I'm working on a conceptual design phase project for aerobatic aircraft (for university) and I can't seem to find any statistics about key aerodynamic properties (such as in the question), so I hope somebody here does know something about this subject?
First, don't take the two-dimensional value from an airfoil chart and use it for the full aircraft. Subtract 15-20% for wingtip margin and fuselage influence. Wingtip margin means that the wing is less loaded towards the tips to keep a lift margin for aileron control and to avoid a tip stall.
Next, aerobatic aircraft have lower maximum lift coefficients than GA aircraft. Their wing loading is lower, so they can afford this. A symmetric airfoil mounted at zero incidence has proven to be the best choice, and while some older aerobatic aircraft use cambered airfoils, the camber creates a distinct disadvantage in transitions from normal to inverted flight and vice versa.
And last, the maximum lift coefficient depends on quite a list of parameters. If you need a value for the calculation of structural loads, make sure you add enough strength to cover the increased lift possible with high pitch rates.
If you need a figure for a single-seater piston-powered aerobatic aircraft without flaps for the estimation of minimum speed, use a lift coefficient of 1.3.
The primary textbook for many (possibly most) University aerodynamic classes is FREE (Aerodynamics for Naval Aviators). This book explains all theoretical and practical knowledge needed to have a well rounded understanding of aerodynamics. It explains all the formulas needed to design an airplane in the real world. It does not get into the bizarre out of touch academia :)
Page 75 discusses span lift. https://www.faa.gov/regulations_policies/handbooks_manuals/aviation/media/00-80T-80.pdf
To directly answer your questions regarding aerobatic CL. Most purely refined aerobatic airplanes will use a symmetric or modified symmetric airfoil. The exact coefficient of lift depends on shape of the leading edge, chord width, and Reynold number (~speed vs chord width).
The 1.3 given above would be close to typical - perhaps a little low, but it depends on how rounded the leading edge is and the design speed of the aircraft. Airfoil books I have show very thin sharp symmetric airfoils at 1.2 and very fat ones at 1.6. Most are 1.4 to 1.5. But remember, the exact same airfoil will show minor differences due to wind tunnel peculiarities, and now most "testing" uses computer fluid dynamic simulation!
An example of a popular aerobatic plane is Extra 300 (symmetric airfoil) often used in Red Bull Competition https://en.wikipedia.org/wiki/Extra_EA-300
You can study various CL at
Other good books I use
An excellent basic series of how2 design aircraft was published in the EAA "Sport Aviation" magazine from February 1990 thru February 1991 primarily by John Roncz.