I have a question about a second part of the original problem.

The original problem calculated a semimajor axis (a) and eccentricity of its orbit (e).

those answers were (a) = 8388.14 km and (e) = 0.1848 I was able to get these correct, based on this

Given those answers above, The next question asks me to determine the altitude above the Earth of the orbit when the true anomaly isv = 65.

I know that for true anomaly we have R = a(1-e²) / 1 + cos(v)

Given v= 65⁰

so I thought this would be (8388.14 km) x (1 - 0.1848²) / 1 + cos(65⁰)

I get 9041.45 km for the altitude

but I looked this up and found the answer to be 1164km.

Can someone help explain this or solve this to help me with the correct answer?