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Understanding Aerothermodynamics: Coefficients of Pressure and Drag in Supersonic Flow

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palma
6 diapositives · 195 Views · Oct 13, 2014

This document discusses CP and CD models relevant to aerothermodynamics, focusing on the coefficient of pressure and drag coefficients as applied to linear supersonic theory. The developed code can scale with various geometries, aiding in the identification of critical parameters like the center of pressure and drag values. Insights into drag behaviors under small angles of attack (AOA) and future integrations with additional aerodynamic codes are highlighted. Key references in the field provide foundational support for the discussion. Contributions from team members and professors are acknowledged.

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  1. Alex Woods2/6/08Aerothermodynamics GroupCp and Cd Models

  2. Cp and Cd models • Coefficient of Pressure • Used linear supersonic theory • Code scales with any given approximate geometry • Useful for determining locations of Center of Pressure, Drag values, Moments Group Name (i.e.Trajectory Optimization)

  3. Drag Coefficients • Drag coefficient scales with starting axial force. • Drag increases approximately linearly for small aoa’s Future Work • Integrate further aero codes into Master • Take part in MAT duties Chart by Alex Woods and Jayme Zott Group Name (i.e.Trajectory Optimization)

  4. References • Ashley, Holt, Engineering Analysis of Flight Vehicles, Dover Publications Inc., New York, 1974, pp. 303-312 • Anderson, John D., Fundamentals of Aerodynamics, Mcgraw-Hill Higher Education, 2001 • Jayme Zott, for working with me, as well as her previous work with drag coefficients • Professor Colicott, in reference to linearized theory applications Group Name (i.e.Trajectory Optimization)

  5. Backup Slides • Assumptions • Nose Cone may be modeled in two dimensions as a wedge • Adjacent stream lines vary with the cosine of the cylindrical angle from the windward radian • Drag coefficient scales upwards from Cd = .15 • Rocket diameter small enough to be considered within Linear Supersonic Theory

  6. Drag Scaling with Angle of Attack • Drag should scale with aoa according to the equation: Cn is output from Cp code, while Ca is output by Jayme’s cd_m code.