AAE 450 Spring Brian Budzinski February 21, 2008 Aerothermal Group Contact Lifting Bodies / Pitching Moment and Shear Assistance from: Alex Woods

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

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

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

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

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

AAE 450 Spring Code: Brian Budzinski 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 Fin Shear Coefficient

AAE 450 Spring References:  (1) Hankey, Wilbur L. “Re-Entry Aerodynamics” AIAA, Washington D.C., 1988, pp  (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 , June 1995 Aerothermal

AAE 450 Spring Work Outline Aerothermal Group Contact  Interface between groups  Interface within group CFD  CATIA Model  Gambit Mesh  FLUENT Lifting Bodies  Wing -C D, C L, C M, Shear  Fins -C D, C L, C M, Shear