RG 12A-1.8/9.0 AIRFOIL (rg12a189-il)
RG 12A-1.8/9.0 AIRFOIL - Rolf Girsberger RG 12A-1.8/9.0 airfoil
| Details | Dat file | Parser | |
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(rg12a189-il) RG 12A-1.8/9.0 AIRFOIL Rolf Girsberger RG 12A-1.8/9.0 airfoil Max thickness 9% at 34.4% chord. Max camber 1.8% at 34.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RG 12A-1.8/9.0 AIRFOIL
32. 32.
0.0000000 0.0000000
0.0010000 0.0053100
0.0073500 0.0122600
0.0181000 0.0194200
0.0333900 0.0267100
0.0530600 0.0337300
0.0770200 0.0403000
0.1050600 0.0462500
0.1369700 0.0514300
0.1724800 0.0557300
0.2113100 0.0590600
0.2531100 0.0613800
0.2975200 0.0626700
0.3441300 0.0629400
0.3925000 0.0622200
0.4421700 0.0605800
0.4926600 0.0580900
0.5434000 0.0548700
0.5939300 0.0510400
0.6436800 0.0467400
0.6921300 0.0421200
0.7387900 0.0373000
0.7830999 0.0323200
0.8245300 0.0273100
0.8625801 0.0223800
0.8967800 0.0176600
0.9266600 0.0132500
0.9517900 0.0092100
0.9719400 0.0055100
0.9870300 0.0024600
0.9966500 0.0005900
1.0000000 0.0000000
0.0000000 0.0000000
0.0035400 -.0038900
0.0095300 -.0070300
0.0220400 -.0113800
0.0376000 -.0148400
0.0575600 -.0179300
0.0814300 -.0205300
0.1091800 -.0226600
0.1405900 -.0243400
0.1754800 -.0256000
0.2135800 -.0264600
0.2546200 -.0269600
0.2982900 -.0271100
0.3442100 -.0269400
0.3919900 -.0264700
0.4411900 -.0256900
0.4913200 -.0246100
0.5419200 -.0231800
0.5924800 -.0213500
0.6426000 -.0189000
0.6914800 -.0155900
0.7381600 -.0118400
0.7823300 -.0082700
0.8236600 -.0051700
0.8616600 -.0026600
0.8958900 -.0008400
0.9258700 0.0003000
0.9511300 0.0008500
0.9714701 0.0009200
0.9868200 0.0006400
0.9966100 0.0002200
1.0000000 0.0000000
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Polars for RG 12A-1.8/9.0 AIRFOIL (rg12a189-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg12a189-il | 50,000 | 9 | 34 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a189-il | 50,000 | 5 | 35.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a189-il | 100,000 | 9 | 50.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a189-il | 100,000 | 5 | 49.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a189-il | 200,000 | 9 | 67.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a189-il | 200,000 | 5 | 62.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a189-il | 500,000 | 9 | 86.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a189-il | 500,000 | 5 | 74.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a189-il | 1,000,000 | 9 | 96.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a189-il | 1,000,000 | 5 | 83.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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