[nicholas1339]

Hi everyone,

I'm using Fluent to determine the drag on an aircraft. Fluid flow is set at 16.3 m/s and the cd result i get is 0.017785, and a drag force of 3.218N. In power terms this is 52.45W.

The total thrust force for the aircraft is 8.34N and hence 133W at 16.3m/s.

This means that the drag is equivalent to 52.45/133*100 = 39.4% of the total thrust. This appears to be huge to me and I would like to know if this appears to be sensible.

For reference, the aircraft is shaped like the 'B-2 spirit' bomber, and hence is relatively steamlined.

Any assistance would be appreciated. Thanks!

[moh_zain]

you can read more about thrust to drag ratio in aircraft performance look at the book https://www.google.com/url?sa=t&rct=...os50Nh5jUS_mTr