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Explore aerodynamics principles, airfoils, wings, and induced drag for optimizing aircraft performance in this comprehensive guide. Learn about different types of airfoils, geometry, lift, drag, and associated design factors.
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PRJ – 30Projeto e Construção de Aeromodelos Unit 3/8 Aerodynamics & Performance DEPARTAMENTO DE CIÊNCIA E TECNOLOGIA AEROESPACIAL INSTITUTO TECNOLÓGICO DE AERONÁUTICA DIVISÃO DE ENGENHARIA AERONÁUTICA DEPARTAMENTO DE PROJETOS DE AERONAVES Prof. Adson Agrico Prof. Vitor Kleine São José dos Campos, SP, Brazil – March, 2016
Schedule Aerodynamics Performance
Schedule Aerodynamics Performance
Aerodynamics Aerodynamic forces AED Geometry
Aerodynamic Design Airfoils Surfaces L/D ~ 50 L/D ~ 25 Aircraft L/D ~ 10 Bodies L/D ~ 3
Aerodynamic Design Airfoils Surfaces L/D ~ 50 L/D ~ 25 Aircraft L/D ~ 10 Bodies L/D ~ 3
Types of airfoils Symmetrical airfoils Cambered airfoils NACA 0012 RG 14 High-lift airfoils Reflex airfoils Selig 1223 Eppler 325 Want more?: UIUC Airfoil Data Site
Main curves MH32 airfoil Re 4.4e5 XFOIL Lift curve CL vs a
Main curves MH32 airfoil Re 4.4e5 XFOIL stall Raymer, 1992 Lift curve CL vs a
Main curves MH32 airfoil Re 4.4e5 XFOIL Drag polar CL vs CD
Main curves MH32 airfoil Re 4.4e5 XFOIL L/D curve CM vs a
Main curves MH32 airfoil Re 4.4e5 XFOIL Moment curve CM vs a
Main curves MH32 airfoil Re 4.4e5 XFOIL
Camber NACA 0012 Re 3e5 XFOIL NACA 2412 Re 3e5 XFOIL
Camber NACA 0012 Re 3e5 XFOIL NACA 2412 Re 3e5 XFOIL
Camber NACA 0012 Re 3e5 XFOIL NACA 2412 Re 3e5 XFOIL
Thickness NACA 0012 Re 3e5 XFOIL NACA 0015 Re 3e5 XFOIL
Thickness Zoom!!! NACA 0012 Re 3e5 XFOIL NACA 0015 Re 3e5 XFOIL
Thickness NACA 0012 Re 3e5 XFOIL NACA 0015 Re 3e5 XFOIL
High-lift airfoils Eppler 420 Xfoil Eppler 420 gf03 Fluent Selig 1223 Xfoil Re = 3e5
Reynolds number sd7062
Manufacturing Lift Moment Xfoil Tunnel Olafesky 02 lower clmax same clmax Selig 1223 Re=2·105
Aerodynamic Design Airfoils Surfaces L/D ~ 50 L/D ~ 25 Aircraft L/D ~ 10 Bodies L/D ~ 3
Wings Airfoil = Infinite wing Finite wing ... ... 2D aerodynamics 3D aerodynamics
Induced Drag LIFT LIFT More lift Greater vortices MORE DRAG
Induced Drag LIFT LIFT More lift Greater vortices MORE DRAG
Induced Drag en.wikipedia.org en.wikipedia.org
Induced Drag NACA 2412 airfoil Re 3e5 XFOIL NACA 2412 wing Re 3e5; AR=6 Non-linear LLT
Induced Drag NACA 2412 airfoil Re 3e5 XFOIL NACA 2412 wing Re 3e5; AR=6 Non-linear LLT
Induced Drag NACA 2412 airfoil Re 3e5 XFOIL NACA 2412 wing Re 3e5; AR=6 Non-linear LLT
Induced Drag parasite drag induced drag NACA 2412 airfoil Re 3e5 XFOIL NACA 2412 wing Re 3e5; AR=6 Non-linear LLT
Induced Drag parasite drag induced drag airfoil planform NACA 2412 airfoil Re 3e5 XFOIL NACA 2412 wing Re 3e5; AR=6 Non-linear LLT
Induced Drag Highly Cambered Airfoil
Aspect Ratio NACA 2412 wing Re 3e5; AR=6 Non-linear LLT NACA 2412 wing Re 3e5; AR=4 Non-linear LLT NACA 2412 wing Re 3e5; AR=8 Non-linear LLT
Aspect Ratio NACA 2412 wing Re 3e5; AR=6 Non-linear LLT NACA 2412 wing Re 3e5; AR=4 Non-linear LLT NACA 2412 wing Re 3e5; AR=8 Non-linear LLT
Aspect Ratio NACA 2412 wing Re 3e5; AR=6 Non-linear LLT NACA 2412 wing Re 3e5; AR=4 Non-linear LLT NACA 2412 wing Re 3e5; AR=8 Non-linear LLT
Taper ratio NACA 2412 wing Re 3e5; AR=6; l=1.0 Non-linear LLT NACA 2412 wing Re 3e5; AR=6; l=0.5 Non-linear LLT NACA 2412 wing Re 3e5; AR=6; l=0.1 Non-linear LLT
Taper ratio LIFT ~ NACA 2412 wing Re 3e5; AR=6; l=1.0 Non-linear LLT NACA 2412 wing Re 3e5; AR=6; l=0.5 Non-linear LLT NACA 2412 wing Re 3e5; AR=6; l=0.1 Non-linear LLT
Taper ratio More taper increases loading at the root better for structures LIFT ~ NACA 2412 wing Re 3e5; AR=6; l=1.0 Non-linear LLT NACA 2412 wing Re 3e5; AR=6; l=0.5 Non-linear LLT NACA 2412 wing Re 3e5; AR=6; l=0.1 Non-linear LLT
Taper ratio • Comparison with rectangular wing: • Induced drag reduced by 6%. • Manufacturing time doubles. 75 man-hours 150 man-hours
Sweep Raymer, 1992
Sweep M=0.3 Raymer, 1992
Sweep Raymer, 1992
Stall progression http://www.homebuiltairplanes.com/f
Wingtip devices Raymer, 1992