A • TRANSITION FROM LAMINAR TO TURBULENT FLOW 



M = 0.29, Ooo = 0.02° M = 0.40, a.. = 0.03° 



- 0. 



0.8 



1.6 



0.8 



0.8 



1.6 

 - 1.6 



-0.8 



0.8 



M = 0.60, ace = 0.03' 



M = 0.80, a^ r= 0.04° 



M - 0.65, a„ = 0.02= 



□ 



M = 0.84, a„ = 0.03^ 



0.2 0.4 



0.2 0.4 0.6 0.8 1.0 



model, all of fineness ratio 12.2. Measurements were made of transition 

 and skin friction at Mach numbers from 1.2 to 2.2 and tunnel pressures 

 from 0.125 to 2.25 atmospheres. The approximate Reynolds numbers for 

 transition at the base were 2.5 million for the cone cylinder, 4.7 million 

 for the ogive cyhnder, and 11 miUion for the RM-10. 



Data on a 20° cone cylinder obtained in the NOL 40 cm aerobalistics 

 wind tunnel No. 2 at Mach numbers from 1.86 to 4.24 are reported by 

 Potter [113]. The observed transition Reynolds number increased from 



< 60) 



