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ULTIMATE (ultimate-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: ULTIMATE (ultimate-il)
Reynolds number: 50,000
Max Cl/Cd: 28.36 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ultimate-il-50000.txt
Download as CSV file: xf-ultimate-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ULTIMATE                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6324   0.14259   0.13546   0.0225   1.0000   0.2869
 -11.500  -0.6215   0.13710   0.12996   0.0216   1.0000   0.2884
 -11.250  -0.7809   0.09491   0.08810  -0.0193   1.0000   0.1267
 -11.000  -0.7707   0.08994   0.08312  -0.0192   1.0000   0.1247
 -10.750  -0.7925   0.08296   0.07611  -0.0222   1.0000   0.1221
 -10.500  -0.8296   0.07636   0.06942  -0.0241   1.0000   0.1194
 -10.250  -0.8733   0.07124   0.06407  -0.0222   1.0000   0.1168
 -10.000  -0.9292   0.06686   0.05899  -0.0175   1.0000   0.1126
  -9.750  -0.9326   0.06249   0.05434  -0.0155   1.0000   0.1122
  -9.500  -0.9329   0.05829   0.04981  -0.0133   1.0000   0.1117
  -9.250  -0.9311   0.05433   0.04544  -0.0110   1.0000   0.1115
  -9.000  -0.9273   0.05070   0.04132  -0.0084   1.0000   0.1120
  -8.750  -0.9167   0.04715   0.03745  -0.0065   1.0000   0.1145
  -8.500  -0.8976   0.04434   0.03459  -0.0056   1.0000   0.1197
  -8.250  -0.8822   0.04145   0.03121  -0.0037   1.0000   0.1236
  -8.000  -0.8619   0.03851   0.02788  -0.0024   1.0000   0.1282
  -7.750  -0.8388   0.03625   0.02554  -0.0016   1.0000   0.1384
  -7.500  -0.8123   0.03385   0.02314  -0.0012   1.0000   0.1504
  -7.250  -0.7871   0.03167   0.02091  -0.0003   1.0000   0.1687
  -7.000  -0.7653   0.02946   0.01899   0.0009   1.0000   0.1994
  -6.750  -0.7548   0.02720   0.01740   0.0040   1.0000   0.2578
  -6.500  -0.7605   0.02559   0.01672   0.0105   1.0000   0.3602
  -6.250  -0.7602   0.02514   0.01667   0.0167   1.0000   0.4423
  -6.000  -0.7519   0.02507   0.01674   0.0216   1.0000   0.5002
  -5.750  -0.7360   0.02547   0.01732   0.0258   1.0000   0.5495
  -5.500  -0.7158   0.02648   0.01846   0.0303   1.0000   0.5984
  -5.250  -0.6954   0.02712   0.01908   0.0342   1.0000   0.6387
  -5.000  -0.6706   0.02739   0.01925   0.0368   1.0000   0.6695
  -4.750  -0.6449   0.02750   0.01923   0.0388   1.0000   0.6970
  -4.500  -0.6123   0.02775   0.01932   0.0399   1.0000   0.7224
  -4.250  -0.5872   0.02764   0.01907   0.0415   1.0000   0.7479
  -4.000  -0.5522   0.02780   0.01904   0.0416   1.0000   0.7727
  -3.750  -0.5097   0.02803   0.01906   0.0403   1.0000   0.7967
  -3.500  -0.4790   0.02788   0.01875   0.0403   1.0000   0.8224
  -3.250  -0.4059   0.02841   0.01897   0.0333   1.0000   0.8439
  -3.000  -0.3601   0.02824   0.01862   0.0300   1.0000   0.8686
  -2.750  -0.2834   0.02829   0.01840   0.0211   1.0000   0.8885
  -2.500  -0.2291   0.02794   0.01789   0.0155   1.0000   0.9113
  -2.250  -0.1667   0.02747   0.01727   0.0081   1.0000   0.9323
  -2.000  -0.1078   0.02692   0.01661   0.0009   1.0000   0.9542
  -1.750  -0.0446   0.02622   0.01583  -0.0075   1.0000   0.9747
  -1.500   0.0208   0.02535   0.01490  -0.0168   1.0000   0.9951
  -1.250   0.0434   0.02468   0.01423  -0.0186   1.0000   1.0000
  -1.000   0.0422   0.02436   0.01394  -0.0161   1.0000   1.0000
  -0.750   0.0361   0.02419   0.01379  -0.0126   1.0000   1.0000
  -0.500   0.0259   0.02413   0.01375  -0.0085   1.0000   1.0000
  -0.250   0.0119   0.02415   0.01377  -0.0039   1.0000   1.0000
   0.000  -0.0047   0.02423   0.01385   0.0011   1.0000   1.0000
   0.250  -0.0222   0.02433   0.01394   0.0062   1.0000   1.0000
   0.500  -0.0371   0.02449   0.01406   0.0110   1.0000   1.0000
   0.750  -0.0460   0.02476   0.01428   0.0148   1.0000   1.0000
   1.000  -0.0483   0.02516   0.01461   0.0177   1.0000   1.0000
   1.250   0.0051   0.02599   0.01547   0.0104   0.9858   1.0000
   1.500   0.0623   0.02678   0.01633   0.0028   0.9677   1.0000
   1.750   0.1166   0.02749   0.01714  -0.0040   0.9496   1.0000
   2.000   0.1720   0.02812   0.01789  -0.0107   0.9323   1.0000
   2.250   0.2198   0.02868   0.01856  -0.0157   0.9142   1.0000
   2.500   0.2641   0.02919   0.01923  -0.0198   0.8956   1.0000
   2.750   0.3146   0.02963   0.01985  -0.0248   0.8774   1.0000
   3.000   0.3677   0.02988   0.02034  -0.0296   0.8591   1.0000
   3.250   0.4111   0.03005   0.02072  -0.0323   0.8397   1.0000
   3.500   0.4388   0.03039   0.02120  -0.0322   0.8182   1.0000
   3.750   0.4784   0.03027   0.02132  -0.0331   0.7978   1.0000
   4.000   0.5057   0.03037   0.02160  -0.0322   0.7767   1.0000
   4.250   0.5320   0.03039   0.02181  -0.0308   0.7550   1.0000
   4.500   0.5659   0.02987   0.02152  -0.0295   0.7349   1.0000
   4.750   0.5839   0.03009   0.02192  -0.0268   0.7104   1.0000
   5.000   0.6101   0.02924   0.02125  -0.0233   0.6824   1.0000
   5.250   0.6336   0.02668   0.01867  -0.0159   0.6354   1.0000
   5.500   0.6510   0.02511   0.01704  -0.0097   0.5857   1.0000
   5.750   0.6670   0.02430   0.01618  -0.0048   0.5338   1.0000
   6.000   0.6746   0.02379   0.01545   0.0012   0.4372   1.0000
   6.250   0.6668   0.02610   0.01601   0.0080   0.2426   1.0000
   6.500   0.6790   0.02858   0.01780   0.0106   0.1867   1.0000
   6.750   0.6998   0.03051   0.01948   0.0122   0.1612   1.0000
   7.000   0.7250   0.03247   0.02128   0.0132   0.1452   1.0000
   7.250   0.7492   0.03433   0.02321   0.0143   0.1331   1.0000
   7.500   0.7748   0.03672   0.02586   0.0153   0.1270   1.0000
   7.750   0.7974   0.03904   0.02836   0.0164   0.1209   1.0000
   8.000   0.8174   0.04184   0.03133   0.0175   0.1160   1.0000
   8.250   0.8327   0.04480   0.03481   0.0193   0.1139   1.0000
   8.500   0.8452   0.04821   0.03868   0.0212   0.1134   1.0000
   8.750   0.8534   0.05187   0.04279   0.0232   0.1134   1.0000
   9.000   0.8569   0.05568   0.04700   0.0254   0.1134   1.0000
   9.250   0.8547   0.05969   0.05140   0.0276   0.1135   1.0000
   9.500   0.8481   0.06388   0.05591   0.0297   0.1141   1.0000
   9.750   0.8387   0.06825   0.06053   0.0315   0.1150   1.0000
  10.000   0.8296   0.07279   0.06522   0.0330   0.1161   1.0000
  10.250   0.8334   0.07777   0.07028   0.0336   0.1176   1.0000
  10.500   0.7254   0.08632   0.07910   0.0320   0.1281   1.0000
  10.750   0.7077   0.09360   0.08639   0.0288   0.1329   1.0000
  11.000   0.5076   0.10384   0.09677   0.0228   0.1551   1.0000
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