F,23 • CITED REFERENCES 



10 12 14 16 



Mach number Moo 



20 



Fig. F,22i. Effect of dissociation on heat transfer at the stagnation point of a sphere 

 at 100,000-ft altitude in the ICAO atmosphere. Wall temperature at 2500°R. 



F,23. Cited References. 



1. Crocco, L. Lo strato limite laminare nei gas. Ministero delta Difesa-Aeronautica, 

 Roma., Monografie Scientifiche di Aeronautica 3, 1946. Transl. in Aerophys. Lab., 

 North Amer. Aviation Rept. AL-684, 1948. 



2. van Driest, E. R. Investigation of laminar boundary layer in compressible fluids 

 using the Crocco method. NACA Tech. Note 2597, 1952. 



3. van Driest, E. R. The laminar boundary layer with variable fluid properties. 

 Heat Transfer and Fluid Mech. Inst., Berkeley, 1954. 



4. Keyes, F. G. The heat conductivity, viscosity, specific heat, and Prandtl num- 

 bers for thirteen gases. Mass Inst. Technol. Project SQUID Tech. Rept. 37, 1952. 



5. Tables of the Thermal Properties of Gases. Natl. Bur. Standards Circular 564, U.S. 

 Government Printing Office, 1955. 



6. Hantzsche, W., and Wendt, H. Jahrbuch deut. Luftfahrtforschung 76, 1941. 



7. Goldstein, S. Modern Developments in Fluid Dynamics, 1st ed.. Vol. 2. Oxford 

 Univ. Press, 1938. 



8. Homann, F. Z. angew Math. u. Mech. 16, 159 (1936). 



9. Sibulkin, M. J. Aeronaut. Sci. 19, 570 (1952). 



10. Grimminger, G., Williams, E. P., and Young, G. B. W. J. Aeronaut. Sci. 17, 675 

 (1950). 



11. Korobkin, I. Laminar heat-transfer characteristics of a hemisphere for the Mach 

 number range 1.9 to 4.9. Nav. Ord. Lab. Rept. 3841, 1954. 



12. Stine, H. A., and Wanlass, K. Theoretical and experimental investigation of 

 aerodynamic-heating and isothermal heat-transfer parameters on a hemispherical 

 nose with laminar boundary layer at supersonic Mach numbers. NACA Tech. 

 Note 3344, 1954. 



< 425 > 



