Method and system for reducing a temperature differential across a flight vehicle

A method for reducing a temperature differential across an exterior of a flight vehicle, the method comprising:

• advancing the flight vehicle at a flight speed of at least Mach 3, wherein the exterior of the flight vehicle is aerodynamically heated via advancing the flight vehicle at the flight speed, and wherein the exterior includes a first exterior panel being at a first initial temperature and a second exterior panel being at a second initial temperature, wherein the first initial temperature is greater than the second initial temperature, and a temperature difference between the first initial temperature and the second initial temperature defines an initial temperature differential;
• circulating a supercritical working fluid through a fluid loop, wherein the fluid loop is coupled to the first exterior panel and the second exterior panel;
• transferring heat from the first exterior panel to the supercritical working fluid, which decreases the first initial temperature of the first exterior panel to a first altered temperature and heats the supercritical working fluid;
• and circulating the heated supercritical working fluid from the first exterior panel and using the heated supercritical working fluid to heat the second exterior panel to a second altered temperature greater than the second initial temperature, wherein a temperature difference between the first altered temperature and the second altered temperature defines a secondary temperature differential less than the initial temperature differential.