HW $2-25$ points

Using the geometry given in Figure $5\mathrm{.}9$ and considering that the geometry is $2$D$,$ calculate the pressure

distribution over the nose of the body from the leading edge, $x=0\mathrm{.}01370207,$ to $x=3\mathrm{.}291.$ The

upstream flow Mach number is $M1=3,Y=1\mathrm{.}4,P1=101325Pa,T1=298\mathrm{.}15K.$

The geometry is defined by the following equation:

$y=-0\mathrm{.}008333+0\mathrm{.}609425**x-0\mathrm{.}092593**x^2$

Normalize the pressure distribution over the body by the upstream pressure, P$1.$

Plot P $/$ P$1$ using the following methods and compare your results to the pressure distribution given in

Figure $5\mathrm{.}10$:

a$)$ Newtonian method

b$)$ Modified Newtonian method

c$)$ Tangent$-$Wedge method

d$)$ Shock$-$Expansion method