The fuel of a liquid-propellant rocket is usually kerosene or liquid hydrogen; the oxidizer is usually liquid oxygen. They are combined inside a cavity called the combustion chamber.
Chemical rockets have a maximum Isp of 500 seconds, with an exhaust velocity of 4,900 meters per second (m/s). Nuclear rockets can have Isp's of up to 6,000 seconds. A nuclear fission engine with 1,000 Isp will produce twice the speed of exhausted gases: 9,800 m/s
A: NASA's Juno spacecraft is the fastest man-made object ever recorded, at roughly 365,000 km/h (165,000 mph) as it approached Jupiter. The fastest launch velocity belongs to New Horizons, which went 58,000 km/h (36,000 mph) .
Professor, Just for your information which may help you and your students,
When we are learning to design an aircraft to fly under Earth Atmosphere,
Here TEMS ERA - WINGS OF AERO presenting you
Dr. Daniel Raymar (The Author of Aircraft Conceptual Design Book) who is going to deliver a lecture on "How to design manned aircraft which can fly in MARS"
Date: 1st October'20 Time: 08:00 PM (IST)
Register for free : https://wingsofaero.in/blog/danielraymer
E-certificate will be provided.
Surely it will be very much useful professor for you and your students...