Missile Cl / Cd / Cm Study
Budget: $750 – $1,500 USD
I need a thorough aerodynamic analysis of my missile configuration, with the emphasis on extracting the key aerodynamic coefficients—lift (Cl), drag (Cd) and moment (Cm).
Scope
• Mid-course flight is the primary regime of interest, so the data set must capture typical cruise altitudes, Mach numbers and angles of attack found in that portion of the trajectory.
• In addition, I want the same three coefficients tabulated for the launch phase to complete my performance database.
Preferred approach
I am open to classical panel-code methods, Missile DATCOM, CFD in ANSYS Fluent / OpenFOAM, or a hybrid workflow—whichever you can justify for accuracy and turnaround. Just be clear about the mesh strategy, turbulence model (if any) and reference geometry you plan to use.
Deliverables
1. Coefficient tables and plots (Cl, Cd, Cm) versus angle of attack and Mach for both launch and mid-course phases.
2. Brief technical memo explaining assumptions, solver settings, grid independence checks and observed trends.
3. Native project files plus a concise summary spreadsheet—ready for import into my 6-DOF simulator.
Acceptance criteria
• Convergence residuals below 1 × 10⁻⁴ (for CFD routes) or equivalent validation evidence for semi-empirical codes.
• Coefficient curves smooth and physically consistent; no discontinuities across Mach bins.
• All data referenced to the specified missile datum and presented in non-dimensional form.
If you can meet these points and outline a clear timeline, I’m ready to move forward immediately.
Scope
• Mid-course flight is the primary regime of interest, so the data set must capture typical cruise altitudes, Mach numbers and angles of attack found in that portion of the trajectory.
• In addition, I want the same three coefficients tabulated for the launch phase to complete my performance database.
Preferred approach
I am open to classical panel-code methods, Missile DATCOM, CFD in ANSYS Fluent / OpenFOAM, or a hybrid workflow—whichever you can justify for accuracy and turnaround. Just be clear about the mesh strategy, turbulence model (if any) and reference geometry you plan to use.
Deliverables
1. Coefficient tables and plots (Cl, Cd, Cm) versus angle of attack and Mach for both launch and mid-course phases.
2. Brief technical memo explaining assumptions, solver settings, grid independence checks and observed trends.
3. Native project files plus a concise summary spreadsheet—ready for import into my 6-DOF simulator.
Acceptance criteria
• Convergence residuals below 1 × 10⁻⁴ (for CFD routes) or equivalent validation evidence for semi-empirical codes.
• Coefficient curves smooth and physically consistent; no discontinuities across Mach bins.
• All data referenced to the specified missile datum and presented in non-dimensional form.
If you can meet these points and outline a clear timeline, I’m ready to move forward immediately.