Question

A model airplane wing is to be tested for de-icing experiments by subjecting it to a stream of air at 0 deg C. the wing surface is held at 5 deg C. it's chord length (=Lc) is 1 m, and the average heat flux over the whole surface is found to be 500W*m-2. estimate the heat flux from a prototype wing of similar design but chord length of 3m. assume temperature differences

Answer 1

If this is helpful, please UPVOTE. Thank you !!