λ+Performance+Projections

Performance Projections
Using several known facts about the rocket and the Estes B6 engine, we were able to calculate estimates for the rocket's performance. These do not account for factors such as drag, wind, or non-verticality of launch.

Maximum velocity
M (mass of rocket) = 110g = 0.11kg Fa (B6 avg. thrust) = 6N T (B6 burn time) = 0.85s V1 = 0 V2 = ? A = ? D1 (distance under power) = ?

Fg = MA Fg = 0.11(9.8) Fg = 1.1N

Fnet = Fa - Fg __Fnet = 4.9N__

F = MA 4.9 = 0.11A __A = 45 m/s^2__

V2 = V1 + AT V2 = 0 + 45(0.85) __V2 = 38 m/s__

Maximum velocity of 38 m/s will occur just as the fuel is exhausted.

V2^2 = V1^2 + 2AD 1444 = 0 + 2(45)D1 1444 = 90D1 __D1 = 16m__

Maximum Altitude
V1 = 38 m/s V2 = 0 Ag = -9.8 m/s^2 D1 = 16m D2 (distance coasting) = ? D (max. altitude) = ?

V2^2 = V1^2 + 2AD 0 = 1444 + 2(-9.8)D2 19.6D2 = 1444 __D2 = 74m__

D = D1 + D2 __D = 90m__

Assuming vertical launch and no air resistance, the rocket should achieve 38m/s max. velocity and a 90m apogee.

λ - Design - Performance Projections - Materials - Time Line   Primary Launch -  Secondary launch - Analysis  - Conclusion   Lab Report