This paper investigates aerodynamic heating on a flared cone in a Mach 6 wind tunnel. Two data processing methods to calculate the Stanton number and recovery factor simultaneously are presented, using the experimentally measured wall temperature in a hypersonic wind-tunnel test. The first method is the linear fitting of the measured temperature and calculated heat flux. The second method is to solve an inverse problem of a one-dimensional transient heat conduction equation with the convection boundary condition. Distributions of heat flux, Stanton number, and recovery factor for the flared cone with a smooth wall or wavy wall are obtained. Compared with the smooth wall, the wavy wall can remove the local high Stanton number region before the boundary-layer transition. In addition, the wavy wall can reduce the growth rate of Stanton number in the boundary-layer transition and delay the transition process.
Heat Transfer and Recovery Factor of Aerodynamic Heating on a Flared Cone
AIAA Journal ; 59 , 11 ; 4284-4292
2021-10-06
9 pages
Article (Journal)
Electronic Resource
English
Hypersonic Stability Analysis of a Flared Cone
AIAA | 2013
|Hypersonic Stability Analysis of a Flared Cone
British Library Conference Proceedings | 2013
|Aerodynamic performance of flared fan nozzles used as inlets
TIBKAT | 1976
|WAVE PACKETS ON A FLARED CONE AT MACH 6
TIBKAT | 2020
|