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USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 35 A AIRFOIL (usa35a-il)
Reynolds number: 500,000
Max Cl/Cd: 92.3 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa35a-il-500000-n5.txt
Download as CSV file: xf-usa35a-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 35 A AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6048   0.03428   0.02991  -0.1346   0.8594   0.0300
 -12.750  -0.6124   0.03118   0.02653  -0.1359   0.8454   0.0302
 -12.500  -0.6057   0.02916   0.02427  -0.1361   0.8348   0.0304
 -12.250  -0.5938   0.02754   0.02244  -0.1360   0.8249   0.0306
 -11.750  -0.5611   0.02502   0.01952  -0.1354   0.8077   0.0309
 -11.500  -0.5424   0.02397   0.01834  -0.1350   0.7988   0.0311
 -11.250  -0.5220   0.02310   0.01736  -0.1346   0.7908   0.0313
 -11.000  -0.5001   0.02232   0.01651  -0.1343   0.7820   0.0315
 -10.750  -0.4775   0.02165   0.01573  -0.1339   0.7734   0.0317
 -10.500  -0.4539   0.02101   0.01500  -0.1337   0.7658   0.0319
 -10.250  -0.4299   0.02041   0.01431  -0.1334   0.7573   0.0321
 -10.000  -0.4057   0.01985   0.01364  -0.1330   0.7493   0.0324
  -9.750  -0.3808   0.01929   0.01300  -0.1328   0.7409   0.0326
  -9.500  -0.3559   0.01877   0.01237  -0.1324   0.7317   0.0329
  -9.250  -0.3306   0.01826   0.01176  -0.1322   0.7231   0.0333
  -9.000  -0.3051   0.01778   0.01117  -0.1319   0.7131   0.0336
  -8.750  -0.2794   0.01733   0.01060  -0.1316   0.7036   0.0340
  -8.500  -0.2534   0.01690   0.01005  -0.1313   0.6923   0.0343
  -8.250  -0.2274   0.01651   0.00954  -0.1310   0.6809   0.0346
  -8.000  -0.2016   0.01612   0.00907  -0.1306   0.6679   0.0350
  -7.750  -0.1752   0.01580   0.00869  -0.1304   0.6555   0.0354
  -7.500  -0.1488   0.01554   0.00834  -0.1301   0.6433   0.0358
  -7.250  -0.1219   0.01528   0.00800  -0.1298   0.6306   0.0362
  -7.000  -0.0952   0.01505   0.00768  -0.1295   0.6191   0.0368
  -6.750  -0.0683   0.01483   0.00736  -0.1293   0.6073   0.0374
  -6.500  -0.0412   0.01461   0.00705  -0.1290   0.5973   0.0381
  -6.250  -0.0142   0.01440   0.00675  -0.1288   0.5875   0.0387
  -6.000   0.0130   0.01420   0.00651  -0.1286   0.5792   0.0394
  -5.750   0.0405   0.01404   0.00630  -0.1284   0.5708   0.0401
  -5.500   0.0676   0.01390   0.00609  -0.1281   0.5634   0.0409
  -5.250   0.0956   0.01372   0.00586  -0.1280   0.5578   0.0418
  -5.000   0.1235   0.01356   0.00564  -0.1279   0.5524   0.0427
  -4.750   0.1510   0.01341   0.00547  -0.1277   0.5468   0.0436
  -4.500   0.1786   0.01332   0.00533  -0.1276   0.5408   0.0446
  -4.250   0.2068   0.01319   0.00517  -0.1275   0.5351   0.0459
  -4.000   0.2346   0.01310   0.00502  -0.1273   0.5292   0.0472
  -3.750   0.2621   0.01302   0.00491  -0.1271   0.5236   0.0486
  -3.500   0.2901   0.01295   0.00482  -0.1270   0.5187   0.0502
  -3.250   0.3185   0.01286   0.00470  -0.1270   0.5144   0.0520
  -3.000   0.3466   0.01277   0.00461  -0.1269   0.5107   0.0536
  -2.750   0.3747   0.01271   0.00453  -0.1268   0.5074   0.0555
  -2.500   0.4027   0.01266   0.00445  -0.1267   0.5039   0.0573
  -2.250   0.4303   0.01263   0.00440  -0.1266   0.5002   0.0593
  -2.000   0.4589   0.01257   0.00434  -0.1266   0.4974   0.0617
  -1.750   0.4873   0.01250   0.00429  -0.1266   0.4943   0.0640
  -1.500   0.5156   0.01246   0.00426  -0.1265   0.4912   0.0666
  -1.250   0.5437   0.01243   0.00422  -0.1265   0.4880   0.0691
  -1.000   0.5716   0.01241   0.00420  -0.1264   0.4848   0.0722
  -0.750   0.5992   0.01242   0.00418  -0.1262   0.4815   0.0753
  -0.500   0.6269   0.01241   0.00418  -0.1261   0.4783   0.0790
  -0.250   0.6552   0.01237   0.00417  -0.1261   0.4752   0.0830
   0.000   0.6833   0.01235   0.00416  -0.1261   0.4717   0.0877
   0.250   0.7111   0.01233   0.00417  -0.1260   0.4681   0.0931
   0.500   0.7385   0.01234   0.00418  -0.1258   0.4645   0.1001
   0.750   0.7655   0.01235   0.00420  -0.1256   0.4609   0.1106
   1.000   0.7929   0.01231   0.00425  -0.1255   0.4577   0.1331
   1.250   0.8206   0.01221   0.00432  -0.1256   0.4543   0.1851
   1.500   0.8479   0.01219   0.00439  -0.1255   0.4502   0.2163
   1.750   0.8747   0.01219   0.00445  -0.1253   0.4456   0.2466
   2.000   0.9005   0.01218   0.00455  -0.1250   0.4409   0.2972
   2.250   0.9275   0.01201   0.00468  -0.1250   0.4365   0.4071
   2.500   0.9540   0.01191   0.00481  -0.1248   0.4314   0.4956
   2.750   0.9780   0.01157   0.00501  -0.1243   0.4261   0.6884
   3.000   0.9988   0.01140   0.00518  -0.1227   0.4212   0.8222
   3.250   1.0269   0.01129   0.00529  -0.1224   0.4147   1.0000
   3.500   1.0509   0.01148   0.00541  -0.1217   0.4070   1.0000
   3.750   1.0751   0.01167   0.00554  -0.1210   0.3993   1.0000
   4.000   1.0980   0.01190   0.00570  -0.1201   0.3903   1.0000
   4.250   1.1205   0.01214   0.00587  -0.1192   0.3819   1.0000
   4.500   1.1406   0.01241   0.00607  -0.1179   0.3729   1.0000
   4.750   1.1611   0.01268   0.00629  -0.1166   0.3653   1.0000
   5.000   1.1816   0.01298   0.00653  -0.1154   0.3578   1.0000
   5.250   1.2015   0.01332   0.00681  -0.1141   0.3518   1.0000
   5.500   1.2231   0.01361   0.00707  -0.1131   0.3457   1.0000
   5.750   1.2427   0.01399   0.00740  -0.1119   0.3394   1.0000
   6.000   1.2626   0.01436   0.00774  -0.1107   0.3342   1.0000
   6.250   1.2840   0.01469   0.00805  -0.1098   0.3296   1.0000
   6.500   1.3038   0.01509   0.00843  -0.1087   0.3246   1.0000
   6.750   1.3218   0.01558   0.00886  -0.1074   0.3194   1.0000
   7.000   1.3424   0.01596   0.00924  -0.1064   0.3152   1.0000
   7.250   1.3626   0.01636   0.00965  -0.1055   0.3114   1.0000
   7.500   1.3816   0.01683   0.01010  -0.1044   0.3075   1.0000
   7.750   1.3992   0.01738   0.01063  -0.1032   0.3037   1.0000
   8.000   1.4177   0.01789   0.01114  -0.1022   0.3006   1.0000
   8.250   1.4377   0.01835   0.01161  -0.1013   0.2976   1.0000
   8.500   1.4565   0.01887   0.01214  -0.1004   0.2941   1.0000
   8.750   1.4739   0.01947   0.01275  -0.0993   0.2905   1.0000
   9.000   1.4897   0.02018   0.01345  -0.0981   0.2870   1.0000
   9.250   1.5060   0.02087   0.01415  -0.0970   0.2841   1.0000
   9.500   1.5246   0.02145   0.01476  -0.0962   0.2814   1.0000
   9.750   1.5422   0.02210   0.01544  -0.0953   0.2782   1.0000
  10.000   1.5578   0.02288   0.01624  -0.0943   0.2748   1.0000
  10.250   1.5718   0.02377   0.01713  -0.0931   0.2713   1.0000
  10.500   1.5849   0.02475   0.01812  -0.0920   0.2680   1.0000
  10.750   1.6017   0.02550   0.01892  -0.0912   0.2650   1.0000
  11.000   1.6162   0.02643   0.01988  -0.0902   0.2612   1.0000
  11.250   1.6283   0.02753   0.02099  -0.0891   0.2569   1.0000
  11.500   1.6373   0.02888   0.02234  -0.0879   0.2529   1.0000
  11.750   1.6516   0.02986   0.02338  -0.0870   0.2487   1.0000
  12.000   1.6620   0.03118   0.02472  -0.0860   0.2436   1.0000
  12.250   1.6688   0.03281   0.02635  -0.0848   0.2387   1.0000
  12.500   1.6792   0.03417   0.02776  -0.0839   0.2340   1.0000
  12.750   1.6867   0.03582   0.02943  -0.0829   0.2283   1.0000
  13.000   1.6910   0.03779   0.03141  -0.0818   0.2229   1.0000
  13.250   1.6969   0.03967   0.03332  -0.0809   0.2167   1.0000
  13.500   1.6970   0.04212   0.03578  -0.0798   0.2105   1.0000
  13.750   1.7011   0.04424   0.03793  -0.0789   0.2043   1.0000
  14.000   1.6986   0.04707   0.04077  -0.0779   0.1979   1.0000
  14.250   1.6982   0.04975   0.04348  -0.0771   0.1921   1.0000
  14.500   1.6940   0.05286   0.04660  -0.0763   0.1865   1.0000
  14.750   1.6914   0.05585   0.04963  -0.0756   0.1819   1.0000
  15.000   1.6894   0.05882   0.05264  -0.0750   0.1775   1.0000
  15.250   1.6831   0.06233   0.05617  -0.0744   0.1735   1.0000
  15.500   1.6809   0.06539   0.05928  -0.0740   0.1704   1.0000
  15.750   1.6809   0.06821   0.06215  -0.0737   0.1674   1.0000
  16.000   1.6775   0.07147   0.06545  -0.0733   0.1646   1.0000
  16.250   1.6735   0.07481   0.06883  -0.0731   0.1621   1.0000
  16.500   1.6700   0.07810   0.07217  -0.0729   0.1599   1.0000
  16.750   1.6731   0.08062   0.07475  -0.0728   0.1582   1.0000
  17.000   1.6732   0.08352   0.07772  -0.0727   0.1564   1.0000
  17.250   1.6739   0.08634   0.08060  -0.0726   0.1546   1.0000
  17.500   1.6722   0.08950   0.08380  -0.0727   0.1527   1.0000
  17.750   1.6699   0.09272   0.08707  -0.0728   0.1509   1.0000
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