Design and simulate compressed-air paper rockets launched from 1/2" PVC tubes
Paper cone taped on with electrical tape. Base slightly larger than rocket body. Stuffing adds forward weight for stability.
Heavy-duty packing tape wrapped around the full body for strength
3/4" wide electrical tape, ~0.18 mm thick per layer. Nose position moves CG forward for stability.
| Shape | Area Formula | Cd Effect |
|---|---|---|
| Triangle | 1/2 x span x root | Lowest drag |
| Trapezoid | 1/2 x span x (root+tip) | Moderate drag |
| Swept Delta | 1/2 x span x root | Good supersonic |
| Clipped Delta | 1/2 x span x (root+tip) | Most stable |
Rocket wraps around the tube. Rocket OD = tube OD = 0.840"
Center of Gravity (CG) must be forward of Center of Pressure (CP) for stable flight. Stability margin = (CP - CG) / diameter. Target: 1–2 calibers.
Shows how velocity and max height vary with chamber pressure, holding all other parameters constant.
| Chamber Pressure | 60 psi |
| Chamber Volume | 0 in³ |
| Launch Tube Volume | 0 in³ |
| Volume Ratio (C:B) | 0:1 |
| Exit Pressure | 0 psi |
| Adiabatic Work | 0 J |
| Valve Cv | 0 |
| Valve Open Time | 0 ms |
| Valve Efficiency | 0% |
| Time in Tube | 0 ms |
| Drag Coefficient (Cd) | 0 |
| Reference Area | 0 in² |
| Fin Drag Addition | 0 |
| Nose Cone Factor | 0 |
| Spin Rate | 0 RPM |
| Spin Decay Rate | 0 RPM/s |
| Reynolds Number | 0 |
| Terminal Velocity | 0 ft/s |
| Stability Margin | 0 cal |
| CG from nose | 0" |