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Analysis of Wing and Fin Aerodynamics for Rocket Design Using Newtonian Models

This document presents a comprehensive analysis of wing and fin aerodynamic characteristics for rocket design, focusing on pitching moments and shear coefficients under turbulent flow conditions. It investigates the lift and normal force coefficients for delta wing configurations, employing a Newtonian model framework. The study outlines assumptions related to static center of mass and unstable configurations, discusses methodology, and indicates future work to validate results. The research is part of AAE 450 Senior Design Class (Spring 2008) and references significant contributions in aerodynamics.

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Analysis of Wing and Fin Aerodynamics for Rocket Design Using Newtonian Models

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  1. Brian BudzinskiFebruary 21, 2008Aerothermal Group ContactLifting Bodies / Pitching Moment and ShearAssistance from: Alex Woods AAE 450 Spring 2008

  2. Wing Pitching Moment Coefficient • Assumptions: • Newtonian Model • Turbulent Flow • Unstable Configuration • Static Center of Mass • Moments about Center of Mass • Model: • Air launch • Initial Configuration: Horizontal (α=0°) • Final Configuration: Vertical (α=90°) Code: Brian Budzinski AAE 450 Spring 2008 Aerothermal

  3. Wing Shear Coefficient • Assumptions: • Newtonian Model • Turbulent Flow • Shear imparted on rocket from wing is equal to the normal force acting on the wing. • Future Work: • Double Check Validity of Results • Further Code Integration Code: Brian Budzinski Code: Brian Budzinski AAE 450 Spring 2008 Aerothermal

  4. Wing Normal Force Coefficient Normal force as a function of angle of attack for a delta wing configuration Code: Brian Budzinski AAE 450 Spring 2008

  5. Wing Axial Force Coefficient Axial force coefficient as a function of angle of attack for a delta wing configuration Code: Brian Budzinski AAE 450 Spring 2008

  6. Fin Pitching Moment Coefficient • Assumptions: • Newtonian Model • Turbulent Flow • Unstable Configuration • Static Center of Mass • Moments about Center of Mass NOTE: Unsure about the validity of the results Code: Brian Budzinski AAE 450 Spring 2008

  7. Fin Shear Coefficient • Assumptions: • Newtonian Model • Turbulent Flow • Shear imparted on rocket from fins is equal to the normal force acting on the fins. NOTE: Unsure about the validity of the results Code: Brian Budzinski AAE 450 Spring 2008

  8. References: • (1) Hankey, Wilbur L. “Re-Entry Aerodynamics” AIAA, Washington D.C., 1988, pp. 70-73. • (2) AAE 450 Senior Design Class: Spring 2007, "Project Aquarius" • (3) Rhode, M.N., Engelund, W.C., and Mendenhall, M.R. “Experimental Aerodynamic Characteristics of the Pegasus Air-Launched Booster and Comparisons with Predicted and Flight Results” AIAA 95-1830, June 1995 AAE 450 Spring 2008 Aerothermal

  9. Work Outline Aerothermal Group Contact • Interface between groups • Interface within group CFD • CATIA Model • Gambit Mesh • FLUENT Lifting Bodies • Wing -CD, CL, CM, Shear • Fins -CD, CL, CM, Shear AAE 450 Spring 2008

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