S9027 (8%) (s9027-il)
S9027 (8%) - Selig S9027 (8%) symmetrical vertical stab airfoil used on the Opus R/C sailplane
| Details | Dat file | Parser | |
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(s9027-il) S9027 (8%) Selig S9027 (8%) symmetrical vertical stab airfoil used on the Opus R/C sailplane Max thickness 8% at 22.9% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S9027 (8%)
1.00000 0.00000
0.99917 0.00001
0.99672 0.00009
0.99267 0.00029
0.98710 0.00063
0.98007 0.00112
0.97164 0.00175
0.96187 0.00249
0.95079 0.00330
0.93841 0.00416
0.92475 0.00507
0.90984 0.00605
0.89375 0.00711
0.87651 0.00825
0.85819 0.00946
0.83886 0.01074
0.81856 0.01209
0.79738 0.01351
0.77538 0.01498
0.75262 0.01651
0.72919 0.01807
0.70515 0.01965
0.68058 0.02124
0.65552 0.02282
0.63007 0.02441
0.60430 0.02597
0.57828 0.02750
0.55208 0.02900
0.52579 0.03045
0.49947 0.03184
0.47320 0.03315
0.44705 0.03438
0.42110 0.03553
0.39542 0.03657
0.37008 0.03748
0.34514 0.03828
0.32067 0.03894
0.29676 0.03946
0.27345 0.03980
0.25079 0.03999
0.22885 0.04000
0.20769 0.03983
0.18737 0.03947
0.16790 0.03890
0.14937 0.03814
0.13182 0.03717
0.11527 0.03597
0.09973 0.03454
0.08525 0.03291
0.07188 0.03107
0.05962 0.02899
0.04846 0.02670
0.03843 0.02425
0.02959 0.02161
0.02192 0.01877
0.01534 0.01576
0.00990 0.01268
0.00569 0.00955
0.00267 0.00631
0.00071 0.00303
0.00000 0.00000
0.00071 -0.00303
0.00267 -0.00631
0.00569 -0.00955
0.00990 -0.01268
0.01534 -0.01576
0.02192 -0.01877
0.02959 -0.02161
0.03843 -0.02425
0.04846 -0.02670
0.05962 -0.02899
0.07188 -0.03107
0.08525 -0.03291
0.09973 -0.03454
0.11527 -0.03597
0.13182 -0.03717
0.14937 -0.03814
0.16790 -0.03890
0.18737 -0.03947
0.20769 -0.03983
0.22885 -0.04000
0.25079 -0.03999
0.27345 -0.03980
0.29676 -0.03946
0.32067 -0.03894
0.34514 -0.03828
0.37008 -0.03748
0.39542 -0.03657
0.42110 -0.03553
0.44705 -0.03438
0.47320 -0.03315
0.49947 -0.03184
0.52579 -0.03045
0.55208 -0.02900
0.57828 -0.02750
0.60430 -0.02597
0.63007 -0.02441
0.65552 -0.02282
0.68058 -0.02124
0.70515 -0.01965
0.72919 -0.01807
0.75262 -0.01651
0.77538 -0.01498
0.79738 -0.01351
0.81856 -0.01209
0.83886 -0.01074
0.85819 -0.00946
0.87651 -0.00825
0.89375 -0.00711
0.90984 -0.00605
0.92475 -0.00507
0.93841 -0.00416
0.95079 -0.00330
0.96187 -0.00249
0.97164 -0.00175
0.98007 -0.00112
0.98710 -0.00063
0.99267 -0.00029
0.99672 -0.00009
0.99917 -0.00001
1.00000 0.00000
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Polars for S9027 (8%) (s9027-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s9027-il | 50,000 | 9 | 22.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 50,000 | 5 | 23.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 100,000 | 9 | 30.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 100,000 | 5 | 32.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 200,000 | 9 | 40.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 200,000 | 5 | 43.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 500,000 | 9 | 57.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 500,000 | 5 | 59.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 1,000,000 | 9 | 71.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 1,000,000 | 5 | 73.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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