A,25 • EFFECT OF MACH NUMBER ON TRANSITION 



M = 0.50, aco = 0.03° M = 0.55, a«, = 0.03' 



-0.8 



0.8 



1.6 



0.8 



a 



8 



0.8 



1.6 

 1.6 



0.8 



0.8 



1.6 



M = 0.70, a„ = 0.02° 



M=r 0.86, aoo = 0.02^ 



] 



D 



0.2 0.4 0.6 0.8 1.0 0.2 0.4 0.6 0.8 1.0 



x/c 



Fig. A,25b. Pressure distribution on modified NACA 0012 

 airfoil as a function of Mach number. 



There are a few investigations of transition on bodies of revolution 

 without heat transfer at supersonic speeds. Czarnecki and Sinclair [111] 

 measured transition on the parabolic^^body of revolution RM-10 in the 

 NACA Langley 4-foot wind tunnel. A transition Reynolds number of 

 11.5 miUion was observed. A further investigation [112] in the same wind 

 tunnel was made on an ogive cyUnder, a cone cyhnder, and an RM-10 



(59) 



