Carl Alexander

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Carl Alexander
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Apollo 11 Mission Overview | NASA

Apollo 11 Mission Overview | NASA

Beginner's Guide to Aeronautics - NASA Glenn Research Center

Beginner's Guide to Aerodynamics: This NASA site offers a collection of information pages, activity pages, tools, and resources for students of all ages.

How rockets apply Newtons Third Law to overcome the forces or Earth πŸš€πŸš€πŸš€πŸš€ #dragon #nasa #saturnv #space #exploration #spacex #mars #aerospace #aerospaceengineering #mechanicalengineering #engineer #engineering #engineeringmemes #engineeringlife #instadaily #dailyposts #dailyengineering #engineeringdaily #engineeringstudents #physics #mathematics #innovation #technology #instaaviation #computeraideddesign

How rockets apply Newtons Third Law to overcome the forces or Earth πŸš€πŸš€πŸš€πŸš€ #dragon #nasa #saturnv #space #exploration #spacex #mars #aerospace #aerospaceengineering #mechanicalengineering #engineer #engineering #engineeringmemes #engineeringlife #instadaily #dailyposts #dailyengineering #engineeringdaily #engineeringstudents #physics #mathematics #innovation #technology #instaaviation #computeraideddesign

NASA, Boeing rewriting the book on building the SLS Core Stage – NASASpaceFlight.com

NASA, Boeing rewriting the book on building the SLS Core Stage – NASASpaceFlight.com

Derivation of the ideal rocket equation which describes the change in  velocity as a function of the exit velocity of the rocket and the change in mass of the rocket during the burn.

Derivation of the ideal rocket equation which describes the change in velocity as a function of the exit velocity of the rocket and the change in mass of the rocket during the burn.

Computer drawing of a rocket nozzle with the equation  for thrust. Thrust equals the exit mass flow rate times exit velocity  plus exit pressure minus free stream pressure times nozzle area.

Computer drawing of a rocket nozzle with the equation for thrust. Thrust equals the exit mass flow rate times exit velocity plus exit pressure minus free stream pressure times nozzle area.

Computer drawing of a rocket engine with the math equations   necessary to compute the theoretical thrust.

Computer drawing of a rocket engine with the math equations necessary to compute the theoretical thrust.