1)What must be the orbital speed of a satellite in a circular orbit 740 above the surface of the earth?

2)What is the period of revolution of a satellite with mass that orbits the earth in a circular path of radius 8000 (about 1630 above the surface of the earth)?

You must provide units with your numbers. You should have learned that by now

Since 8000 - 1630 = 6370, the radius of the earth in km, I believe I am on safe ground assuming that you mean "740km" above the earth in your first question.

The velocity required to maintain a circular orbit derives from Vc = sqrt(µ/r) where Vc = the velocity in m/s, µ = the earth's gravitational constant, 3.9863x10^14 m^3/sc^2 and r = the orbital radius in meters.

Therefore,
Vc = sqrt[3.9863x10^14/(6370+740)1000]

The period of a particular orbit derives from
T = 2(Pi)sqrt(r^3/µ)

I'll let you complete this one.

To find the orbital speed of a satellite, we can use the formula:

V = sqrt(G * M / r)

Where:
V = orbital speed
G = gravitational constant (approximately 6.67 x 10^-11 N(m/kg)^2)
M = mass of the Earth (approximately 5.97 x 10^24 kg)
r = distance from the center of the Earth to the satellite (in this case, 740 km above the surface of the Earth)

1) Plugging in the values into the formula:
V = sqrt((6.67 x 10^-11 N(m/kg)^2) * (5.97 x 10^24 kg) / (740 km))

Note: The distance should be converted to meters.
740 km = 740,000 meters

V = sqrt((6.67 x 10^-11 N(m/kg)^2) * (5.97 x 10^24 kg) / 740,000 m)

Calculating the result will give us the orbital speed of the satellite in meters per second.

2) The period of revolution (T) is the time it takes for a satellite to complete one full orbit. It can be calculated using the formula:

T = (2 * π * r) / V

Where:
T = period of revolution
π = pi (approximately 3.14159)
r = radius of the circular path (in this case, 8000 km above the surface of the Earth)

2) Plugging in the values into the formula:
T = (2 * π * 8000 km) / V

Again, the distance should be converted to meters.
8000 km = 8,000,000 meters

T = (2 * π * 8,000,000 m) / V

Calculating the result will give us the period of revolution in seconds.

To answer the first question, you need to calculate the orbital speed of the satellite in a circular orbit 740 km above the surface of the Earth.

The orbital speed of a satellite can be determined using the formula:
v = √(GM/r)

Where:
v is the orbital speed,
G is the gravitational constant (approximately 6.67430 × 10^-11 m^3 kg^-1 s^-2),
M is the mass of the Earth (approximately 5.972 × 10^24 kg), and
r is the distance between the center of the Earth and the satellite's orbit (in this case, 740 km above the surface, so r = 740 km + radius of the Earth).

To calculate the orbital speed, you can follow these steps:
1. Convert the distance from km to meters by multiplying by 1000.
2. Add the radius of the Earth (approximately 6,371 km) to the distance.
3. Plug these values into the formula, and solve for v.

For the second question, you need to calculate the period of revolution of a satellite with mass that orbits the Earth in a circular path with a radius of 8000 km (about 1630 km above the surface of the Earth).

The period of revolution, denoted as T, is the time it takes for a satellite to complete one full orbit around the Earth.

The period can be calculated using the formula:
T = 2π√(r^3)/(GM)

Where:
T is the period of revolution,
r is the distance between the center of the Earth and the satellite's orbit (in this case, 8000 km + the radius of the Earth),
π is a mathematical constant (approximately 3.14159),
G is the gravitational constant (approximately 6.67430 × 10^-11 m^3 kg^-1 s^-2),
and M is the mass of the Earth (approximately 5.972 × 10^24 kg).

To calculate the period of revolution, you can follow these steps:
1. Convert the distance from km to meters by multiplying by 1000.
2. Add the radius of the Earth (approximately 6,371 km) to the distance.
3. Plug these values into the formula, and solve for T.