The Component Analysis tool lets you examine how individual parts of your rocket contribute to stability, drag, and roll — at any combination of Mach number and angle of attack. This is useful for diagnosing stability problems, understanding where drag comes from, and checking roll behavior on finned designs.
Opening component analysis
To open the tool, go to Analyze → Component analysis in the menu bar. The window shows three tabs: Stability, Drag, and Roll.
At the top of the window you can select the Flight configuration and set the Mach number and Angle of attack to analyze. All tables update immediately as you change these values.
Stability tab
The Stability tab shows the contribution of each rocket component to the overall center of pressure (CP) location and to the normal force coefficient (CNα).
| Column | Description |
|---|
| Component | Name of the rocket component |
| CP | Center of pressure location measured from the nose tip |
| CNα | Normal force coefficient derivative — how much normal force this component contributes per radian of angle of attack |
Stability margin is defined as (CG − CP) / reference diameter. A margin of at least 1 caliber is the commonly recommended minimum for a stable flight. A margin above about 2 calibers may cause the rocket to weathercock excessively in wind.
Drag tab
The Drag tab shows the drag coefficient breakdown for each component, at the selected Mach number and angle of attack.
| Column | Description |
|---|
| Component | Name of the rocket component |
| Pressure CD | Pressure (form) drag coefficient |
| Base CD | Base drag coefficient (only applies to components with a flat base exposed to flow) |
| Friction CD | Skin friction drag coefficient |
| CD per instance | Total drag coefficient for one instance of this component |
| Total CD | Total drag coefficient contribution from all instances of this component |
- A blunt nose cone will have a large pressure drag contribution
- Long, thin tubes with rough surface finishes will have elevated friction drag
- Fins contribute both pressure and friction drag, and their count multiplies the per-instance value
To reduce drag, focus first on the components with the highest Total CD contribution. Small improvements to a high-drag component have more effect than the same change to a low-drag one.
Roll tab
The Roll tab shows the roll coefficients for each component that contributes to roll moments. This is relevant when fins are canted (swept or angled) intentionally to induce spin, or unintentionally due to manufacturing variation.
| Column | Description |
|---|
| Component | Name of the rocket component |
| Roll forcing coefficient (Clf) | Coefficient representing the aerodynamic force that drives the rocket to spin |
| Roll damping coefficient (Cld) | Coefficient representing the aerodynamic resistance to spinning |
| Total roll coefficient | Net roll coefficient for this component (Clf − Cld) |
A positive net total roll coefficient means the rocket will spin up in flight. Very high spin rates can cause roll-coupled instability. If you’re adding intentional spin (e.g., for stability in wind), verify that the resulting spin rate is within acceptable limits for your design.
How analysis values relate to simulation
The values shown in Component Analysis are computed at a single operating point (one Mach number and angle of attack). During an actual simulation, these values change continuously as the rocket accelerates, decelerates, and changes orientation.
To see how CP location, stability margin, drag coefficients, or roll coefficients evolve over an entire flight, add those variables to a simulation plot. See Advanced flight simulation for instructions on configuring simulation plots.