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OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: OAF102 AIRFOIL (oaf102-il)
Reynolds number: 200,000
Max Cl/Cd: 82.22 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf102-il-200000.txt
Download as CSV file: xf-oaf102-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF102 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5526   0.07181   0.06843  -0.0411   1.0000   0.0408
  -9.000  -0.5711   0.06190   0.05855  -0.0498   1.0000   0.0396
  -8.750  -0.5795   0.04031   0.03611  -0.0838   1.0000   0.0375
  -8.500  -0.5568   0.03333   0.02838  -0.0917   1.0000   0.0378
  -8.250  -0.5288   0.02923   0.02368  -0.0957   1.0000   0.0390
  -8.000  -0.4993   0.02732   0.02125  -0.0979   1.0000   0.0410
  -7.750  -0.4731   0.02405   0.01780  -0.0999   1.0000   0.0436
  -7.500  -0.4487   0.02268   0.01628  -0.1003   1.0000   0.0460
  -7.250  -0.4270   0.02149   0.01491  -0.1000   1.0000   0.0486
  -7.000  -0.4076   0.02057   0.01376  -0.0993   1.0000   0.0515
  -6.750  -0.3886   0.01936   0.01259  -0.0989   1.0000   0.0552
  -6.500  -0.3541   0.01842   0.01150  -0.1009   0.9975   0.0604
  -6.250  -0.3126   0.01717   0.01021  -0.1044   0.9945   0.0684
  -6.000  -0.2714   0.01611   0.00909  -0.1077   0.9904   0.0784
  -5.750  -0.2293   0.01525   0.00824  -0.1111   0.9867   0.0934
  -5.500  -0.1858   0.01443   0.00741  -0.1148   0.9840   0.1164
  -5.250  -0.1449   0.01376   0.00684  -0.1180   0.9789   0.1472
  -5.000  -0.1042   0.01339   0.00650  -0.1210   0.9736   0.1795
  -4.750  -0.0651   0.01311   0.00623  -0.1235   0.9678   0.2076
  -4.500  -0.0287   0.01294   0.00602  -0.1254   0.9598   0.2326
  -4.250   0.0047   0.01282   0.00592  -0.1266   0.9511   0.2540
  -4.000   0.0363   0.01279   0.00583  -0.1272   0.9424   0.2745
  -3.750   0.0646   0.01276   0.00580  -0.1272   0.9315   0.2926
  -3.500   0.0922   0.01275   0.00579  -0.1269   0.9217   0.3094
  -3.250   0.1190   0.01275   0.00577  -0.1264   0.9127   0.3256
  -3.000   0.1463   0.01274   0.00576  -0.1261   0.9025   0.3415
  -2.750   0.1730   0.01273   0.00573  -0.1256   0.8937   0.3572
  -2.500   0.2000   0.01271   0.00570  -0.1252   0.8844   0.3730
  -2.250   0.2277   0.01270   0.00569  -0.1249   0.8757   0.3889
  -2.000   0.2550   0.01269   0.00566  -0.1246   0.8679   0.4048
  -1.750   0.2833   0.01269   0.00567  -0.1245   0.8597   0.4210
  -1.500   0.3109   0.01268   0.00566  -0.1242   0.8525   0.4370
  -1.250   0.3395   0.01269   0.00569  -0.1243   0.8447   0.4533
  -1.000   0.3676   0.01268   0.00569  -0.1241   0.8379   0.4696
  -0.750   0.3962   0.01269   0.00573  -0.1242   0.8305   0.4858
  -0.500   0.4245   0.01268   0.00574  -0.1241   0.8234   0.5015
  -0.250   0.4531   0.01268   0.00578  -0.1241   0.8165   0.5169
   0.000   0.4818   0.01267   0.00581  -0.1242   0.8093   0.5327
   0.250   0.5102   0.01268   0.00585  -0.1241   0.8028   0.5499
   0.500   0.5389   0.01266   0.00592  -0.1242   0.7949   0.5680
   0.750   0.5668   0.01264   0.00597  -0.1240   0.7886   0.5870
   1.000   0.5957   0.01262   0.00607  -0.1242   0.7805   0.6088
   1.250   0.6235   0.01258   0.00613  -0.1239   0.7747   0.6346
   1.500   0.6522   0.01253   0.00630  -0.1241   0.7664   0.6704
   1.750   0.6785   0.01237   0.00638  -0.1234   0.7602   0.7284
   2.000   0.6943   0.01179   0.00627  -0.1201   0.7522   1.0000
   2.250   0.7242   0.01194   0.00635  -0.1204   0.7456   1.0000
   2.500   0.7540   0.01212   0.00654  -0.1208   0.7376   1.0000
   2.750   0.7831   0.01227   0.00666  -0.1209   0.7307   1.0000
   3.000   0.8123   0.01245   0.00689  -0.1212   0.7222   1.0000
   3.250   0.8402   0.01249   0.00690  -0.1207   0.7108   1.0000
   3.500   0.8668   0.01232   0.00668  -0.1198   0.6904   1.0000
   3.750   0.8931   0.01216   0.00641  -0.1187   0.6684   1.0000
   4.000   0.9206   0.01212   0.00640  -0.1182   0.6467   1.0000
   4.250   0.9482   0.01216   0.00644  -0.1179   0.6274   1.0000
   4.500   0.9756   0.01221   0.00650  -0.1174   0.6039   1.0000
   4.750   1.0027   0.01230   0.00657  -0.1170   0.5730   1.0000
   5.000   1.0286   0.01251   0.00666  -0.1163   0.5229   1.0000
   5.250   1.0495   0.01349   0.00697  -0.1151   0.3914   1.0000
   5.500   1.0562   0.01716   0.00886  -0.1133   0.1182   1.0000
   5.750   1.0761   0.01864   0.01010  -0.1123   0.0847   1.0000
   6.000   1.0974   0.01978   0.01120  -0.1114   0.0717   1.0000
   6.250   1.1175   0.02100   0.01243  -0.1103   0.0641   1.0000
   6.500   1.1376   0.02216   0.01356  -0.1091   0.0583   1.0000
   6.750   1.1564   0.02354   0.01498  -0.1077   0.0538   1.0000
   7.000   1.1774   0.02461   0.01610  -0.1066   0.0501   1.0000
   7.250   1.1972   0.02596   0.01741  -0.1054   0.0472   1.0000
   7.500   1.2174   0.02806   0.01951  -0.1041   0.0446   1.0000
   7.750   1.2402   0.02909   0.02068  -0.1032   0.0422   1.0000
   8.000   1.2631   0.03050   0.02220  -0.1023   0.0402   1.0000
   8.250   1.2860   0.03209   0.02387  -0.1015   0.0386   1.0000
   8.500   1.3094   0.03404   0.02586  -0.1009   0.0372   1.0000
   8.750   1.3335   0.03781   0.02979  -0.1005   0.0356   1.0000
   9.000   1.3517   0.03916   0.03147  -0.0989   0.0344   1.0000
   9.250   1.3700   0.04176   0.03442  -0.0974   0.0337   1.0000
   9.500   1.3853   0.04494   0.03798  -0.0956   0.0334   1.0000
   9.750   1.3965   0.04867   0.04210  -0.0934   0.0333   1.0000
  10.000   1.4024   0.05290   0.04674  -0.0908   0.0337   1.0000
  10.250   1.4032   0.05723   0.05145  -0.0880   0.0340   1.0000
  10.500   1.3992   0.06154   0.05611  -0.0849   0.0342   1.0000
  10.750   1.3904   0.06568   0.06057  -0.0815   0.0343   1.0000
  11.000   1.3765   0.06983   0.06499  -0.0780   0.0346   1.0000
  11.250   1.3584   0.07406   0.06942  -0.0744   0.0349   1.0000
  11.500   1.2536   0.07205   0.06754  -0.0588   0.0361   1.0000
  11.750   1.2294   0.07485   0.07057  -0.0557   0.0364   1.0000
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