Recent content by suwinhua

i think u may set value for the choked point to check the effect of it. i checked some references. the result may be plus. the first reason is the way can not measure the effect of frictional force, the second reason is the result of drag is not precise, we usually use the momentum conservation...

it means where and how u fix the airfoil. some NACA series is unusual. it is not easy to measure the drag precisely. u may check the measure system carefully, including pressure measurement point, the compute procedure. wind tunnel test is very hard. u must pay attension to all details...

I think there may be some interference in the test results. the force direction is right. drag at some point of the airfoil may be nagtive. but the total drag must point downward. may be the renolds is very small,so the friction drag is small. and what support did you use in the test? there may...

also i want to ask the wall presure signature methods. which one is more credible.

1.i want to use the engineering method to evaluate the support interference value. i think the sigularity method may be valid, but i don't know how to simulate and decompose the support effect. 2.when i do the two step mirrior method to measure the support interference , the mirror and the main...

I will do research on the vertical single strut. i want to ask if there is something interesting to study?