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PRJ – 30 Projeto e Construção de Aeromodelos

PRJ – 30 Projeto e Construção de Aeromodelos. U nit 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.

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PRJ – 30 Projeto e Construção de Aeromodelos

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  1. 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

  2. Schedule Aerodynamics Performance

  3. Schedule Aerodynamics Performance

  4. Aerodynamics Aerodynamic forces AED Geometry

  5. Aerodynamic Forces

  6. Aerodynamic Design Airfoils Surfaces L/D ~ 50 L/D ~ 25 Aircraft L/D ~ 10 Bodies L/D ~ 3

  7. Aerodynamic Design Airfoils Surfaces L/D ~ 50 L/D ~ 25 Aircraft L/D ~ 10 Bodies L/D ~ 3

  8. Airfoilgeometry

  9. 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

  10. Main curves MH32 airfoil Re 4.4e5 XFOIL Lift curve CL vs a

  11. Main curves MH32 airfoil Re 4.4e5 XFOIL stall Raymer, 1992 Lift curve CL vs a

  12. Main curves MH32 airfoil Re 4.4e5 XFOIL Drag polar CL vs CD

  13. Main curves MH32 airfoil Re 4.4e5 XFOIL L/D curve CM vs a

  14. Main curves MH32 airfoil Re 4.4e5 XFOIL Moment curve CM vs a

  15. Main curves MH32 airfoil Re 4.4e5 XFOIL

  16. Camber NACA 0012 Re 3e5 XFOIL NACA 2412 Re 3e5 XFOIL

  17. Camber NACA 0012 Re 3e5 XFOIL NACA 2412 Re 3e5 XFOIL

  18. Camber NACA 0012 Re 3e5 XFOIL NACA 2412 Re 3e5 XFOIL

  19. Thickness NACA 0012 Re 3e5 XFOIL NACA 0015 Re 3e5 XFOIL

  20. Thickness Zoom!!! NACA 0012 Re 3e5 XFOIL NACA 0015 Re 3e5 XFOIL

  21. Thickness NACA 0012 Re 3e5 XFOIL NACA 0015 Re 3e5 XFOIL

  22. High-lift airfoils Eppler 420 Xfoil Eppler 420 gf03 Fluent Selig 1223 Xfoil Re = 3e5

  23. Reynolds number sd7062

  24. Manufacturing Lift Moment Xfoil Tunnel Olafesky 02 lower clmax same clmax Selig 1223 Re=2·105

  25. Aerodynamic Design Airfoils Surfaces L/D ~ 50 L/D ~ 25 Aircraft L/D ~ 10 Bodies L/D ~ 3

  26. Wings Airfoil = Infinite wing Finite wing ... ... 2D aerodynamics 3D aerodynamics

  27. Induceddrag

  28. Induced Drag LIFT LIFT More lift  Greater vortices  MORE DRAG

  29. Induced Drag LIFT LIFT More lift  Greater vortices  MORE DRAG

  30. Induced Drag en.wikipedia.org en.wikipedia.org

  31. Induced Drag NACA 2412 airfoil Re 3e5 XFOIL NACA 2412 wing Re 3e5; AR=6 Non-linear LLT

  32. Induced Drag NACA 2412 airfoil Re 3e5 XFOIL NACA 2412 wing Re 3e5; AR=6 Non-linear LLT

  33. Induced Drag NACA 2412 airfoil Re 3e5 XFOIL NACA 2412 wing Re 3e5; AR=6 Non-linear LLT

  34. Induced Drag parasite drag induced drag NACA 2412 airfoil Re 3e5 XFOIL NACA 2412 wing Re 3e5; AR=6 Non-linear LLT

  35. Induced Drag parasite drag induced drag airfoil planform NACA 2412 airfoil Re 3e5 XFOIL NACA 2412 wing Re 3e5; AR=6 Non-linear LLT

  36. Induced Drag Highly Cambered Airfoil

  37. 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

  38. 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

  39. 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

  40. 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

  41. 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

  42. 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

  43. Taper ratio • Comparison with rectangular wing: • Induced drag reduced by 6%. • Manufacturing time doubles. 75 man-hours 150 man-hours

  44. Sweep Raymer, 1992

  45. Sweep M=0.3 Raymer, 1992

  46. Sweep Raymer, 1992

  47. Stall progression http://www.homebuiltairplanes.com/f

  48. Wingtip devices Raymer, 1992

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