Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SM701 (sm701-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SM701 (sm701-il)
Reynolds number: 500,000
Max Cl/Cd: 95.88 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sm701-il-500000.txt
Download as CSV file: xf-sm701-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SM701                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3392   0.08208   0.07982  -0.0808   0.9865   0.0342
 -10.500  -0.3986   0.06092   0.05838  -0.1029   0.9817   0.0346
 -10.250  -0.4667   0.02478   0.02082  -0.1173   0.9584   0.0252
 -10.000  -0.5061   0.03415   0.02992  -0.1169   0.9580   0.0242
  -9.750  -0.5017   0.03093   0.02640  -0.1155   0.9485   0.0236
  -9.500  -0.4793   0.02742   0.02248  -0.1173   0.9459   0.0231
  -9.250  -0.4498   0.02501   0.01979  -0.1192   0.9443   0.0231
  -9.000  -0.4331   0.02356   0.01817  -0.1179   0.9364   0.0233
  -8.750  -0.4046   0.02229   0.01674  -0.1188   0.9328   0.0240
  -8.500  -0.3732   0.02097   0.01526  -0.1201   0.9303   0.0244
  -8.250  -0.3512   0.01992   0.01409  -0.1193   0.9231   0.0246
  -8.000  -0.3225   0.01889   0.01295  -0.1199   0.9180   0.0249
  -7.750  -0.2896   0.01799   0.01194  -0.1212   0.9147   0.0252
  -7.500  -0.2672   0.01709   0.01098  -0.1204   0.9058   0.0254
  -7.250  -0.2380   0.01589   0.00975  -0.1211   0.9008   0.0259
  -7.000  -0.2143   0.01513   0.00898  -0.1208   0.8926   0.0266
  -6.750  -0.1856   0.01450   0.00832  -0.1214   0.8862   0.0274
  -6.500  -0.1604   0.01402   0.00779  -0.1213   0.8781   0.0283
  -6.250  -0.1332   0.01353   0.00723  -0.1215   0.8710   0.0292
  -6.000  -0.1078   0.01310   0.00674  -0.1214   0.8637   0.0299
  -5.750  -0.0825   0.01266   0.00623  -0.1212   0.8567   0.0305
  -5.500  -0.0566   0.01212   0.00564  -0.1213   0.8507   0.0319
  -5.250  -0.0319   0.01180   0.00530  -0.1210   0.8438   0.0334
  -5.000  -0.0039   0.01152   0.00495  -0.1212   0.8383   0.0353
  -4.750   0.0226   0.01121   0.00462  -0.1213   0.8328   0.0388
  -4.500   0.0488   0.01091   0.00433  -0.1212   0.8270   0.0463
  -4.250   0.0753   0.01025   0.00394  -0.1216   0.8219   0.1064
  -4.000   0.1013   0.00960   0.00364  -0.1220   0.8167   0.1974
  -3.750   0.1268   0.00861   0.00323  -0.1227   0.8108   0.3563
  -3.500   0.1555   0.00809   0.00315  -0.1235   0.8056   0.5003
  -3.250   0.1842   0.00811   0.00319  -0.1236   0.8001   0.5372
  -3.000   0.2123   0.00814   0.00321  -0.1235   0.7938   0.5576
  -2.750   0.2421   0.00821   0.00319  -0.1238   0.7881   0.5716
  -2.500   0.2698   0.00826   0.00322  -0.1237   0.7818   0.5826
  -2.250   0.2979   0.00831   0.00325  -0.1236   0.7756   0.5937
  -2.000   0.3277   0.00845   0.00333  -0.1238   0.7705   0.6074
  -1.750   0.3550   0.00857   0.00344  -0.1236   0.7648   0.6197
  -1.500   0.3823   0.00868   0.00359  -0.1232   0.7592   0.6317
  -1.000   0.4391   0.00874   0.00358  -0.1233   0.7484   0.6417
  -0.750   0.4672   0.00874   0.00355  -0.1233   0.7425   0.6446
  -0.500   0.4968   0.00878   0.00352  -0.1236   0.7372   0.6478
  -0.250   0.5240   0.00877   0.00350  -0.1235   0.7309   0.6509
   0.000   0.5524   0.00878   0.00346  -0.1236   0.7246   0.6537
   0.250   0.5805   0.00878   0.00343  -0.1237   0.7184   0.6566
   0.500   0.6074   0.00876   0.00343  -0.1234   0.7112   0.6594
   0.750   0.6359   0.00880   0.00341  -0.1235   0.7045   0.6623
   1.000   0.6622   0.00879   0.00343  -0.1232   0.6964   0.6654
   1.250   0.6901   0.00884   0.00341  -0.1232   0.6888   0.6687
   1.500   0.7166   0.00885   0.00342  -0.1230   0.6798   0.6720
   1.750   0.7433   0.00887   0.00342  -0.1227   0.6711   0.6752
   2.000   0.7689   0.00888   0.00346  -0.1222   0.6601   0.6784
   2.250   0.7949   0.00892   0.00349  -0.1218   0.6491   0.6819
   2.500   0.8202   0.00898   0.00351  -0.1213   0.6362   0.6856
   2.750   0.8448   0.00906   0.00354  -0.1207   0.6201   0.6892
   3.000   0.8681   0.00913   0.00360  -0.1198   0.6008   0.6928
   3.250   0.8898   0.00928   0.00367  -0.1185   0.5770   0.6968
   3.500   0.9098   0.00951   0.00378  -0.1170   0.5476   0.7012
   3.750   0.9285   0.00984   0.00395  -0.1153   0.5168   0.7055
   4.000   0.9464   0.01015   0.00415  -0.1134   0.4885   0.7095
   4.250   0.9645   0.01050   0.00439  -0.1117   0.4628   0.7139
   4.500   0.9830   0.01083   0.00462  -0.1100   0.4387   0.7189
   4.750   1.0000   0.01117   0.00486  -0.1080   0.4162   0.7238
   5.000   1.0164   0.01149   0.00512  -0.1060   0.3967   0.7288
   5.250   1.0344   0.01183   0.00539  -0.1042   0.3791   0.7345
   5.500   1.0528   0.01218   0.00568  -0.1027   0.3624   0.7405
   5.750   1.0706   0.01253   0.00600  -0.1010   0.3467   0.7460
   6.000   1.0895   0.01288   0.00631  -0.0995   0.3322   0.7524
   6.250   1.1087   0.01321   0.00662  -0.0981   0.3193   0.7588
   6.500   1.1274   0.01355   0.00697  -0.0967   0.3075   0.7655
   7.000   1.1634   0.01431   0.00770  -0.0936   0.2848   0.7805
   7.250   1.1827   0.01468   0.00806  -0.0924   0.2751   0.7894
   7.500   1.1990   0.01511   0.00850  -0.0906   0.2657   0.7980
   7.750   1.2181   0.01546   0.00888  -0.0894   0.2568   0.8076
   8.000   1.2345   0.01591   0.00934  -0.0877   0.2484   0.8177
   8.250   1.2524   0.01630   0.00978  -0.0863   0.2406   0.8285
   8.500   1.2678   0.01680   0.01029  -0.0845   0.2335   0.8410
   8.750   1.2854   0.01718   0.01074  -0.0831   0.2266   0.8552
   9.000   1.2979   0.01773   0.01131  -0.0808   0.2198   0.8724
   9.250   1.3124   0.01806   0.01176  -0.0788   0.2142   0.8960
   9.500   1.3191   0.01832   0.01215  -0.0752   0.2090   1.0000
   9.750   1.3359   0.01902   0.01282  -0.0742   0.2031   1.0000
  10.000   1.3556   0.01954   0.01337  -0.0735   0.1974   1.0000
  10.250   1.3714   0.02027   0.01408  -0.0724   0.1918   1.0000
  10.500   1.3876   0.02098   0.01480  -0.0713   0.1869   1.0000
  10.750   1.4052   0.02161   0.01546  -0.0704   0.1818   1.0000
  11.000   1.4194   0.02244   0.01628  -0.0691   0.1768   1.0000
  11.250   1.4342   0.02327   0.01714  -0.0680   0.1723   1.0000
  11.500   1.4511   0.02397   0.01789  -0.0671   0.1677   1.0000
  11.750   1.4645   0.02489   0.01881  -0.0659   0.1630   1.0000
  12.000   1.4766   0.02592   0.01985  -0.0646   0.1585   1.0000
  12.250   1.4931   0.02667   0.02068  -0.0638   0.1545   1.0000
  12.500   1.5059   0.02769   0.02171  -0.0627   0.1494   1.0000
  12.750   1.5160   0.02892   0.02294  -0.0615   0.1447   1.0000
  13.000   1.5320   0.02975   0.02385  -0.0608   0.1404   1.0000
  13.250   1.5434   0.03093   0.02504  -0.0597   0.1353   1.0000
  13.500   1.5525   0.03232   0.02643  -0.0586   0.1310   1.0000
  13.750   1.5670   0.03331   0.02752  -0.0579   0.1268   1.0000
  14.000   1.5771   0.03467   0.02890  -0.0570   0.1223   1.0000
  14.250   1.5836   0.03636   0.03059  -0.0559   0.1181   1.0000
  14.500   1.5972   0.03750   0.03182  -0.0554   0.1143   1.0000
  14.750   1.6061   0.03905   0.03341  -0.0546   0.1100   1.0000
  15.000   1.6102   0.04108   0.03544  -0.0537   0.1058   1.0000
  15.250   1.6220   0.04244   0.03691  -0.0532   0.1022   1.0000
  15.500   1.6293   0.04426   0.03877  -0.0526   0.0981   1.0000
  15.750   1.6315   0.04663   0.04115  -0.0519   0.0940   1.0000
  16.000   1.6404   0.04838   0.04299  -0.0515   0.0907   1.0000
  16.250   1.6456   0.05054   0.04520  -0.0511   0.0864   1.0000
  16.500   1.6452   0.05337   0.04806  -0.0508   0.0824   1.0000
  16.750   1.6513   0.05555   0.05033  -0.0506   0.0790   1.0000
  17.000   1.6532   0.05827   0.05311  -0.0505   0.0752   1.0000
  17.250   1.6502   0.06166   0.05655  -0.0506   0.0718   1.0000
  17.500   1.6533   0.06439   0.05937  -0.0508   0.0685   1.0000
  17.750   1.6518   0.06776   0.06280  -0.0511   0.0651   1.0000
  18.000   1.6450   0.07194   0.06704  -0.0518   0.0619   1.0000
  18.250   1.6441   0.07544   0.07064  -0.0525   0.0589   1.0000
  18.500   1.6384   0.07970   0.07499  -0.0535   0.0557   1.0000
  18.750   1.6282   0.08472   0.08007  -0.0549   0.0529   1.0000
  19.000   1.6229   0.08913   0.08459  -0.0563   0.0502   1.0000
  19.250   1.6129   0.09437   0.08993  -0.0581   0.0475   1.0000
<< Back to SM701 (sm701-il)

Polar data table (+)

Polar graphs


<< Back to SM701 (sm701-il)