Helpful factoids about orbits. To raise an orbit, you need a force that "pushes from behind", who's net effect accelerates you in the prograde direction. For circular orbits you can call that the $+\theta$ or tangential or $\mathbf{\hat{v}}$ direction. Counterintuitively this push from behind slows you down by an amount equal to the delta-v imparted, but it does raise your orbit.
Drag actually speeds you up by pushing against you, but lowers your orbit.
Aerodynamic drag always pushes in the exact opposite direction of your motion, because that's the definition. Aerodynamic effects on spacecraft in directions perpendicular to your velocity (radial or out-of-plane) are called lift.
The problem with comparing aerodynamic drag to effects from the solar wind or photon pressure is that those particles and photons are moving so much faster than the spacecraft's motion around the Earth, or the spacecraft plus Earth's motion around the Sun. These effects could be prograde at one point in the orbit and retrograde a half an orbit later, and ultimately substantially average out in some cases.
So it's a bit of an apples-to-oranges comparison.
However, in the plot below, the author has tried to show accelerations caused by various effects in an order-of-magnitude sort of way. For example, at an altitude of about 1300 km the acceleration due to solar radiation pressure is about the same size as that due to drag during maximum solar activity. Drag at high altitude is dramatically modulated by heating and expansion of the atmosphere by particles from the Sun, so actually both are caused by the Sun even though one also involves the atmosphere.
Below is borrowed from my answer to the question The sorting of perturbational effects by the power (used here as well).
I found the following plot in the book Satellite Orbits; Models, Methods, Applications by Oliver Montenbruck and Eberhard Gill, Springer, 2000. The figure and description can also be found in google books. It's a low quality snapshot but it's hard to capture a dozen different dependencies over 20 orders of magnitude without showing the whole thing.
Here is the bit of text that discusses the figure in more detail:
The effect of various perturbations a s a function of geocentric satellite distance is illustrated in Figure 3.1. For the calculation of the influence of atmospheric drag on circular low-Earth satellite orbits, exospheric temperatures between 500K and 2000K (cf. Sect. 3.5) have been assumed. The area-to-mass ratio used in the computation of non-gravitational forces is 0.01 m2/kg. For specially designed geodetic satellites like LAGEOS, the corresponding value may be smaller by one or two orders of magnitude. The perturbations due to various Geopotential coefficients Jn,m and the lunisolar attraction have been calculated from rule-of-thumb formulas by Milani et al. (1987). For the purposes of comparison it is mentioned that a constant radial acceleration of 10-11 km/s2 changes the semi-major axis of a geostationary satellite by approximately 1 m.
Aside from the aforementioned forces, various minor perturbations are considered in Fig. 3.1 which produce accelerations in the order of 10-15 to 10-12 km/s2. The most are due to the radiation pressure, resulting from the sunlight reflected by the Earth (albedo), as well as relativistic effects and the solid Earth tides.
