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

GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)
Reynolds number: 200,000
Max Cl/Cd: 81.23 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe301-il-200000.txt
Download as CSV file: xf-goe301-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 301 (FRIEDRICHSHAFEN G 13) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2503   0.11559   0.11211  -0.0330   1.0000   0.0357
  -9.250  -0.2617   0.11503   0.11163  -0.0328   1.0000   0.0359
  -9.000  -0.2765   0.11461   0.11129  -0.0317   1.0000   0.0360
  -8.500  -0.2653   0.10730   0.10405  -0.0274   1.0000   0.0367
  -8.250  -0.2689   0.10556   0.10237  -0.0250   1.0000   0.0371
  -8.000  -0.2757   0.10422   0.10111  -0.0227   0.9998   0.0376
  -7.750  -0.2533   0.10024   0.09711  -0.0281   0.9957   0.0389
  -7.500  -0.2318   0.09629   0.09316  -0.0341   0.9899   0.0404
  -7.250  -0.1965   0.09203   0.08887  -0.0542   0.9761   0.0421
  -7.000  -0.1698   0.08626   0.08308  -0.0591   0.9725   0.0426
  -6.750  -0.1501   0.08222   0.07905  -0.0583   0.9657   0.0433
  -6.500  -0.1184   0.07807   0.07487  -0.0639   0.9607   0.0451
  -6.250  -0.0875   0.07392   0.07069  -0.0714   0.9506   0.0474
  -6.000  -0.0280   0.06769   0.06424  -0.0942   0.9390   0.0498
  -5.750  -0.0075   0.06359   0.06018  -0.0935   0.9348   0.0506
  -5.500   0.0199   0.06019   0.05677  -0.0960   0.9281   0.0519
  -5.250   0.0544   0.05664   0.05315  -0.1016   0.9192   0.0548
  -5.000   0.1160   0.05139   0.04749  -0.1176   0.9069   0.0589
  -4.750   0.1392   0.04781   0.04395  -0.1185   0.8980   0.0599
  -4.500   0.1661   0.04511   0.04119  -0.1203   0.8858   0.0614
  -4.250   0.1956   0.04261   0.03857  -0.1228   0.8710   0.0645
  -4.000   0.2420   0.03917   0.03461  -0.1297   0.8562   0.0699
  -3.750   0.2635   0.03665   0.03210  -0.1300   0.8414   0.0711
  -3.500   0.2886   0.03471   0.03006  -0.1307   0.8270   0.0732
  -3.250   0.3323   0.03474   0.02934  -0.1335   0.8133   0.0812
  -3.000   0.3523   0.03048   0.02520  -0.1343   0.8012   0.0832
  -2.750   0.3772   0.02891   0.02355  -0.1346   0.7889   0.0863
  -2.500   0.4111   0.02780   0.02193  -0.1358   0.7762   0.0958
  -2.250   0.4350   0.02583   0.01997  -0.1360   0.7645   0.0984
  -2.000   0.4630   0.02483   0.01877  -0.1363   0.7540   0.1052
  -1.750   0.4911   0.02347   0.01718  -0.1367   0.7430   0.1142
  -1.500   0.5187   0.02261   0.01611  -0.1370   0.7320   0.1285
  -1.250   0.5457   0.02177   0.01512  -0.1371   0.7220   0.1451
  -1.000   0.5717   0.02092   0.01420  -0.1371   0.7112   0.1627
  -0.750   0.5983   0.02033   0.01350  -0.1371   0.7010   0.1856
  -0.500   0.6412   0.01768   0.00959  -0.1360   0.6927   0.0823
  -0.250   0.6683   0.01694   0.00871  -0.1356   0.6821   0.0830
   0.000   0.6965   0.01656   0.00811  -0.1352   0.6726   0.0820
   0.250   0.7232   0.01593   0.00741  -0.1348   0.6618   0.0825
   0.500   0.7499   0.01546   0.00689  -0.1344   0.6515   0.0847
   0.750   0.7770   0.01523   0.00659  -0.1340   0.6416   0.0900
   1.000   0.8031   0.01501   0.00634  -0.1334   0.6299   0.0937
   1.250   0.8292   0.01462   0.00596  -0.1330   0.6189   0.0988
   1.500   0.8559   0.01450   0.00578  -0.1325   0.6083   0.1082
   1.750   0.8815   0.01427   0.00562  -0.1320   0.5963   0.1190
   2.000   0.9080   0.01420   0.00555  -0.1316   0.5858   0.1380
   2.250   0.9314   0.01255   0.00562  -0.1307   0.5765   1.0000
   2.500   0.9575   0.01273   0.00561  -0.1301   0.5659   1.0000
   2.750   0.9839   0.01293   0.00565  -0.1297   0.5566   1.0000
   3.000   1.0097   0.01311   0.00574  -0.1292   0.5463   1.0000
   3.250   1.0356   0.01331   0.00587  -0.1288   0.5366   1.0000
   3.500   1.0617   0.01353   0.00595  -0.1284   0.5275   1.0000
   3.750   1.0868   0.01372   0.00614  -0.1278   0.5170   1.0000
   4.000   1.1124   0.01395   0.00628  -0.1273   0.5076   1.0000
   4.250   1.1375   0.01417   0.00643  -0.1268   0.4976   1.0000
   4.500   1.1625   0.01441   0.00666  -0.1262   0.4877   1.0000
   4.750   1.1879   0.01470   0.00682  -0.1257   0.4790   1.0000
   5.000   1.2122   0.01494   0.00709  -0.1251   0.4689   1.0000
   5.250   1.2371   0.01525   0.00735  -0.1246   0.4602   1.0000
   5.500   1.2615   0.01553   0.00762  -0.1240   0.4511   1.0000
   5.750   1.2860   0.01587   0.00794  -0.1234   0.4427   1.0000
   6.000   1.3101   0.01619   0.00822  -0.1228   0.4337   1.0000
   6.250   1.3335   0.01651   0.00859  -0.1221   0.4241   1.0000
   6.500   1.3577   0.01690   0.00889  -0.1215   0.4156   1.0000
   6.750   1.3799   0.01720   0.00928  -0.1206   0.4060   1.0000
   7.000   1.4035   0.01760   0.00965  -0.1199   0.3979   1.0000
   7.250   1.4254   0.01792   0.01006  -0.1189   0.3886   1.0000
   7.500   1.4480   0.01833   0.01046  -0.1181   0.3802   1.0000
   7.750   1.4694   0.01869   0.01086  -0.1171   0.3711   1.0000
   8.000   1.4906   0.01910   0.01133  -0.1160   0.3623   1.0000
   8.250   1.5114   0.01950   0.01174  -0.1149   0.3536   1.0000
   8.500   1.5312   0.01990   0.01224  -0.1137   0.3443   1.0000
   8.750   1.5512   0.02038   0.01268  -0.1125   0.3359   1.0000
   9.000   1.5690   0.02078   0.01322  -0.1109   0.3260   1.0000
   9.250   1.5868   0.02128   0.01375  -0.1093   0.3170   1.0000
   9.500   1.6031   0.02177   0.01427  -0.1075   0.3075   1.0000
   9.750   1.6181   0.02229   0.01490  -0.1055   0.2973   1.0000
  10.000   1.6305   0.02288   0.01548  -0.1031   0.2873   1.0000
  10.250   1.6396   0.02350   0.01611  -0.1002   0.2766   1.0000
  10.500   1.6481   0.02417   0.01687  -0.0973   0.2650   1.0000
  10.750   1.6560   0.02498   0.01771  -0.0945   0.2538   1.0000
  11.000   1.6627   0.02594   0.01866  -0.0917   0.2436   1.0000
  11.250   1.6694   0.02693   0.01970  -0.0890   0.2330   1.0000
  11.500   1.6759   0.02801   0.02086  -0.0866   0.2227   1.0000
  11.750   1.6802   0.02929   0.02215  -0.0840   0.2132   1.0000
  12.000   1.6852   0.03061   0.02353  -0.0817   0.2037   1.0000
  12.250   1.6910   0.03198   0.02501  -0.0797   0.1954   1.0000
  12.500   1.6940   0.03360   0.02666  -0.0777   0.1878   1.0000
  12.750   1.6993   0.03515   0.02835  -0.0760   0.1794   1.0000
  13.000   1.6999   0.03715   0.03037  -0.0743   0.1719   1.0000
  13.250   1.7031   0.03906   0.03241  -0.0729   0.1629   1.0000
  13.500   1.7032   0.04135   0.03478  -0.0716   0.1547   1.0000
  13.750   1.6994   0.04414   0.03762  -0.0705   0.1462   1.0000
  14.000   1.6962   0.04703   0.04059  -0.0696   0.1362   1.0000
  14.250   1.6887   0.05051   0.04414  -0.0689   0.1257   1.0000
  14.500   1.6771   0.05461   0.04828  -0.0684   0.1136   1.0000
  14.750   1.6612   0.05945   0.05314  -0.0682   0.0966   1.0000
  15.000   1.6393   0.06526   0.05884  -0.0684   0.0697   1.0000
  15.250   1.6149   0.07154   0.06504  -0.0688   0.0594   1.0000
  15.500   1.5909   0.07804   0.07155  -0.0696   0.0537   1.0000
  15.750   1.5713   0.08416   0.07777  -0.0705   0.0493   1.0000
  16.000   1.5509   0.09058   0.08427  -0.0718   0.0465   1.0000
<< Back to GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)

Polar data table (+)

Polar graphs


<< Back to GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)