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GOE 523 AIRFOIL (goe523-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 523 AIRFOIL (goe523-il)
Reynolds number: 500,000
Max Cl/Cd: 90.61 at α=0.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe523-il-500000-n5.txt
Download as CSV file: xf-goe523-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 523 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750   0.3511   0.09297   0.08982  -0.1835   0.9020   0.0217
 -11.500   0.3641   0.08991   0.08672  -0.1863   0.8977   0.0227
 -11.250   0.3594   0.08457   0.08135  -0.1889   0.8920   0.0235
 -11.000   0.3706   0.08278   0.07955  -0.1897   0.8864   0.0237
 -10.750   0.3872   0.08109   0.07784  -0.1913   0.8817   0.0240
 -10.500   0.3973   0.07898   0.07570  -0.1924   0.8761   0.0241
 -10.250   0.4073   0.07720   0.07391  -0.1929   0.8694   0.0245
  -9.250   0.1551   0.03129   0.02736  -0.2147   0.8224   0.0273
  -9.000   0.1676   0.02545   0.02118  -0.2275   0.8141   0.0274
  -8.750   0.1993   0.02250   0.01801  -0.2360   0.8078   0.0276
  -8.500   0.2334   0.02072   0.01606  -0.2415   0.8000   0.0279
  -8.250   0.2660   0.01951   0.01467  -0.2450   0.7916   0.0281
  -8.000   0.2968   0.01851   0.01351  -0.2474   0.7812   0.0284
  -7.750   0.3275   0.01770   0.01256  -0.2494   0.7715   0.0287
  -7.500   0.3584   0.01700   0.01170  -0.2512   0.7621   0.0291
  -7.250   0.3887   0.01634   0.01090  -0.2527   0.7523   0.0295
  -7.000   0.4187   0.01572   0.01011  -0.2539   0.7419   0.0299
  -6.750   0.4480   0.01518   0.00942  -0.2548   0.7302   0.0302
  -6.500   0.4765   0.01472   0.00881  -0.2555   0.7178   0.0305
  -6.250   0.5039   0.01435   0.00828  -0.2559   0.7043   0.0308
  -6.000   0.5305   0.01406   0.00783  -0.2559   0.6908   0.0311
  -5.750   0.5577   0.01380   0.00744  -0.2561   0.6785   0.0313
  -5.500   0.5849   0.01352   0.00704  -0.2563   0.6674   0.0316
  -5.000   0.6393   0.01307   0.00643  -0.2567   0.6467   0.0324
  -4.500   0.6941   0.01280   0.00601  -0.2569   0.6309   0.0334
  -4.250   0.7207   0.01270   0.00585  -0.2568   0.6235   0.0340
  -4.000   0.7472   0.01263   0.00570  -0.2567   0.6168   0.0348
  -3.750   0.7741   0.01254   0.00555  -0.2567   0.6098   0.0354
  -3.500   0.7999   0.01251   0.00544  -0.2564   0.6029   0.0359
  -3.250   0.8280   0.01240   0.00529  -0.2566   0.5974   0.0367
  -3.000   0.8555   0.01233   0.00519  -0.2567   0.5915   0.0376
  -2.750   0.8813   0.01233   0.00514  -0.2564   0.5853   0.0385
  -2.500   0.9072   0.01234   0.00509  -0.2561   0.5795   0.0397
  -2.250   0.9335   0.01234   0.00506  -0.2559   0.5730   0.0409
  -2.000   0.9588   0.01238   0.00505  -0.2555   0.5663   0.0429
  -1.750   0.9846   0.01243   0.00507  -0.2552   0.5606   0.0460
  -1.500   1.0108   0.01246   0.00509  -0.2550   0.5540   0.0513
  -1.250   1.0352   0.01254   0.00516  -0.2545   0.5468   0.0618
  -1.000   1.0615   0.01257   0.00522  -0.2544   0.5400   0.0838
  -0.750   1.0868   0.01263   0.00534  -0.2541   0.5323   0.1170
  -0.500   1.1103   0.01277   0.00548  -0.2534   0.5254   0.1386
  -0.250   1.1347   0.01289   0.00560  -0.2529   0.5174   0.1556
   0.000   1.1563   0.01309   0.00578  -0.2519   0.5091   0.1731
   0.250   1.1813   0.01318   0.00594  -0.2516   0.5009   0.2127
   0.500   1.2036   0.01337   0.00619  -0.2508   0.4926   0.2677
   0.750   1.2269   0.01354   0.00641  -0.2501   0.4847   0.3064
   1.000   1.2477   0.01380   0.00668  -0.2491   0.4760   0.3379
   1.250   1.2698   0.01404   0.00693  -0.2482   0.4684   0.3627
   1.500   1.2907   0.01434   0.00721  -0.2471   0.4604   0.3813
   1.750   1.3114   0.01465   0.00752  -0.2460   0.4530   0.4028
   2.000   1.3320   0.01497   0.00784  -0.2449   0.4450   0.4273
   2.250   1.3512   0.01537   0.00821  -0.2435   0.4379   0.4479
   2.500   1.3730   0.01566   0.00852  -0.2426   0.4316   0.4672
   2.750   1.3930   0.01604   0.00888  -0.2414   0.4253   0.4842
   3.000   1.4122   0.01646   0.00928  -0.2401   0.4201   0.4977
   3.250   1.4337   0.01678   0.00961  -0.2392   0.4151   0.5110
   3.500   1.4541   0.01716   0.00999  -0.2381   0.4100   0.5234
   3.750   1.4734   0.01760   0.01041  -0.2369   0.4055   0.5346
   4.000   1.4932   0.01801   0.01083  -0.2358   0.4016   0.5451
   4.250   1.5142   0.01838   0.01121  -0.2348   0.3977   0.5545
   4.500   1.5342   0.01879   0.01164  -0.2338   0.3935   0.5634
   4.750   1.5530   0.01928   0.01211  -0.2326   0.3891   0.5718
   5.000   1.5708   0.01982   0.01265  -0.2312   0.3849   0.5785
   5.250   1.5912   0.02023   0.01308  -0.2303   0.3811   0.5856
   5.500   1.6104   0.02071   0.01357  -0.2292   0.3767   0.5919
   5.750   1.6286   0.02125   0.01412  -0.2280   0.3724   0.5971
   6.000   1.6452   0.02189   0.01474  -0.2266   0.3685   0.6025
   6.250   1.6644   0.02239   0.01527  -0.2255   0.3652   0.6085
   6.500   1.6835   0.02290   0.01582  -0.2245   0.3615   0.6139
   6.750   1.7013   0.02349   0.01644  -0.2234   0.3575   0.6204
   7.000   1.7166   0.02424   0.01718  -0.2219   0.3530   0.6281
   7.250   1.7329   0.02494   0.01790  -0.2206   0.3487   0.6351
   7.500   1.7504   0.02558   0.01858  -0.2194   0.3435   0.6423
   7.750   1.7648   0.02643   0.01942  -0.2180   0.3377   0.6481
   8.000   1.7785   0.02733   0.02033  -0.2164   0.3328   0.6528
   8.250   1.7958   0.02802   0.02107  -0.2154   0.3285   0.6581
   8.500   1.8109   0.02887   0.02195  -0.2141   0.3240   0.6630
   8.750   1.8238   0.02990   0.02298  -0.2126   0.3193   0.6671
   9.000   1.8385   0.03081   0.02393  -0.2114   0.3151   0.6720
   9.250   1.8535   0.03173   0.02488  -0.2102   0.3107   0.6777
   9.500   1.8667   0.03279   0.02598  -0.2089   0.3061   0.6828
   9.750   1.8783   0.03400   0.02721  -0.2074   0.3018   0.6878
  10.000   1.8922   0.03507   0.02833  -0.2063   0.2981   0.6934
  10.250   1.9058   0.03617   0.02948  -0.2051   0.2937   0.6991
  10.500   1.9164   0.03755   0.03089  -0.2037   0.2886   0.7054
  10.750   1.9255   0.03909   0.03245  -0.2023   0.2832   0.7125
  11.000   1.9368   0.04048   0.03389  -0.2011   0.2769   0.7200
  11.250   1.9426   0.04238   0.03580  -0.1995   0.2705   0.7281
  11.500   1.9531   0.04391   0.03739  -0.1984   0.2656   0.7381
  11.750   1.9617   0.04562   0.03917  -0.1971   0.2600   0.7519
  12.000   1.9662   0.04773   0.04133  -0.1956   0.2542   0.7788
  12.250   1.9718   0.04926   0.04303  -0.1939   0.2499   1.0000
  12.500   1.9795   0.05116   0.04497  -0.1928   0.2450   1.0000
  12.750   1.9829   0.05356   0.04739  -0.1915   0.2398   1.0000
  13.000   1.9882   0.05581   0.04968  -0.1904   0.2351   1.0000
  13.250   1.9942   0.05801   0.05193  -0.1894   0.2298   1.0000
  13.500   1.9955   0.06081   0.05475  -0.1883   0.2247   1.0000
  13.750   1.9989   0.06341   0.05739  -0.1874   0.2202   1.0000
  14.000   2.0033   0.06591   0.05994  -0.1865   0.2151   1.0000
  14.250   2.0026   0.06909   0.06317  -0.1856   0.2099   1.0000
  14.500   2.0035   0.07213   0.06625  -0.1849   0.2048   1.0000
  14.750   2.0032   0.07537   0.06953  -0.1842   0.1977   1.0000
  15.000   1.9986   0.07923   0.07342  -0.1835   0.1916   1.0000
  15.250   1.9963   0.08281   0.07705  -0.1830   0.1836   1.0000
  15.500   1.9885   0.08721   0.08147  -0.1825   0.1742   1.0000
  15.750   1.9761   0.09234   0.08659  -0.1822   0.1615   1.0000
  16.000   1.9458   0.10024   0.09442  -0.1821   0.1383   1.0000
  16.250   1.9099   0.10916   0.10327  -0.1825   0.1131   1.0000
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