Write a matlab code for vortex panel method.
Write a matlab code for vortex panel method.
©2024 aerospaceanswers.com
Terms & Privacy
Terms & Privacy
-
LATEST QUESTIONS
-
Consider an airplane in an accelerated climb. At a given instant in this climb, the specific excess power is 120 ft/s
-
Consider an airplane flying at 620 mi/h at 35,000 ft. Calculate its energy height.
-
For a turbojet-powered airplane with the altitude variation of thrust given by Eq. (3.19), show that as the altitude increases, the maximum velocity decreases.
-
The BD-5J is equipped with plain flaps. The airfoil section at the wing root is an NACA 64-212, and interestingly enough, it has a thicker section at the tip, an NACA 64-218.
-
For the BD-5J, calculate (a) The maximum value of CL/CD (b) The maximum value of CL^(1/ 2) /CD
-
-
RELATED QUESTIONS
-
Calculate the velocity at a point on the airfoil.
-
In an inviscid, incompressible flow of air along a streamline, the air density is 0.002377 slug/ft^3. Find the pressure at a point.
-
Show that a uniform flow with velocity \({V_\infty }\) is a physically possible incompressible flow and is irrotational.
-
For a source flow, show that it is a physically possible incompressible flow except at origin. Also, show that it is irrotational.
-