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USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: USA 35 AIRFOIL (usa35-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.33 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa35-il-1000000.txt
Download as CSV file: xf-usa35-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 35 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.6713   0.03344   0.03017  -0.1371   0.9263   0.0312
 -13.500  -0.6815   0.03012   0.02660  -0.1387   0.9082   0.0313
 -13.250  -0.6793   0.02825   0.02454  -0.1381   0.8939   0.0314
 -13.000  -0.6687   0.02674   0.02283  -0.1377   0.8808   0.0315
 -12.750  -0.6541   0.02548   0.02141  -0.1373   0.8695   0.0316
 -12.250  -0.6175   0.02353   0.01915  -0.1365   0.8488   0.0319
 -12.000  -0.6056   0.02159   0.01698  -0.1358   0.8386   0.0322
 -11.750  -0.5856   0.02054   0.01583  -0.1353   0.8304   0.0324
 -11.500  -0.5631   0.01984   0.01504  -0.1349   0.8218   0.0327
 -11.250  -0.5393   0.01926   0.01439  -0.1346   0.8140   0.0329
 -11.000  -0.5146   0.01873   0.01380  -0.1343   0.8060   0.0331
 -10.750  -0.4900   0.01825   0.01323  -0.1340   0.7975   0.0334
 -10.500  -0.4645   0.01775   0.01267  -0.1337   0.7903   0.0336
 -10.250  -0.4390   0.01727   0.01210  -0.1335   0.7824   0.0339
 -10.000  -0.4135   0.01682   0.01155  -0.1332   0.7745   0.0342
  -9.750  -0.3873   0.01633   0.01100  -0.1330   0.7675   0.0345
  -9.500  -0.3611   0.01591   0.01048  -0.1327   0.7592   0.0348
  -9.250  -0.3344   0.01555   0.01003  -0.1325   0.7513   0.0352
  -9.000  -0.3071   0.01522   0.00963  -0.1324   0.7430   0.0355
  -8.750  -0.2801   0.01496   0.00926  -0.1321   0.7336   0.0357
  -8.500  -0.2551   0.01416   0.00839  -0.1318   0.7252   0.0362
  -8.250  -0.2285   0.01379   0.00796  -0.1316   0.7147   0.0366
  -8.000  -0.2010   0.01351   0.00764  -0.1314   0.7042   0.0370
  -7.500  -0.1460   0.01306   0.00705  -0.1310   0.6791   0.0379
  -7.250  -0.1186   0.01285   0.00676  -0.1308   0.6658   0.0384
  -7.000  -0.0914   0.01267   0.00647  -0.1306   0.6509   0.0390
  -6.750  -0.0636   0.01250   0.00621  -0.1304   0.6364   0.0394
  -6.500  -0.0361   0.01233   0.00594  -0.1302   0.6218   0.0398
  -6.250  -0.0097   0.01200   0.00554  -0.1299   0.6076   0.0406
  -6.000   0.0181   0.01186   0.00535  -0.1297   0.5948   0.0413
  -5.750   0.0460   0.01176   0.00519  -0.1296   0.5836   0.0420
  -5.500   0.0738   0.01167   0.00503  -0.1294   0.5731   0.0428
  -5.250   0.1021   0.01158   0.00487  -0.1293   0.5646   0.0436
  -5.000   0.1301   0.01143   0.00467  -0.1292   0.5568   0.0444
  -4.750   0.1576   0.01131   0.00450  -0.1291   0.5487   0.0455
  -4.500   0.1866   0.01120   0.00439  -0.1291   0.5438   0.0465
  -4.250   0.2152   0.01112   0.00427  -0.1291   0.5384   0.0476
  -4.000   0.2435   0.01109   0.00418  -0.1290   0.5328   0.0486
  -3.750   0.2713   0.01092   0.00400  -0.1289   0.5278   0.0500
  -3.500   0.3005   0.01082   0.00391  -0.1290   0.5252   0.0513
  -3.250   0.3296   0.01075   0.00383  -0.1290   0.5221   0.0528
  -3.000   0.3582   0.01065   0.00371  -0.1290   0.5186   0.0543
  -2.750   0.3867   0.01058   0.00364  -0.1290   0.5148   0.0560
  -2.500   0.4149   0.01059   0.00361  -0.1289   0.5106   0.0578
  -2.250   0.4434   0.01053   0.00354  -0.1289   0.5071   0.0597
  -2.000   0.4725   0.01044   0.00347  -0.1290   0.5051   0.0617
  -1.750   0.5017   0.01039   0.00343  -0.1291   0.5026   0.0637
  -1.500   0.5305   0.01031   0.00335  -0.1292   0.4997   0.0660
  -1.250   0.5591   0.01028   0.00333  -0.1292   0.4966   0.0685
  -1.000   0.5874   0.01029   0.00331  -0.1291   0.4931   0.0709
  -0.750   0.6151   0.01029   0.00330  -0.1290   0.4889   0.0741
  -0.500   0.6440   0.01027   0.00328  -0.1291   0.4864   0.0771
  -0.250   0.6730   0.01018   0.00324  -0.1292   0.4841   0.0815
   0.000   0.7019   0.01014   0.00322  -0.1293   0.4813   0.0862
   0.250   0.7304   0.01011   0.00321  -0.1294   0.4782   0.0924
   0.500   0.7585   0.01008   0.00320  -0.1293   0.4748   0.1035
   0.750   0.7859   0.01002   0.00323  -0.1293   0.4710   0.1359
   1.000   0.8136   0.00989   0.00331  -0.1293   0.4675   0.2050
   1.250   0.8423   0.00978   0.00334  -0.1295   0.4650   0.2523
   1.500   0.8706   0.00963   0.00339  -0.1296   0.4616   0.3218
   1.750   0.8982   0.00945   0.00347  -0.1297   0.4576   0.4269
   2.000   0.9250   0.00930   0.00358  -0.1296   0.4531   0.5417
   2.250   0.9505   0.00903   0.00374  -0.1293   0.4485   0.7100
   2.500   0.9707   0.00864   0.00388  -0.1274   0.4448   0.9001
   2.750   1.0055   0.00864   0.00393  -0.1286   0.4389   1.0000
   3.000   1.0313   0.00879   0.00401  -0.1282   0.4327   1.0000
   3.250   1.0584   0.00889   0.00408  -0.1280   0.4277   1.0000
   3.500   1.0854   0.00901   0.00416  -0.1279   0.4214   1.0000
   3.750   1.1104   0.00919   0.00427  -0.1274   0.4138   1.0000
   4.000   1.1370   0.00932   0.00436  -0.1271   0.4068   1.0000
   4.250   1.1616   0.00952   0.00449  -0.1266   0.3976   1.0000
   4.500   1.1866   0.00970   0.00463  -0.1261   0.3892   1.0000
   4.750   1.2099   0.00995   0.00480  -0.1253   0.3797   1.0000
   5.000   1.2340   0.01016   0.00497  -0.1247   0.3717   1.0000
   5.250   1.2557   0.01044   0.00518  -0.1237   0.3628   1.0000
   5.500   1.2776   0.01067   0.00537  -0.1226   0.3557   1.0000
   5.750   1.2982   0.01096   0.00561  -0.1214   0.3484   1.0000
   6.000   1.3191   0.01125   0.00586  -0.1202   0.3422   1.0000
   6.250   1.3414   0.01150   0.00609  -0.1193   0.3370   1.0000
   6.500   1.3619   0.01183   0.00638  -0.1182   0.3313   1.0000
   6.750   1.3824   0.01216   0.00668  -0.1171   0.3262   1.0000
   7.000   1.4051   0.01241   0.00693  -0.1164   0.3229   1.0000
   7.250   1.4265   0.01272   0.00723  -0.1155   0.3189   1.0000
   7.500   1.4464   0.01310   0.00758  -0.1144   0.3147   1.0000
   7.750   1.4653   0.01352   0.00798  -0.1131   0.3102   1.0000
   8.000   1.4881   0.01379   0.00826  -0.1125   0.3077   1.0000
   8.250   1.5093   0.01412   0.00860  -0.1117   0.3046   1.0000
   8.500   1.5292   0.01451   0.00900  -0.1108   0.3014   1.0000
   8.750   1.5479   0.01498   0.00945  -0.1096   0.2978   1.0000
   9.000   1.5648   0.01554   0.01000  -0.1083   0.2940   1.0000
   9.250   1.5868   0.01586   0.01035  -0.1077   0.2920   1.0000
   9.500   1.6074   0.01626   0.01076  -0.1070   0.2893   1.0000
   9.750   1.6262   0.01674   0.01126  -0.1060   0.2862   1.0000
  10.000   1.6436   0.01732   0.01183  -0.1050   0.2828   1.0000
  10.250   1.6582   0.01806   0.01256  -0.1036   0.2788   1.0000
  10.500   1.6779   0.01853   0.01307  -0.1028   0.2763   1.0000
  10.750   1.6970   0.01905   0.01361  -0.1021   0.2732   1.0000
  11.000   1.7136   0.01972   0.01429  -0.1011   0.2694   1.0000
  11.250   1.7277   0.02056   0.01513  -0.0999   0.2653   1.0000
  11.500   1.7423   0.02138   0.01597  -0.0987   0.2616   1.0000
  11.750   1.7601   0.02202   0.01663  -0.0980   0.2582   1.0000
  12.000   1.7742   0.02290   0.01754  -0.0969   0.2538   1.0000
  12.250   1.7840   0.02410   0.01872  -0.0955   0.2483   1.0000
  12.500   1.7987   0.02499   0.01964  -0.0946   0.2434   1.0000
  12.750   1.8083   0.02625   0.02089  -0.0933   0.2365   1.0000
  13.000   1.8170   0.02761   0.02224  -0.0920   0.2297   1.0000
  13.250   1.8226   0.02925   0.02387  -0.0906   0.2216   1.0000
  13.500   1.8284   0.03092   0.02554  -0.0892   0.2134   1.0000
  13.750   1.8286   0.03308   0.02767  -0.0876   0.2048   1.0000
  14.000   1.8301   0.03521   0.02980  -0.0862   0.1968   1.0000
  14.250   1.8286   0.03767   0.03226  -0.0847   0.1898   1.0000
  14.500   1.8276   0.04016   0.03476  -0.0834   0.1838   1.0000
  14.750   1.8252   0.04281   0.03742  -0.0822   0.1789   1.0000
  15.000   1.8267   0.04517   0.03982  -0.0813   0.1752   1.0000
  15.250   1.8240   0.04801   0.04269  -0.0803   0.1718   1.0000
  15.500   1.8183   0.05121   0.04592  -0.0793   0.1682   1.0000
  15.750   1.8208   0.05358   0.04835  -0.0787   0.1662   1.0000
  16.000   1.8221   0.05613   0.05095  -0.0781   0.1643   1.0000
  16.250   1.8204   0.05903   0.05390  -0.0775   0.1623   1.0000
  16.500   1.8166   0.06217   0.05709  -0.0769   0.1601   1.0000
  16.750   1.8111   0.06551   0.06047  -0.0764   0.1580   1.0000
  17.000   1.8037   0.06911   0.06412  -0.0759   0.1559   1.0000
  17.250   1.8079   0.07142   0.06650  -0.0757   0.1547   1.0000
  17.500   1.8085   0.07418   0.06933  -0.0755   0.1533   1.0000
  17.750   1.8093   0.07688   0.07208  -0.0753   0.1518   1.0000
  18.000   1.8056   0.08012   0.07538  -0.0751   0.1503   1.0000
  18.250   1.8031   0.08320   0.07851  -0.0749   0.1487   1.0000
  18.500   1.7951   0.08701   0.08236  -0.0749   0.1469   1.0000
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