I spent 2 years of maths and physics at school to get into university, then 3 years doing my undergraduate degree in aeronautical engineering - and could work this out. Not from the minimum amount of information provided, but from a more complete data set certainly.
To do so reasonably accurately would take me a while, and if I was preparing for the flight test programme on this little single seater described by the OP I'd do so, of course.
Basically
(1) Estimate the zero lift drag coefficient; I'd do that from ESDA data sheets and a drawing of the aeroplane.
(2) Estimate the oswald span efficiency factor, ditto + aerofoil data. That'll give me Cdi with AoA.
(3) Work out the approximate powerplant propulsive efficiency. I've not done that in 20+ years, but IIRC how to do that is well explained in this book
9780471078852: Introduction to Aircraft Performance, Selection and Design - AbeBooks - Hale, Francis J.: 0471078859
(4) Work out a drag polar at this mass
(5) Work out a thrust polar at this altitude and full power
(6) Co-incide the two, where the lines cross is Vh, or maximum achievable speed in level flight.
And don't forget to account for CAS/TAS variations with altitude, and engine power with density.
Ultimately however, Piperboy is right - you'll still want to go and fly it and see what really happens, as the above is only an estimate.
But it isn't one of those things that lend itself to a simple prescriptive "here's the order to do the sums".
But, there's nothing wrong with self education. Here's the order I'd go through the books.
Stinton is a superb book (and he was a superb man), but actually if you want an introduction to the very basics of aircraft configuration design, I'd start with this.
Then progress to Stinton (which I still think is better than Raymer's more advanced books, but Raymer's initial book is a brilliant explanation of the general process).
However, these last two are design books, not necessarily essential for understanding performance of an existing design.
G