The discussion revolves around calculating the tangential velocity of a satellite in a circular orbit 300 km above the Earth's surface, utilizing gravitational equations and understanding the relationship between altitude and orbital radius.
Participants are actively engaging in clarifying the calculations needed for the orbital radius and velocity. Some guidance has been provided regarding the need to convert units and ensure the radius used in calculations reflects the total distance from the Earth's center.
There is an ongoing discussion about the correct interpretation of the radius in the gravitational formula, with emphasis on the need to add the Earth's radius to the altitude of the satellite. Participants also highlight the importance of unit conversion in their calculations.
Use that to calculate the radius of the orbit, which will be "r".astru025 said:How do I incorporate the "300 km above Earth's surface" into this equation?.
In your calculation, you set r = radius of the earth. But that's not correct; r should be the radius of the orbit, which is bigger than the radius of the Earth (by the given amount).astru025 said:I use 300km to calculate the radius of the orbit. What is the equation for the radius?
Just add the altitude of the orbit, which was given, to the radius of the earth.astru025 said:Is there a special equation to find the radius of the orbit?
I don't understand how you got that answer. Did you make sure to put the radius in meters, not km?astru025 said:Okay so now I have : v^2= G (6.67E-11) x ((Me (5.98E24) / (r + 300 km. (6670 km))
Is this correct? So I got 244540.39.