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

NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NREL's S810 Airfoil (s810-nr)
Reynolds number: 50,000
Max Cl/Cd: 16.53 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s810-nr-50000-n5.txt
Download as CSV file: xf-s810-nr-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S810 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.4647   0.15924   0.15250  -0.0423   1.0000   0.1218
 -14.500  -0.4400   0.15465   0.14790  -0.0409   1.0000   0.1272
 -14.250  -0.4607   0.15217   0.14556  -0.0453   1.0000   0.1357
 -14.000  -0.4320   0.14790   0.14125  -0.0433   1.0000   0.1431
 -13.750  -0.4325   0.14451   0.13794  -0.0448   1.0000   0.1534
 -13.500  -0.4340   0.14135   0.13486  -0.0461   1.0000   0.1659
 -13.250  -0.4283   0.13829   0.13182  -0.0463   1.0000   0.1803
 -13.000  -0.4172   0.13566   0.12922  -0.0457   1.0000   0.1978
 -12.750  -0.4119   0.13347   0.12710  -0.0450   1.0000   0.2239
 -12.500  -0.3557   0.10690   0.10108  -0.0715   0.9777   0.0651
 -12.250  -0.3492   0.10217   0.09634  -0.0734   0.9729   0.0616
 -12.000  -0.3637   0.09602   0.09013  -0.0771   0.9693   0.0588
 -11.750  -0.4173   0.08927   0.08309  -0.0813   0.9643   0.0522
 -11.250  -0.5343   0.09020   0.08387  -0.0731   0.9823   0.0609
 -11.000  -0.5479   0.08545   0.07893  -0.0760   0.9722   0.0585
 -10.750  -0.5717   0.08142   0.07458  -0.0777   0.9612   0.0558
 -10.500  -0.5673   0.07756   0.07045  -0.0787   0.9539   0.0494
 -10.250  -0.5716   0.07416   0.06685  -0.0791   0.9458   0.0478
 -10.000  -0.5797   0.07112   0.06354  -0.0783   0.9377   0.0465
  -9.750  -0.5857   0.06853   0.06068  -0.0769   0.9305   0.0457
  -9.500  -0.5908   0.06623   0.05808  -0.0748   0.9238   0.0444
  -9.250  -0.5921   0.06392   0.05547  -0.0728   0.9181   0.0442
  -9.000  -0.5891   0.06159   0.05274  -0.0711   0.9136   0.0433
  -8.750  -0.5879   0.05969   0.05063  -0.0686   0.9079   0.0440
  -8.500  -0.5800   0.05750   0.04810  -0.0668   0.9036   0.0438
  -8.250  -0.5656   0.05524   0.04540  -0.0656   0.9004   0.0431
  -8.000  -0.5595   0.05378   0.04356  -0.0625   0.8957   0.0421
  -7.750  -0.5506   0.05300   0.04233  -0.0595   0.8917   0.0409
  -7.500  -0.5302   0.05162   0.04057  -0.0584   0.8891   0.0402
  -7.250  -0.4923   0.04860   0.03734  -0.0599   0.8880   0.0398
  -7.000  -0.2368   0.04353   0.03190  -0.0816   0.9015   0.0442
  -6.750  -0.1910   0.04372   0.03201  -0.0816   0.9004   0.0486
  -6.500  -0.1707   0.04364   0.03181  -0.0798   0.8973   0.0504
  -6.250  -0.1587   0.04334   0.03139  -0.0777   0.8939   0.0518
  -6.000  -0.1482   0.04282   0.03071  -0.0760   0.8906   0.0532
  -5.750  -0.1427   0.04187   0.02970  -0.0741   0.8874   0.0558
  -5.500  -0.1394   0.04121   0.02897  -0.0718   0.8839   0.0602
  -5.250  -0.1412   0.04085   0.02853  -0.0684   0.8796   0.0651
  -5.000  -0.1428   0.04027   0.02791  -0.0653   0.8763   0.0700
  -4.750  -0.1423   0.03964   0.02721  -0.0625   0.8735   0.0760
  -4.500  -0.1251   0.04084   0.03088  -0.0568   0.8720   0.4830
  -4.250  -0.1495   0.04079   0.03080  -0.0500   0.8668   0.5109
  -4.000  -0.1720   0.04059   0.03056  -0.0435   0.8623   0.5339
  -3.750  -0.1970   0.04006   0.02998  -0.0369   0.8588   0.5521
  -3.500  -0.0689   0.05031   0.03958  -0.0380   0.8610   0.7140
  -3.250  -0.0732   0.05009   0.03925  -0.0342   0.8582   0.7184
  -3.000  -0.0816   0.05018   0.03927  -0.0291   0.8544   0.7216
  -2.750  -0.0833   0.05025   0.03926  -0.0251   0.8511   0.7244
  -2.500  -0.0882   0.05018   0.03911  -0.0207   0.8478   0.7278
  -2.250  -0.1051   0.04990   0.03878  -0.0145   0.8444   0.7324
  -2.000  -0.1176   0.04981   0.03865  -0.0088   0.8409   0.7357
  -1.750  -0.1254   0.04975   0.03853  -0.0037   0.8370   0.7385
  -1.500  -0.1265   0.04948   0.03818  -0.0001   0.8337   0.7416
  -1.250  -0.1294   0.04902   0.03760   0.0036   0.8308   0.7455
  -1.000  -0.1353   0.04857   0.03709   0.0078   0.8274   0.7489
  -0.750  -0.1370   0.04842   0.03688   0.0117   0.8235   0.7512
  -0.500  -0.1295   0.04819   0.03658   0.0139   0.8202   0.7538
  -0.250  -0.1178   0.04789   0.03618   0.0153   0.8172   0.7567
   0.000  -0.1084   0.04748   0.03566   0.0169   0.8143   0.7596
   0.250  -0.1186   0.04706   0.03521   0.0216   0.8093   0.7629
   0.500  -0.1031   0.04700   0.03509   0.0226   0.8057   0.7649
   0.750  -0.0822   0.04693   0.03496   0.0227   0.8027   0.7670
   1.000  -0.0685   0.04681   0.03478   0.0237   0.7990   0.7694
   1.250  -0.0648   0.04659   0.03454   0.0261   0.7939   0.7722
   1.500  -0.0478   0.04641   0.03429   0.0264   0.7899   0.7750
   1.750  -0.0212   0.04646   0.03431   0.0254   0.7869   0.7771
   2.000  -0.0162   0.04650   0.03435   0.0279   0.7808   0.7793
   2.250   0.0037   0.04657   0.03443   0.0280   0.7764   0.7813
   2.500   0.0324   0.04669   0.03454   0.0268   0.7729   0.7832
   2.750   0.0388   0.04674   0.03460   0.0287   0.7662   0.7860
   3.000   0.0622   0.04683   0.03471   0.0279   0.7613   0.7887
   3.250   0.0857   0.04702   0.03493   0.0274   0.7566   0.7909
   3.500   0.0993   0.04723   0.03521   0.0285   0.7496   0.7929
   3.750   0.1291   0.04746   0.03550   0.0272   0.7452   0.7947
   4.000   0.1409   0.04771   0.03581   0.0283   0.7373   0.7971
   4.250   0.1687   0.04794   0.03612   0.0272   0.7320   0.7995
   4.500   0.1849   0.04822   0.03651   0.0275   0.7240   0.8023
   4.750   0.2128   0.04846   0.03685   0.0264   0.7180   0.8047
   5.000   0.2283   0.04880   0.03729   0.0272   0.7094   0.8068
   5.250   0.2579   0.04902   0.03765   0.0261   0.7033   0.8089
   5.500   0.2730   0.04937   0.03812   0.0268   0.6935   0.8113
   5.750   0.3079   0.04951   0.03846   0.0251   0.6879   0.8138
   6.000   0.3230   0.04985   0.03894   0.0255   0.6768   0.8167
   6.250   0.3424   0.05012   0.03937   0.0257   0.6666   0.8193
   6.500   0.3770   0.05002   0.03949   0.0246   0.6598   0.8217
   6.750   0.3936   0.05023   0.03988   0.0253   0.6476   0.8243
   7.000   0.4138   0.05033   0.04022   0.0255   0.6354   0.8271
   7.250   0.4365   0.05030   0.04040   0.0254   0.6227   0.8299
   7.500   0.4596   0.05012   0.04045   0.0256   0.6094   0.8328
   7.750   0.4818   0.04976   0.04035   0.0263   0.5952   0.8357
   8.000   0.5070   0.04912   0.04004   0.0268   0.5800   0.8390
   8.250   0.5305   0.04844   0.03963   0.0275   0.5621   0.8425
   8.500   0.5536   0.04768   0.03915   0.0282   0.5410   0.8460
   8.750   0.5775   0.04645   0.03823   0.0297   0.5182   0.8491
   9.000   0.6004   0.04513   0.03720   0.0313   0.4896   0.8527
   9.250   0.6280   0.04350   0.03587   0.0328   0.4500   0.8567
   9.500   0.6636   0.04119   0.03348   0.0347   0.3766   0.8608
   9.750   0.6789   0.04108   0.03279   0.0372   0.2888   0.8648
  10.000   0.6801   0.04272   0.03399   0.0390   0.2295   0.8692
  10.500   0.6847   0.04656   0.03729   0.0415   0.1560   0.8780
  10.750   0.6912   0.04836   0.03898   0.0423   0.1319   0.8828
  11.000   0.7022   0.05000   0.04055   0.0429   0.1163   0.8878
  11.250   0.7167   0.05129   0.04189   0.0438   0.1033   0.8932
  11.500   0.7324   0.05266   0.04339   0.0443   0.0905   0.8996
  11.750   0.7585   0.05363   0.04461   0.0449   0.0800   0.9063
  12.000   0.7817   0.05500   0.04622   0.0452   0.0694   0.9145
  12.250   0.8064   0.05669   0.04813   0.0453   0.0603   0.9233
  12.500   0.8206   0.05873   0.05028   0.0450   0.0531   0.9348
  12.750   0.8353   0.06163   0.05367   0.0447   0.0471   0.9498
  13.000   0.8393   0.06396   0.05619   0.0442   0.0431   1.0000
  13.250   0.8479   0.06744   0.05985   0.0435   0.0401   1.0000
  13.500   0.8469   0.07176   0.06462   0.0428   0.0387   1.0000
  13.750   0.8382   0.07653   0.06977   0.0419   0.0373   1.0000
  14.000   0.8279   0.08145   0.07501   0.0405   0.0368   1.0000
  14.250   0.8126   0.08687   0.08069   0.0386   0.0359   1.0000
  14.500   0.7952   0.09309   0.08716   0.0360   0.0363   1.0000
  14.750   0.7737   0.10030   0.09459   0.0323   0.0365   1.0000
  15.000   0.7511   0.10853   0.10299   0.0275   0.0372   1.0000
  15.250   0.7295   0.11764   0.11221   0.0218   0.0380   1.0000
<< Back to NREL's S810 Airfoil (s810-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S810 Airfoil (s810-nr)