Introduction to Propulsion

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Presentation transcript:

Introduction to Propulsion Lecture #3 Ehsan Roohi Ferdowsi University of Mashhad Faculty of Engineering

Oblique Shock: who Knows me? (Chap. 4, Anderson, MCF)

Breaking the Sound Barrier with an Aircraft

Shock Relation

Shock Relation

q-b-M Relation

Aerodynamics, by: Anderson Example Pages 513-514 Aerodynamics, by: Anderson

Example P1 effects comes inside Cp

Shock Reflection

INTERSECTION OF SHOCKS OF OPPOSITE FAMILIES q3+f q2-f Therefore, the entropy in regions 4 and 4‘ is different. Consequently, the dividing streamline EF between these two regions is a line across which the entropy changes discontinuously. Such a line is defined as a slip line. temperature and density, as well as the entropy and velocity magnitude, are different in regions 4 and 4'.

INTERSECTION OF SHOCKS OF THE SAME FAMILY

DETACHED SHOCK WAVE IN FRONT OF A BLUNT BODY

PRANDTL-MEYER EXPANSION WAVES When a supersonic flow is turned away from itself Non overtaking Mach Waves: Expansion is Isentropic

Read book on how convert dV to dM

PRANDTL-MEYER EXPANSION WAVES

Example Read Ex. 4.16/ 4.17

Nozzle

Example: Constant Area Heating

Tables

Example L*1: Length required to chock. L*2: Length remaining to chocking length