vchi
- 1
- 0
- Homework Statement
- I was trying to look for an L/D ratio published on the web for the F-117 Nighthawk, and I can't seem to find it; need it for a class project. Since I couldn't find it, I wanted to try calculating myself, but still can't seem to find $$C_l$$ or $$C_d$$ without some sort of paywall on research papers, which I'm not even sure has them in it.
- Relevant Equations
- $$L = \frac{1}{2} C_{l} \cdot \rho v^2 A$$ ........................ lift equation
$$D = \frac{1}{2} C_{d} \cdot \rho v^2 A$$ ...................... drag equation
I was trying to look for an L/D ratio published everywhere on the web and I can't seem to find it for our project. Since I couldn't find it, I wanted to try calculating myself. Can't seem to find $$C_l$$ or $$C_d$$ though without some sort of paywall on research papers.
So L/D would just be:
$$\frac{L}{D} = \frac{C_l}{C_d}$$
or would the effective area be different for L and D, where L is the area of the top/bottom view of the plane, and D is the area of the front/back view? If this were the case then L and D would have to be determined separately.
The problem is that I'm still missing the C_l and C_d, for the F117, to complete this calculation. Does anyone happen to have access to this? Or is it top secret or something? Been scouring the internet for a couple hours now trying to look for it.
So L/D would just be:
$$\frac{L}{D} = \frac{C_l}{C_d}$$
or would the effective area be different for L and D, where L is the area of the top/bottom view of the plane, and D is the area of the front/back view? If this were the case then L and D would have to be determined separately.
The problem is that I'm still missing the C_l and C_d, for the F117, to complete this calculation. Does anyone happen to have access to this? Or is it top secret or something? Been scouring the internet for a couple hours now trying to look for it.