Heat transfer is an integral part of understanding ice accretion in flight. For the speeds expected for small UAS, the heat transfer behavior is in an uncertain range. In order to better understand ice accretion on these aircraft, a heat flux sensor will be flown in icing temperature ranges.
The cylindrical sensor will give heat transfer measurements as a function of angle of attack, or distance from stagnation line. The heat transfer measurements will be made by heat transfer gages contained in a cylinder mounted on the aircraft in the free stream. Each gage consists of a thermocouple and small foil heater fixed onto a leading edge plate with aluminum filled epoxy. Each of these sensors is then placed into the cylinder as shown.
The data will improve and verify the in-house cylinder ice accretion code and can serve as additional inputs into
the LEWICE simulations.