User’s Guide for wing_fin.m Written by Budzinski Revision 2.0 3/29/08 – Description: The purpose of the code is to output all aerodynamic coefficients and loads needed ‘wing_fin.m’ for the addition of a wing and/or fins for an aircraft launch. These outputs include lift coefficient, drag coefficient, normal coefficient, axial coefficient, pitching moment coefficient, and shear coefficient. All of these aerodynamic coefficients and loads are output with respect to Mach number, and angle of attack. Assumptions: Several assumptions are made within the function. The assumptions can be further ‘wing_fin.m’ explained as follows: The Mach number is assumed to from Mach 1.0 to Mach 15.0. This Mach number – is assumed because for an aircraft launch the initial Mach would be near 1.0 and the wing would remain attached up until near Mach 15.0. of Attack The angle of attack is assumed to range from an initial horizontal – configuration (AoA = 0°) to a final vertical configuration (AoA = 90°). The normal force was found assuming the Newtonian Method. Though the Newtonian – Method is geared towards hypersonic flow, the launch vehicle will quickly enter the hypersonic regime with an aircraft launch. Therefore, this remains a reasonable assumption. Similarly, the axial force was found assuming the Newtonian Method. – The shear force acting on the launch vehicle from the wing and/or fin is assumed – to be equivalent to the normal force acting on the wing and/or fin itself. Pitching Moment The pitching moment is found by calculating the normal and axial – forces and multiplying them by their corresponding distances from the center of mass. Input Section: All of the variables that are passed into the code are described Variable Name Description h Altitude measure of the height above ground level, and is initially – chosen to begin at 12,000 m for an aircraft launch. [m] rho Air Density an array initially chosen from an altitude of 12,000 m to – a final altitude of 205,000 m. [kg/m3] T Air Temperature an array initially chosen from an altitude of 12,000 – m to a final altitude of 205,000 m. [K] Variable Name Description
User’s Guide for wing_fin.m Written by Budzinski Revision 2.0 – 3/29/08 Description: The purpose of the code ‘wing_fin.m’ is to output all aerodynamic coefficients and loads needed for the addition of a wing and/or fins for an aircraft launch. These outputs include lift coefficient, drag coefficient, normal coefficient, axial coefficient, pitching moment coefficient, and shear coefficient. All of these aerodynamic coefficients and loads are output with respect to Mach number, and angle of attack. Assumptions: Several assumptions are made within the ‘wing_fin.m’ function. The assumptions can be further explained as follows: Mach number – The Mach number is assumed to from Mach 1.0 to Mach 15.0. This is assumed because for an aircraft launch the initial Mach would be near 1.0 and the wing would remain attached up until near Mach 15.0. of Attack – The angle of attack is assumed to range from an initial horizontal configuration (AoA = 0°) to a final vertical configuration (AoA = 90°). – The normal force was found assuming the Newtonian Method. Though the Newtonian Method is geared towards hypersonic flow, the launch vehicle will quickly enter the hypersonic regime with an aircraft launch. Therefore, this remains a reasonable assumption. – Similarly, the axial force was found assuming the Newtonian Method. – The shear force acting on the launch vehicle from the wing and/or fin is assumed to be equivalent to the normal force acting on the wing and/or fin itself. Pitching Moment – The pitching moment is found by calculating the normal and axial forces and multiplying them by their corresponding distances from the center of mass. Input Section: All of the variables that are passed into the code are described Variable Name Description h Altitude – measure of the height above ground level, and is initially chosen to begin at 12,000 m for an aircraft launch. [m] rho Air Density – an array initially chosen from an altitude of 12,000 m to a final altitude of 205,000 m. [kg/m3] T Variable Name Air Temperature – an array initially chosen from an altitude of 12,000 m to a final altitude of 205,000 m. [K] Description
Report_Section_3.docx