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GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GM15 (smoothed) (gm15sm-il)
Reynolds number: 200,000
Max Cl/Cd: 86.92 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-gm15sm-il-200000-n5.txt
Download as CSV file: xf-gm15sm-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GM15 (smoothed)                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3414   0.10048   0.09696  -0.0295   1.0000   0.0245
  -8.000  -0.3429   0.09821   0.09475  -0.0293   1.0000   0.0247
  -7.500  -0.3535   0.09432   0.09098  -0.0265   1.0000   0.0248
  -6.500  -0.3243   0.08098   0.07775  -0.0362   0.9919   0.0251
  -6.250  -0.3037   0.07426   0.07105  -0.0441   0.9868   0.0256
  -6.000  -0.2900   0.07158   0.06834  -0.0432   0.9833   0.0227
  -5.500  -0.2199   0.05517   0.05178  -0.0678   0.9724   0.0161
  -5.250  -0.1803   0.04750   0.04400  -0.0800   0.9674   0.0157
  -5.000  -0.1110   0.03040   0.02617  -0.1050   0.9648   0.0149
  -4.750  -0.0635   0.02355   0.01836  -0.1139   0.9629   0.0149
  -4.500  -0.0258   0.02027   0.01439  -0.1172   0.9603   0.0154
  -4.250   0.0067   0.01832   0.01197  -0.1186   0.9561   0.0160
  -4.000   0.0414   0.01665   0.00991  -0.1203   0.9531   0.0169
  -3.750   0.0770   0.01556   0.00869  -0.1223   0.9506   0.0198
  -3.500   0.1144   0.01460   0.00755  -0.1243   0.9486   0.0222
  -3.250   0.1447   0.01380   0.00660  -0.1247   0.9431   0.0241
  -3.000   0.1795   0.01294   0.00561  -0.1261   0.9391   0.0278
  -2.750   0.2163   0.01246   0.00500  -0.1279   0.9359   0.0360
  -2.500   0.2468   0.01191   0.00442  -0.1283   0.9296   0.0505
  -2.250   0.2800   0.01132   0.00400  -0.1295   0.9241   0.0982
  -2.000   0.3121   0.01097   0.00379  -0.1303   0.9181   0.1569
  -1.750   0.3424   0.01078   0.00365  -0.1307   0.9104   0.1999
  -1.500   0.3721   0.01063   0.00356  -0.1309   0.9021   0.2350
  -1.250   0.4038   0.01049   0.00342  -0.1315   0.8942   0.2611
  -1.000   0.4314   0.01039   0.00332  -0.1312   0.8832   0.2811
  -0.750   0.4601   0.01028   0.00319  -0.1312   0.8720   0.2995
  -0.500   0.4891   0.01016   0.00308  -0.1311   0.8599   0.3177
  -0.250   0.5180   0.01005   0.00297  -0.1311   0.8465   0.3365
   0.000   0.5470   0.00995   0.00287  -0.1310   0.8315   0.3558
   0.250   0.5762   0.00985   0.00278  -0.1310   0.8146   0.3761
   0.500   0.6053   0.00978   0.00269  -0.1309   0.7956   0.3981
   0.750   0.6337   0.00973   0.00263  -0.1308   0.7742   0.4232
   1.000   0.6615   0.00971   0.00261  -0.1305   0.7522   0.4524
   1.250   0.6880   0.00970   0.00262  -0.1299   0.7298   0.4907
   1.500   0.7135   0.00964   0.00266  -0.1292   0.7079   0.5548
   2.000   0.7713   0.00925   0.00276  -0.1292   0.6654   1.0000
   2.250   0.7968   0.00947   0.00286  -0.1285   0.6454   1.0000
   2.500   0.8220   0.00969   0.00298  -0.1278   0.6258   1.0000
   2.750   0.8472   0.00992   0.00313  -0.1270   0.6067   1.0000
   3.000   0.8721   0.01016   0.00330  -0.1263   0.5883   1.0000
   3.250   0.8971   0.01039   0.00352  -0.1256   0.5697   1.0000
   3.500   0.9218   0.01064   0.00372  -0.1248   0.5507   1.0000
   3.750   0.9464   0.01090   0.00395  -0.1240   0.5326   1.0000
   4.000   0.9709   0.01117   0.00419  -0.1233   0.5136   1.0000
   4.250   0.9952   0.01145   0.00445  -0.1224   0.4942   1.0000
   4.500   1.0192   0.01175   0.00478  -0.1216   0.4746   1.0000
   4.750   1.0427   0.01208   0.00509  -0.1206   0.4504   1.0000
   5.000   1.0628   0.01260   0.00541  -0.1191   0.4024   1.0000
   5.250   1.0802   0.01337   0.00580  -0.1172   0.3320   1.0000
   5.500   1.0988   0.01417   0.00629  -0.1157   0.2703   1.0000
   5.750   1.1168   0.01511   0.00692  -0.1142   0.2037   1.0000
   6.000   1.1316   0.01650   0.00778  -0.1123   0.1114   1.0000
   6.250   1.1452   0.01812   0.00891  -0.1103   0.0431   1.0000
   6.500   1.1644   0.01906   0.00983  -0.1088   0.0301   1.0000
   6.750   1.1844   0.01987   0.01076  -0.1074   0.0252   1.0000
   7.000   1.2009   0.02105   0.01206  -0.1054   0.0217   1.0000
   7.250   1.2191   0.02198   0.01313  -0.1038   0.0202   1.0000
   7.500   1.2371   0.02287   0.01419  -0.1021   0.0180   1.0000
   7.750   1.2537   0.02388   0.01530  -0.1004   0.0162   1.0000
   8.000   1.2675   0.02516   0.01667  -0.0982   0.0151   1.0000
   8.250   1.2770   0.02699   0.01860  -0.0955   0.0141   1.0000
   8.500   1.2888   0.02879   0.02052  -0.0931   0.0134   1.0000
   8.750   1.3045   0.02999   0.02188  -0.0912   0.0125   1.0000
   9.000   1.3194   0.03119   0.02322  -0.0894   0.0113   1.0000
   9.250   1.3321   0.03259   0.02476  -0.0872   0.0105   1.0000
   9.500   1.3436   0.03425   0.02661  -0.0850   0.0100   1.0000
   9.750   1.3540   0.03602   0.02852  -0.0828   0.0096   1.0000
  10.000   1.3627   0.03807   0.03072  -0.0804   0.0091   1.0000
  10.250   1.3701   0.04084   0.03370  -0.0782   0.0088   1.0000
  10.500   1.3738   0.04433   0.03749  -0.0756   0.0086   1.0000
  10.750   1.3749   0.04689   0.04035  -0.0728   0.0085   1.0000
  11.000   1.3723   0.04972   0.04349  -0.0699   0.0083   1.0000
  11.250   1.3665   0.05285   0.04692  -0.0672   0.0083   1.0000
  11.500   1.3576   0.05632   0.05069  -0.0648   0.0082   1.0000
  11.750   1.3465   0.06009   0.05474  -0.0630   0.0082   1.0000
  12.000   1.3334   0.06424   0.05917  -0.0618   0.0081   1.0000
  12.250   1.3187   0.06881   0.06400  -0.0615   0.0081   1.0000
  12.500   1.3027   0.07390   0.06934  -0.0621   0.0080   1.0000
  12.750   1.2859   0.07956   0.07522  -0.0636   0.0080   1.0000
  13.000   1.2682   0.08581   0.08170  -0.0660   0.0081   1.0000
  13.250   1.2500   0.09272   0.08881  -0.0694   0.0081   1.0000
  13.500   1.2314   0.10027   0.09654  -0.0736   0.0081   1.0000
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