Consider a thin airfoil of unit chord length placed in a Mach 2 supersonic freestream parallel to the x-axis. The airfoi
Posted: Tue Apr 26, 2022 4:52 pm
Consider a thin airfoil of unit chord length placed in a Mach 2
supersonic freestream parallel to the x-axis. The airfoil leading
edge is at x=0. The trailing edge is at x= 1. The lower surface of
the airfoil is flat, lying on the x-axis.
The upper surface is made of a parabolic arc: Z(x) = 0.04 * x *
(1 – x)
Compute and sketch Cp vs x/c using Ackert's theory. Compute Cl ,
Cd and the pitching moment coefficient at the leading edge Cm,LE
using Ackert's theory. Compute also the center of pressure. Show
all the work. Do not use a calculator for integration.
supersonic freestream parallel to the x-axis. The airfoil leading
edge is at x=0. The trailing edge is at x= 1. The lower surface of
the airfoil is flat, lying on the x-axis.
The upper surface is made of a parabolic arc: Z(x) = 0.04 * x *
(1 – x)
Compute and sketch Cp vs x/c using Ackert's theory. Compute Cl ,
Cd and the pitching moment coefficient at the leading edge Cm,LE
using Ackert's theory. Compute also the center of pressure. Show
all the work. Do not use a calculator for integration.