I'll have a go.....
Using the relationship for incompressible lift from elliptical wing theory and Prandtl Glauert (or even better von Karman and Tsien) relationships, along with the tables here:
http://books.elsevier.com/companions...le-2/table.htm
you can work out a compressible lift coefficient assuming the lift curve slope of the two dimensional wing is 95% of the theoretical value and an angle of attack of 4 degrees in the cruise.
Suffice to say, lets call it 0.4 - because I can't be bothered to work it out otherwise.
You can then look in some magic tables which plot M_crit (zero sweep) against t/c ratio for various C_L.
The tables in the html file above give t/c ratio for 733 as ~12.9 and sweep as 25 degrees.
M_crit (zero sweep) is thus 0.69 according to my magic table.
Since M_crit (with sweep) is equivalent to M_crit (zero sweep) divided by the cosine of the sweep angle, I'm going for
M_crit (25 degrees sweep) = 0.75.
A good approximation of M_{drag divergence}, assuming that this is the Mach number where the gradient of the C_d versus Mach number curve reaches 0.05, is:
M_{drag divergence} = M_crit*[1.02 + (1-cos(sweep angle))*(0.08)]
This assumes two dimensional wing theory and applies only exactly to a wing of infinite span. It should be good for wings of high aspect ratio.
This gives
M_{drag divergence} ~= 0.77
We know
Mmo = 0.82 and
M_ne should be about 5% higher: ~= 0.86
I have observed Mach Tuck in a 737 sim before but I can't remember what Mach number it manifest itself at.
Someone tell me my guesses are right!
PS: The other good time to see shock waves is in humid conditions at TO which only serves to illustrate
Sam_airman's point about how dependent M_crit is on C_L.