Alternate Approach to the P-38 Compressibility Problem

[Aeroweanie]

Hi Dave - my question was awkwardly expressed. More directly, can the code compare boundary layer build up in turbulent flow to predict approximate location of adverse pressure gradient triggering full blown separation? I have always pondered comparisons between a NACA 23016 configured wing with the NAA/NACA 45-100 to better understand the pressure drag comparisons.

Definitely - we do that all the time

 

[drgondog]

Definitely - we do that all the time View attachment 861563

am I looking at preliminary pressure loss inboard of WS 50-70 at approx 40% chord due to the extended chord achieved by the wing crank from fuselage? with full developed shock wave in 50-60% range