HEALY, You may find the following of use
http://www.hq.nasa.gov/pao/History/SP-468/ch10-4.htm
Towards the bottom of the page you will find a section headed
"Stalling of Swept Wings".
Is indeed a complex subject as the following shows from
http://adg.stanford.edu/aa241/drag/sweepncdc.html
"Near the wing tip the flow around the tip from the lower to upper surface obviously alters the effect of sweep. The effect is to unsweep the spanwise constant pressure lines known as isobars. To compensate, the wing tip may be given additional structural sweep. It is at the wing root that the straight fuselage sides more seriously degrade,the sweep effect by interfering with curved flow. Airfoils are often modified near the root to change the basic pressure distribution to compensate for the distortions to the swept wing flow. Since the fuselage effect is to increase the effective airfoil camber, the modification is to reduce the root airfoil camber and in some cases to use negative camber. The influence of the fuselage then changes the altered root airfoil pressures back to the desired positive camber pressure distribution existing farther out along the wing span."
Always wondered why the Boeings had flat topped, no camber on the upper surface aft of about the quarter chord. Guess this is why. Mad (Flt) Scientist?