Experimental data for validation of a 2D conv-div nozzle in mach range 0.2-2.0
 

Dear reader,

I am looking for experimental data of a (non)adiabatic air flow trough a 2Dconverging-diverging nozzle in the Mach range of around 0.2 at the inlet to 2.0 Ma at the outlet for validation of a Boundary Layer code.
Most important are the velocity profiles and displacement thickness for the validation of my code. I am using the CS-model described by Cebeci and Smith from their 1974 book [1].

After searching, the only valuable thing I found was a plot of 'measured' displacement and momentum thickness in a nozzle in a NASA report by McNally [2]. However, the measurements did not go far beyond the throat, and no velocity profiles were available.

Does anybody now a nozzle case with experimental data for air in this Mach range? Thank you in advance.

[1] Analysis of turbulent boundary layers; Cebeci, T.; Smith, A.M.O.; 1974
[2] FORTRAN Program for calculating compressible laminar and turbulent boundary layers in arbitrary pressure gradients; McNally, D.; 1970