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 S835 Airfoil (s835-nr) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NREL's S835 Airfoil (s835-nr)
Reynolds number: 50,000
Max Cl/Cd: 19.2 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s835-nr-50000-n5.txt
Download as CSV file: xf-s835-nr-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S835 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4668   0.12756   0.11741  -0.0405   1.0000   0.2285
 -11.750  -0.4806   0.12350   0.11334  -0.0408   1.0000   0.2335
 -11.500  -0.4893   0.12014   0.10997  -0.0406   1.0000   0.2378
 -11.250  -0.4780   0.11941   0.10925  -0.0392   1.0000   0.2403
 -11.000  -0.4746   0.11773   0.10757  -0.0382   1.0000   0.2439
 -10.750  -0.4885   0.11394   0.10378  -0.0380   1.0000   0.2491
 -10.500  -0.5031   0.11012   0.09996  -0.0377   1.0000   0.2541
 -10.250  -0.4915   0.10965   0.09948  -0.0360   1.0000   0.2567
 -10.000  -0.4889   0.10809   0.09793  -0.0348   1.0000   0.2602
  -9.500  -0.5226   0.10055   0.09040  -0.0335   1.0000   0.2712
  -9.250  -0.5128   0.10010   0.08997  -0.0317   1.0000   0.2739
  -8.750  -0.5667   0.09083   0.08070  -0.0302   1.0000   0.2871
  -8.500  -0.5508   0.09122   0.08112  -0.0280   1.0000   0.2891
  -8.250  -0.5428   0.09075   0.08066  -0.0261   1.0000   0.2920
  -7.750  -0.6049   0.08148   0.07140  -0.0234   1.0000   0.3059
  -7.500  -0.5775   0.08187   0.07178  -0.0233   0.9974   0.3084
  -7.250  -0.5552   0.08086   0.07073  -0.0249   0.9928   0.3127
  -6.500  -0.6504   0.06214   0.05177  -0.0298   0.9688   0.3424
  -6.250  -0.6035   0.06373   0.05336  -0.0309   0.9657   0.3446
  -6.000  -0.6914   0.05304   0.04238  -0.0315   0.9518   0.3601
  -5.750  -0.6572   0.05414   0.04353  -0.0310   0.9473   0.3624
  -5.500  -0.6292   0.05465   0.04406  -0.0305   0.9419   0.3655
  -5.250  -0.6139   0.05316   0.04250  -0.0317   0.9365   0.3722
  -5.000  -0.6280   0.04932   0.03847  -0.0314   0.9276   0.3811
  -4.750  -0.5964   0.04985   0.03904  -0.0316   0.9230   0.3846
  -4.500  -0.5769   0.04919   0.03833  -0.0317   0.9175   0.3902
  -4.250  -0.5746   0.04635   0.03528  -0.0325   0.9099   0.3997
  -4.000  -0.5417   0.04696   0.03595  -0.0328   0.9057   0.4033
  -3.750  -0.5238   0.04666   0.03565  -0.0320   0.8994   0.4083
  -3.500  -0.5105   0.04439   0.03314  -0.0338   0.8928   0.4185
  -3.250  -0.4776   0.04497   0.03381  -0.0341   0.8888   0.4222
  -3.000  -0.4607   0.04492   0.03380  -0.0328   0.8821   0.4270
  -2.750  -0.4405   0.04350   0.03219  -0.0344   0.8759   0.4368
  -2.500  -0.4091   0.04367   0.03241  -0.0351   0.8717   0.4415
  -2.250  -0.3920   0.04376   0.03256  -0.0336   0.8649   0.4463
  -2.000  -0.3693   0.04307   0.03177  -0.0345   0.8587   0.4548
  -1.750  -0.3384   0.04288   0.03159  -0.0358   0.8542   0.4615
  -1.500  -0.3196   0.04305   0.03182  -0.0345   0.8475   0.4664
  -1.250  -0.2972   0.04262   0.03133  -0.0350   0.8409   0.4747
  -1.000  -0.2662   0.04245   0.03117  -0.0362   0.8362   0.4819
  -0.750  -0.2450   0.04268   0.03146  -0.0353   0.8297   0.4873
  -0.500  -0.2238   0.04236   0.03110  -0.0356   0.8226   0.4959
  -0.250  -0.1932   0.04231   0.03108  -0.0365   0.8177   0.5028
   0.000  -0.1696   0.04254   0.03138  -0.0359   0.8116   0.5087
   0.250  -0.1494   0.04229   0.03109  -0.0361   0.8037   0.5183
   0.500  -0.1200   0.04242   0.03128  -0.0364   0.7986   0.5244
   0.750  -0.0942   0.04261   0.03154  -0.0362   0.7929   0.5309
   1.000  -0.0743   0.04240   0.03129  -0.0368   0.7843   0.5415
   1.250  -0.0467   0.04269   0.03170  -0.0362   0.7789   0.5465
   1.500  -0.0218   0.04286   0.03193  -0.0360   0.7726   0.5536
   1.750  -0.0012   0.04284   0.03189  -0.0363   0.7638   0.5635
   2.000   0.0275   0.04304   0.03222  -0.0359   0.7585   0.5692
   2.250   0.0474   0.04329   0.03253  -0.0352   0.7505   0.5767
   2.500   0.0720   0.04332   0.03259  -0.0358   0.7424   0.5860
   2.750   0.1035   0.04338   0.03277  -0.0356   0.7374   0.5923
   3.250   0.1471   0.04375   0.03325  -0.0352   0.7200   0.6089
   3.500   0.1822   0.04359   0.03321  -0.0354   0.7157   0.6161
   3.750   0.1908   0.04419   0.03386  -0.0339   0.7027   0.6248
   4.000   0.2256   0.04394   0.03371  -0.0345   0.6972   0.6325
   4.250   0.2357   0.04453   0.03441  -0.0324   0.6852   0.6392
   4.500   0.2729   0.04424   0.03416  -0.0341   0.6785   0.6504
   4.750   0.2872   0.04464   0.03470  -0.0320   0.6679   0.6561
   5.000   0.3141   0.04457   0.03474  -0.0316   0.6593   0.6643
   5.250   0.3576   0.04381   0.03407  -0.0332   0.6547   0.6745
   5.500   0.3617   0.04467   0.03505  -0.0304   0.6396   0.6808
   5.750   0.4049   0.04374   0.03423  -0.0316   0.6347   0.6911
   6.000   0.4129   0.04452   0.03511  -0.0296   0.6192   0.6982
   6.250   0.4530   0.04340   0.03412  -0.0295   0.6143   0.7074
   6.500   0.4657   0.04411   0.03492  -0.0285   0.5983   0.7167
   7.000   0.5171   0.04336   0.03442  -0.0264   0.5767   0.7341
   7.250   0.5321   0.04361   0.03481  -0.0246   0.5622   0.7422
   7.500   0.5735   0.04212   0.03344  -0.0245   0.5543   0.7523
   7.750   0.5877   0.04247   0.03390  -0.0229   0.5377   0.7612
   8.000   0.6063   0.04237   0.03393  -0.0211   0.5227   0.7705
   8.250   0.6450   0.04100   0.03265  -0.0208   0.5109   0.7811
   8.500   0.6657   0.04068   0.03244  -0.0191   0.4942   0.7908
   8.750   0.6855   0.04059   0.03244  -0.0176   0.4756   0.8011
   9.000   0.7049   0.04041   0.03232  -0.0159   0.4566   0.8117
   9.250   0.7260   0.04016   0.03211  -0.0143   0.4362   0.8222
   9.500   0.7475   0.03999   0.03193  -0.0129   0.4146   0.8340
   9.750   0.7646   0.03991   0.03182  -0.0109   0.3926   0.8455
  10.000   0.7762   0.04043   0.03232  -0.0089   0.3697   0.8577
  10.250   0.7873   0.04107   0.03294  -0.0071   0.3469   0.8709
  10.500   0.7958   0.04172   0.03356  -0.0050   0.3252   0.8852
  10.750   0.8037   0.04249   0.03431  -0.0029   0.3043   0.9014
  11.000   0.8114   0.04342   0.03521  -0.0013   0.2842   0.9202
  11.250   0.8218   0.04451   0.03630  -0.0006   0.2640   0.9470
  11.500   0.8310   0.04573   0.03747  -0.0004   0.2450   1.0000
  11.750   0.8435   0.04754   0.03920  -0.0009   0.2264   1.0000
  12.000   0.8550   0.04948   0.04106  -0.0014   0.2094   1.0000
  12.250   0.8655   0.05154   0.04305  -0.0018   0.1937   1.0000
  12.500   0.8755   0.05367   0.04513  -0.0022   0.1794   1.0000
  12.750   0.8852   0.05586   0.04728  -0.0026   0.1665   1.0000
  13.000   0.8945   0.05810   0.04945  -0.0030   0.1550   1.0000
  13.250   0.9036   0.06033   0.05157  -0.0034   0.1447   1.0000
  13.500   0.9112   0.06286   0.05418  -0.0038   0.1347   1.0000
  13.750   0.9190   0.06541   0.05676  -0.0043   0.1260   1.0000
  14.000   0.9273   0.06786   0.05917  -0.0047   0.1185   1.0000
  14.250   0.9343   0.07049   0.06183  -0.0052   0.1115   1.0000
  14.500   0.9401   0.07338   0.06482  -0.0058   0.1051   1.0000
  14.750   0.9500   0.07566   0.06698  -0.0062   0.0999   1.0000
  15.000   0.9516   0.07922   0.07078  -0.0071   0.0947   1.0000
  15.250   0.9602   0.08170   0.07320  -0.0077   0.0904   1.0000
  15.500   0.9587   0.08577   0.07753  -0.0088   0.0864   1.0000
  15.750   0.9672   0.08828   0.07997  -0.0095   0.0829   1.0000
  16.000   0.9600   0.09326   0.08524  -0.0113   0.0800   1.0000
  16.250   0.9571   0.09762   0.08974  -0.0130   0.0772   1.0000
  16.500   0.9647   0.10036   0.09243  -0.0140   0.0747   1.0000
  16.750   0.9432   0.10795   0.10040  -0.0177   0.0730   1.0000
  17.000   0.9197   0.11631   0.10906  -0.0223   0.0716   1.0000
  17.250   0.8853   0.12741   0.12047  -0.0289   0.0707   1.0000
<< Back to NREL's S835 Airfoil (s835-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S835 Airfoil (s835-nr)