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GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.9 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe242-il-1000000-n5.txt
Download as CSV file: xf-goe242-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 242 (MVA PR.2) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.5768   0.05604   0.05309  -0.1065   0.8252   0.0089
 -13.750  -0.5933   0.04910   0.04598  -0.1128   0.8185   0.0089
 -13.500  -0.5998   0.04403   0.04076  -0.1177   0.8123   0.0090
 -13.250  -0.6006   0.03995   0.03656  -0.1220   0.8057   0.0090
 -13.000  -0.5971   0.03664   0.03310  -0.1260   0.7989   0.0091
 -12.750  -0.5837   0.03345   0.02979  -0.1314   0.7929   0.0093
 -12.500  -0.5641   0.03060   0.02683  -0.1371   0.7859   0.0096
 -12.250  -0.5392   0.02833   0.02446  -0.1423   0.7791   0.0099
 -12.000  -0.5110   0.02646   0.02250  -0.1471   0.7710   0.0102
 -11.750  -0.4808   0.02481   0.02073  -0.1516   0.7623   0.0106
 -11.500  -0.4488   0.02331   0.01912  -0.1560   0.7515   0.0110
 -11.250  -0.4155   0.02190   0.01758  -0.1604   0.7398   0.0114
 -11.000  -0.3812   0.02062   0.01614  -0.1646   0.7260   0.0118
 -10.750  -0.3465   0.01956   0.01496  -0.1684   0.7081   0.0123
 -10.500  -0.3128   0.01884   0.01412  -0.1713   0.6865   0.0127
 -10.250  -0.2791   0.01821   0.01335  -0.1740   0.6660   0.0132
 -10.000  -0.2449   0.01756   0.01257  -0.1768   0.6488   0.0138
  -9.750  -0.2100   0.01687   0.01174  -0.1797   0.6350   0.0143
  -9.500  -0.1746   0.01617   0.01089  -0.1826   0.6239   0.0148
  -9.250  -0.1403   0.01570   0.01035  -0.1849   0.6147   0.0153
  -9.000  -0.1074   0.01543   0.01002  -0.1866   0.6061   0.0158
  -8.750  -0.0746   0.01518   0.00970  -0.1881   0.5990   0.0164
  -8.500  -0.0418   0.01489   0.00934  -0.1897   0.5923   0.0170
  -8.250  -0.0089   0.01455   0.00890  -0.1913   0.5863   0.0176
  -8.000   0.0244   0.01417   0.00843  -0.1929   0.5817   0.0181
  -7.750   0.0576   0.01380   0.00799  -0.1945   0.5769   0.0186
  -7.500   0.0901   0.01357   0.00772  -0.1958   0.5721   0.0191
  -7.250   0.1217   0.01343   0.00753  -0.1969   0.5680   0.0195
  -7.000   0.1539   0.01323   0.00729  -0.1980   0.5645   0.0200
  -6.750   0.1863   0.01298   0.00700  -0.1992   0.5608   0.0206
  -6.500   0.2185   0.01277   0.00671  -0.2004   0.5571   0.0213
  -6.250   0.2504   0.01258   0.00646  -0.2014   0.5535   0.0219
  -6.000   0.2826   0.01237   0.00619  -0.2025   0.5506   0.0223
  -5.750   0.3152   0.01212   0.00589  -0.2037   0.5478   0.0227
  -5.500   0.3493   0.01174   0.00548  -0.2054   0.5447   0.0234
  -5.250   0.3816   0.01153   0.00524  -0.2066   0.5415   0.0239
  -5.000   0.4139   0.01135   0.00501  -0.2077   0.5383   0.0244
  -4.500   0.4781   0.01101   0.00460  -0.2098   0.5334   0.0256
  -4.250   0.5104   0.01084   0.00439  -0.2109   0.5314   0.0261
  -4.000   0.5425   0.01068   0.00419  -0.2119   0.5292   0.0265
  -3.750   0.5743   0.01054   0.00401  -0.2128   0.5269   0.0269
  -3.500   0.6059   0.01043   0.00386  -0.2137   0.5247   0.0273
  -3.250   0.6371   0.01035   0.00374  -0.2145   0.5225   0.0275
  -3.000   0.6695   0.01018   0.00352  -0.2156   0.5203   0.0286
  -2.750   0.7009   0.01009   0.00339  -0.2164   0.5183   0.0294
  -2.500   0.7321   0.01001   0.00330  -0.2172   0.5169   0.0301
  -2.250   0.7630   0.00994   0.00322  -0.2178   0.5151   0.0308
  -2.000   0.7937   0.00990   0.00315  -0.2185   0.5132   0.0315
  -1.750   0.8242   0.00987   0.00310  -0.2191   0.5105   0.0324
  -1.500   0.8542   0.00987   0.00307  -0.2196   0.5065   0.0332
  -1.250   0.8840   0.00990   0.00305  -0.2200   0.5013   0.0344
  -1.000   0.9144   0.00987   0.00301  -0.2206   0.4970   0.0381
  -0.750   0.9492   0.00947   0.00291  -0.2226   0.4933   0.1836
  -0.500   0.9802   0.00938   0.00290  -0.2234   0.4908   0.2267
  -0.250   1.0129   0.00910   0.00290  -0.2249   0.4879   0.3597
   0.000   1.0423   0.00915   0.00297  -0.2252   0.4852   0.3839
   0.250   1.0717   0.00919   0.00303  -0.2256   0.4827   0.3956
   0.500   1.1008   0.00925   0.00310  -0.2259   0.4794   0.4068
   0.750   1.1296   0.00933   0.00318  -0.2261   0.4753   0.4151
   1.000   1.1581   0.00944   0.00325  -0.2263   0.4715   0.4206
   1.250   1.1869   0.00952   0.00333  -0.2265   0.4690   0.4247
   1.500   1.2157   0.00958   0.00342  -0.2268   0.4666   0.4316
   1.750   1.2444   0.00966   0.00351  -0.2270   0.4636   0.4358
   2.000   1.2729   0.00976   0.00359  -0.2272   0.4602   0.4377
   2.250   1.3011   0.00986   0.00369  -0.2274   0.4566   0.4401
   2.500   1.3292   0.00997   0.00379  -0.2276   0.4531   0.4427
   2.750   1.3576   0.01006   0.00390  -0.2277   0.4487   0.4457
   3.000   1.3853   0.01018   0.00401  -0.2279   0.4427   0.4485
   3.250   1.4128   0.01033   0.00414  -0.2279   0.4368   0.4515
   3.500   1.4403   0.01046   0.00426  -0.2280   0.4296   0.4538
   3.750   1.4672   0.01064   0.00441  -0.2280   0.4215   0.4557
   4.000   1.4936   0.01084   0.00459  -0.2279   0.4097   0.4581
   4.250   1.5184   0.01117   0.00483  -0.2275   0.3908   0.4610
   4.500   1.5395   0.01179   0.00526  -0.2266   0.3572   0.4640
   4.750   1.5599   0.01243   0.00574  -0.2255   0.3297   0.4664
   5.000   1.5819   0.01292   0.00614  -0.2247   0.3117   0.4686
   5.250   1.6039   0.01338   0.00652  -0.2239   0.2975   0.4706
   5.500   1.6254   0.01385   0.00692  -0.2230   0.2838   0.4727
   5.750   1.6458   0.01435   0.00735  -0.2220   0.2690   0.4750
   6.000   1.6660   0.01483   0.00778  -0.2209   0.2553   0.4773
   6.250   1.6858   0.01529   0.00820  -0.2197   0.2436   0.4795
   6.500   1.7039   0.01582   0.00867  -0.2183   0.2318   0.4818
   6.750   1.7195   0.01640   0.00920  -0.2164   0.2198   0.4840
   7.000   1.7321   0.01696   0.00972  -0.2139   0.2098   0.4860
   7.250   1.7444   0.01751   0.01026  -0.2114   0.2020   0.4878
   7.500   1.7560   0.01825   0.01096  -0.2089   0.1919   0.4898
   7.750   1.7666   0.01909   0.01176  -0.2065   0.1796   0.4923
   8.000   1.7727   0.02024   0.01283  -0.2035   0.1631   0.4947
   8.250   1.7505   0.02327   0.01557  -0.1971   0.1127   0.4963
   8.500   1.7348   0.02625   0.01842  -0.1922   0.0755   0.4980
   8.750   1.7379   0.02804   0.02020  -0.1898   0.0634   0.5002
   9.000   1.7428   0.02975   0.02192  -0.1877   0.0552   0.5023
   9.250   1.7456   0.03170   0.02385  -0.1855   0.0460   0.5041
   9.500   1.7398   0.03449   0.02657  -0.1828   0.0263   0.5057
   9.750   1.7364   0.03715   0.02925  -0.1804   0.0147   0.5076
  10.000   1.7411   0.03916   0.03132  -0.1789   0.0127   0.5100
  10.250   1.7473   0.04107   0.03330  -0.1775   0.0117   0.5124
  10.500   1.7527   0.04310   0.03539  -0.1762   0.0110   0.5150
  10.750   1.7569   0.04530   0.03766  -0.1749   0.0103   0.5176
  11.000   1.7601   0.04768   0.04012  -0.1736   0.0095   0.5201
  11.500   1.7687   0.05241   0.04499  -0.1716   0.0087   0.5254
  11.750   1.7716   0.05498   0.04763  -0.1706   0.0083   0.5281
  12.000   1.7735   0.05771   0.05043  -0.1696   0.0079   0.5308
  12.250   1.7746   0.06058   0.05337  -0.1688   0.0075   0.5334
  12.500   1.7750   0.06357   0.05643  -0.1679   0.0071   0.5360
  12.750   1.7767   0.06641   0.05935  -0.1671   0.0069   0.5384
  13.000   1.7774   0.06937   0.06240  -0.1664   0.0067   0.5412
  13.250   1.7774   0.07245   0.06556  -0.1657   0.0065   0.5443
  13.500   1.7775   0.07554   0.06872  -0.1651   0.0063   0.5478
  13.750   1.7766   0.07879   0.07205  -0.1645   0.0061   0.5512
  14.000   1.7749   0.08215   0.07549  -0.1639   0.0059   0.5543
  14.250   1.7734   0.08548   0.07890  -0.1634   0.0057   0.5575
  14.500   1.7697   0.08915   0.08265  -0.1630   0.0055   0.5609
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