S8052 (11.88%) (s8052-il)
S8052 (11.88%) - Selig S8052 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(s8052-il) S8052 (11.88%) Selig S8052 low Reynolds number airfoil Max thickness 11.9% at 33.3% chord. Max camber 1.2% at 44.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S8052 (11.88%)
1.00000 0.00000
0.99803 0.00018
0.99231 0.00079
0.98301 0.00181
0.97022 0.00330
0.95412 0.00533
0.93491 0.00790
0.91280 0.01104
0.88804 0.01472
0.86087 0.01891
0.83155 0.02357
0.80036 0.02863
0.76759 0.03400
0.73351 0.03957
0.69841 0.04524
0.66259 0.05083
0.62635 0.05617
0.58984 0.06088
0.55299 0.06482
0.51588 0.06814
0.47873 0.07081
0.44169 0.07283
0.40501 0.07423
0.36887 0.07498
0.33344 0.07511
0.29896 0.07461
0.26560 0.07351
0.23357 0.07182
0.20304 0.06957
0.17422 0.06676
0.14727 0.06341
0.12234 0.05951
0.09956 0.05510
0.07907 0.05012
0.06085 0.04458
0.04493 0.03864
0.03140 0.03234
0.02025 0.02579
0.01165 0.01916
0.00552 0.01240
0.00163 0.00569
0.00001 -0.00037
0.00147 -0.00540
0.00651 -0.00985
0.01471 -0.01427
0.02583 -0.01860
0.03977 -0.02271
0.05642 -0.02654
0.07569 -0.03003
0.09749 -0.03316
0.12169 -0.03590
0.14818 -0.03824
0.17678 -0.04018
0.20735 -0.04171
0.23970 -0.04283
0.27364 -0.04354
0.30896 -0.04385
0.34545 -0.04377
0.38288 -0.04331
0.42100 -0.04248
0.45957 -0.04127
0.49834 -0.03967
0.53702 -0.03758
0.57556 -0.03494
0.61389 -0.03185
0.65181 -0.02843
0.68916 -0.02481
0.72568 -0.02116
0.76113 -0.01762
0.79518 -0.01433
0.82751 -0.01136
0.85782 -0.00876
0.88581 -0.00656
0.91121 -0.00475
0.93377 -0.00330
0.95325 -0.00218
0.96950 -0.00128
0.98246 -0.00056
0.99204 -0.00011
0.99798 0.00002
1.00000 0.00000
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Polars for S8052 (11.88%) (s8052-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8052-il | 50,000 | 9 | 31 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8052-il | 50,000 | 5 | 32.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8052-il | 100,000 | 9 | 48.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8052-il | 100,000 | 5 | 46.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8052-il | 200,000 | 9 | 66.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8052-il | 200,000 | 5 | 58.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8052-il | 500,000 | 9 | 81.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8052-il | 500,000 | 5 | 73.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8052-il | 1,000,000 | 9 | 92.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8052-il | 1,000,000 | 5 | 87.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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