# How do I calculate the change in the argument of periapsis after a plane change maneuver?

Let's say I have a spacecraft in an initial geocentric orbit with the following parameters: a = 7,960,000 m, e = 0.010, $$\Omega$$ = 180$$^{\circ}$$, i = 98$$^{\circ}$$, $$\omega$$ = 90$$^{\circ}$$, $$\theta_0$$ = 20$$^{\circ}$$.

I perform a plane change maneuver with $$\theta$$ = 1.19661$$^{\circ}$$ at a true anomaly f$$_1$$ = -48.1904$$^{\circ}$$ that alters my inclination to 98.8911$$^{\circ}$$ and my right ascension to 179.1926$$^{\circ}$$. Since it's a pure plane change, this shouldn't alter my semimajor axis or eccentricity, but I don't know how to calculate how this would change my spacecraft's argument of perigee or how to calculate my new true or mean anomaly from there.