.250   1.8431   0.01861   0.01171  -0.2180   0.2217   0.3534
   8.500   1.8587   0.01919   0.01230  -0.2160   0.2154   0.3549
   8.750   1.8717   0.01994   0.01304  -0.2138   0.2076   0.3563
   9.000   1.8856   0.02066   0.01375  -0.2117   0.1982   0.3578
   9.250   1.8971   0.02154   0.01460  -0.2093   0.1864   0.3592
   9.500   1.8985   0.02312   0.01599  -0.2056   0.1583   0.3603
   9.750   1.8724   0.02670   0.01919  -0.1986   0.1038   0.3606
  10.250   1.8447   0.03292   0.02504  -0.1892   0.0401   0.3615
  10.500   1.8490   0.03473   0.02688  -0.1869   0.0348   0.3633
  10.750   1.8546   0.03649   0.02867  -0.1848   0.0325   0.3648
  11.000   1.8609   0.03822   0.03046  -0.1828   0.0308   0.3662
  11.250   1.8692   0.03978   0.03210  -0.1811   0.0299   0.3675
  11.500   1.8754   0.04157   0.03396  -0.1793   0.0289   0.3688
  11.750   1.8803   0.04354   0.03598  -0.1774   0.0280   0.3701
  12.000   1.8835   0.04573   0.03824  -0.1755   0.0269   0.3713
  12.250   1.8851   0.04814   0.04073  -0.1737   0.0260   0.3726
  12.500   1.8917   0.05008   0.04274  -0.1723   0.0255   0.3740
  12.750   1.8972   0.05215   0.04488  -0.1708   0.0250   0.3753
  13.000   1.9010   0.05445   0.04725  -0.1694   0.0244   0.3765
  13.250   1.9042   0.05686   0.04974  -0.1680   0.0237   0.3775
  13.500   1.9058   0.05952   0.05246  -0.1667   0.0231   0.3788
  13.750   1.9043   0.06262   0.05564  -0.1654   0.0224   0.3806
  14.000   1.8972   0.06644   0.05958  -0.1640   0.0217   0.3818
  14.250   1.9002   0.06909   0.06231  -0.1631   0.0214   0.3832
  14.500   1.9027   0.07181   0.06512  -0.1622   0.0211   0.3845
  14.750   1.9037   0.07477   0.06816  -0.1613   0.0206   0.3859
  15.000   1.9032   0.07796   0.07144  -0.1606   0.0202   0.3873
  15.250   1.9022   0.08123   0.07479  -0.1599   0.0197   0.3886
  15.500   1.9006   0.08459   0.07822  -0.1592   0.0193   0.3899
  15.750   1.8962   0.08838   0.08208  -0.1587   0.0189   0.3911
  16.000   1.8883   0.09272   0.08651  -0.1582   0.0184   0.3920
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