3241 Lecture 14

# 3241 Lecture 14 - MAE 3241 AERODYNAMICS AND FLIGHT...

This preview shows pages 1–6. Sign up to view the full content.

MAE 3241: AERODYNAMICS AND FLIGHT MECHANICS Overview of Shock Waves and Shock Drag Mechanical and Aerospace Engineering Department Florida Institute of Technology D. R. Kirk

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
PERTINENT SECTIONS Chapter 7: Overview of Compressible Flow Physics Reads very well after Chapter 2 (§2.7: Energy Equation) §7.5, many aerospace engineering students don’t know this 100% Chapter 8: Normal Shock Waves §8.2: Control volume around a normal shock wave §8.3: Speed of sound Sound wave modeled as isentropic Definition of Mach number compares local velocity to local speed of sound, M=V/a Square of Mach number is proportional to ratio of kinetic energy to internal energy of a gas flow (measure of the directed motion of the gas compared with the random thermal motion of the molecules) §8.4: Energy equation §8.5: Discussion of when a flow may be considered incompressible §8.6: Flow relations across normal shock waves
PERTINENT SECTIONS Chapter 9: Oblique shock and expansion waves §9.2: Oblique shock relations Tangential component of flow velocity is constant across an oblique shock Changes across an oblique shock wave are governed only by the component of velocity normal to the shock wave (exactly the same equations for a normal shock wave) §9.3: Difference between supersonic flow over a wedge (2D, infinite) and a cone (3D, finite) §9.4: Shock interactions and reflections §9.5: Detached shock waves in front of blunt bodies §9.6: Prandtl-Meyer expansion waves Occur when supersonic flow is turned away from itself Expansion process is isentropic Prandtl-Meyer expansion function (Appendix C) §9.7: Application t supersonic airfoils

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
EXAMPLES OF SUPERSONIC WAVE DRAG F-104 Starfighter
DYNAMIC PRESSURE FOR COMPRESSIBLE FLOWS Dynamic pressure is defined as q = ½ ρ V 2 For high speed flows, where Mach number is used frequently, it is convenient to express q in terms of pressure p and Mach number, M, rather than ρ and V Derive an equation for q = q(p,M) 2 2 2 2 2 2 2 2 2 2 2 2 2 2 1 2 1 2 1 = = = = = = = = M p q pM a V p q p a V p p V p p V q V q γ γ γ ρ γ ρ γ ρ γ γ ρ ρ

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
This is the end of the preview. Sign up to access the rest of the document.

{[ snackBarMessage ]}

### What students are saying

• As a current student on this bumpy collegiate pathway, I stumbled upon Course Hero, where I can find study resources for nearly all my courses, get online help from tutors 24/7, and even share my old projects, papers, and lecture notes with other students.

Kiran Temple University Fox School of Business ‘17, Course Hero Intern

• I cannot even describe how much Course Hero helped me this summer. It’s truly become something I can always rely on and help me. In the end, I was not only able to survive summer classes, but I was able to thrive thanks to Course Hero.

Dana University of Pennsylvania ‘17, Course Hero Intern

• The ability to access any university’s resources through Course Hero proved invaluable in my case. I was behind on Tulane coursework and actually used UCLA’s materials to help me move forward and get everything together on time.

Jill Tulane University ‘16, Course Hero Intern