UFO Travel Calculator

The calculator evaluates complex relationships between mass, thrust, and aerodynamics. First, total mass ($M$) is determined by combining the bare hull weight, passenger load (assuming an average human mass of 80 kg), and the aggregate weight of the selected propulsion engines. Thrust ($T$) is calculated using individual engine output multiplied by the total engine count. Acceleration ($a$) is derived from Newton's second law: $a = T / M$. Maximum velocity ($v_{max}$) factors in aerodynamic properties, wing loading ($M/A$), air density ($ ho$), drag coefficient ($C$), and induced drag factor ($K$) through the quadratic formulation: $v_{max} = \sqrt{ \frac{T}{W}\frac{M}{A} + \frac{M}{A}\sqrt{ \left(\frac{T}{W}\right)^2 - 4CK } } / \sqrt{\rho C}$. Finally, travel time ($t$) is computed by dividing the total distance by the maximum velocity.

Imagine we are testing a prototype saucer craft with a hull weight ($UFOWeight1$) of 5,000 kg, equipped with 4 propulsion units weighing 200 kg each, carrying 5 passengers, and possessing an effective wing surface area ($Area1$) of 50 square meters. Step 1: Calculate total mass. Passenger load is $5 \times 80\text{ kg} = 400\text{ kg}$. Engine total weight is $4 \times 200\text{ kg} = 800\text{ kg}$. Total mass $M_1 = 5000 + 400 + 800 = 6,200\text{ kg}$. Step 2: Determine weight force $W_1 = 6200 \times 9.81 = 60,822\text{ N}$. Step 3: If total combined thrust is 300,000 N, acceleration equals $300,000 / 6200 = 48.39\text{ m/s}^2$. Step 4: Factoring standard atmospheric density and drag coefficients, the maximum velocity resolves to roughly 1,250 m/s. For a journey of 5,000 kilometers ($5,000,000\text{ m}$), the travel time is $5,000,000 / 1250 = 4,000\text{ seconds}$ (approximately 1.11 hours).

When modeling hypothetical craft, always ensure your units match standard international (SI) measurements—using kilograms for mass and meters for distance. Keep in mind that increasing passenger capacity automatically scales total mass, which directly dampens your potential acceleration unless paired with higher-thrust propulsion engines. Experiment with different wing-loading configurations to see how surface area impacts atmospheric drag versus vacuum performance.