Missile Test Flight and Effective Launch Speed Calculator

This calculator helps determine missile effective launch speed, flight time, altitude gain, and range based on input parameters for missile design and test conditions.

Input Parameters

Calculation Results

Calculation Results

Effective Launch Speed: -- m/s

Maximum Altitude: -- m

Maximum Range: -- m

Flight Time: -- s

Burnout Time: -- s

Calculation Formula

Effective Launch Speed = √(Initial Velocity² + (Thrust Force × Angle Factor))

Where:
Initial Velocity: Starting speed of the missile
Thrust Force: Propulsion force applied
Angle Factor: sin(2 × Angle of Elevation)
Effective Launch Speed is calculated at burnout point

Missile Test Flight and Effective Launch Speed Calculator Usage Guide

Learn how to use the calculator for analyzing missile performance during test flights

How to Use This Calculator

  1. Enter the missile's initial velocity (starting speed in m/s)
  2. Input the launch angle of elevation (degrees from horizontal, 0-90)
  3. Specify the rocket's mass in kilograms
  4. Enter the thrust force in Newtons
  5. Input the fuel burn rate in kg/s
  6. Adjust gravity if needed (default is Earth's gravity: 9.81 m/s²)
  7. Click "Calculate" to compute the missile performance metrics
  8. Use "Reset" to clear all inputs and start over

Understanding the Results

  • Effective Launch Speed: The speed of the missile at burnout (when fuel is depleted)
  • Maximum Altitude: The highest point reached by the missile
  • Maximum Range: The horizontal distance traveled by the missile
  • Flight Time: Total time from launch to landing
  • Burnout Time: Time until fuel is completely consumed

Principle Explanations

This calculator uses simplified ballistic equations to estimate missile performance. It assumes a constant thrust force and neglects air resistance for simplicity. The effective launch speed combines the initial velocity with the additional speed gained from thrust, considering the angle of launch.

The maximum altitude and range calculations are based on standard projectile motion equations modified to account for the changing mass of the missile as fuel is consumed:

h = v₀² * sin²(θ) / (2g) + (F_t * t_b * sin(θ)) - 0.5 * g * t_b²

R = (v₀² * sin(2θ)) / g + (F_t * sin(2θ) * t_b) / g

Where:
h = maximum altitude
v₀ = initial velocity
θ = angle of elevation
g = gravity
F_t = thrust force
t_b = burnout time

Note: This calculator provides simplified estimates for educational purposes. Real-world missile performance would require more complex models considering air resistance, changing thrust profiles, and other factors.