RG 15A-1.8/11.0 AIRFOIL (rg15a111-il)
RG 15A-1.8/11.0 AIRFOIL - Rolf Girsberger RG 15A-1.8/11.0 airfoil
| Details | Dat file | Parser | |
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(rg15a111-il) RG 15A-1.8/11.0 AIRFOIL Rolf Girsberger RG 15A-1.8/11.0 airfoil Max thickness 11% at 30.2% chord. Max camber 1.8% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RG 15A-1.8/11.0 AIRFOIL
32. 32.
0.0000000 0.0000000
0.0021400 0.0071400
0.0088800 0.0153300
0.0202800 0.0237900
0.0360400 0.0322200
0.0561900 0.0402300
0.0805500 0.0476700
0.1089500 0.0543500
0.1411700 0.0601200
0.1769400 0.0648800
0.2159500 0.0685400
0.2578900 0.0710500
0.3023600 0.0724100
0.3489700 0.0726200
0.3972800 0.0717300
0.4468300 0.0697900
0.4971200 0.0669000
0.5476300 0.0631300
0.5978700 0.0585800
0.6473300 0.0534100
0.6954800 0.0477900
0.7417800 0.0418900
0.7857000 0.0359000
0.8267400 0.0299600
0.8644000 0.0242400
0.8982100 0.0188600
0.9277400 0.0139500
0.9525500 0.0095600
0.9724200 0.0056500
0.9872800 0.0024900
0.9967200 0.0005900
1.0000000 0.0000000
0.0000000 0.0000000
0.0039600 -.0063900
0.0132000 -.0121800
0.0250100 -.0170900
0.0415600 -.0218300
0.0617900 -.0258900
0.0860800 -.0294000
0.1141100 -.0322700
0.1457700 -.0345200
0.1808100 -.0361500
0.2190200 -.0371800
0.2601000 -.0376300
0.3037500 -.0375400
0.3495900 -.0369200
0.3972400 -.0358000
0.4462600 -.0341700
0.4961900 -.0320500
0.5466600 -.0293200
0.5970500 -.0257800
0.6464601 -.0216300
0.6944200 -.0173500
0.7405500 -.0132500
0.7843699 -.0095400
0.8253900 -.0063500
0.8631000 -.0037800
0.8970600 -.0018500
0.9267800 -.0005600
0.9517900 0.0001800
0.9719100 0.0004800
0.9870500 0.0004400
0.9966700 0.0001700
1.0000000 0.0000000
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Polars for RG 15A-1.8/11.0 AIRFOIL (rg15a111-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg15a111-il | 50,000 | 9 | 32.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 50,000 | 5 | 35.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 100,000 | 9 | 50 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 100,000 | 5 | 49.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 200,000 | 9 | 66.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 200,000 | 5 | 62.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 500,000 | 9 | 87.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 500,000 | 5 | 79.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 1,000,000 | 9 | 101.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 1,000,000 | 5 | 90 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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