Hi rb1957,
it is computed from the flight data recorded. Hmmmmm... probably I would suggest one more run to verify the flight data @15k feet in clean configuration, what do you think?
and I observed that difference between the Cd0 values of clean and structural modified configurations tend to...
Hi all,
so I have managed to compute the Cdo (parasite drag) for the aircraft in clean configuration and with structural modification and are as follow:
Clean Config
@15k feet, Cd0= 0.0316
@10k feet, Cd0= 0.0282
@5k feet, Cd0= 0.0279
Structural modified
@15k feet, Cd0= 0.0308
@10k feet, Cd0=...
Hi rb1957,
Basically the objective of this project is to compare the Cd0 (parasite drag) of an aircraft with clean configuration and with installed structural modification. Of cause there is another set of similar flight data (also collected at 3 different altitude) for the aircraft with...
Hi rb1957,
this is not homework, I've long graduated but still kind of lost in this topic haha!
Can I clarify that so for the second method for finding Cd0 (CD against CL square), if 3 different data sets (for each altitude) are being plotted separately, wouldn't I be seeing 3 different Cd0...
Hi rb1957,
thanks for the clarification on the Cd0, yes it is the value of CD when CL=0, my mistake.
attached is the set of data collected from the test flight and the drag polar (CL vs CD) plotted by me using excel. Based on the drag polar plot, how do I determine the Cd0 (parasite drag) as I...
Hi all,
So I am working on a project (Flight testing) which requires me to calculate the parasite drag of the aircraft. The following are the parameters provided:
1. Pressure altitude (feet)
2. Airspeed (KCAS)
3. TAT (degree Celsius)
4. CL (Lift coefficient)
5. CL Square
6. CD (Drag...
