Solutions to Problems

15.1 Solution to Problem 1

15.1.1 Thin Airfoil Theory (2-D Inviscid Flow)

15.1.1.1 Quiz

In subsonic flow, the aerodynamic coefficient dependency upon the small parameters is given in Table 15.1. In supersonic flow, the aerodynamic coefficient dependency upon the small parameters is given in Table 15.2.

15.1.1.2 Lift Coefficient

The lift coefficient Ci in incompressible flow (low speed) is given by

Solutions to Problems

6.28(0.0873 + .04) — 0.8

 

At M0 — 0.7, using Prandtl-Glauert correction one finds

Solutions to Problems

15.1.1.3 Drag Coefficient

If the drag coefficient of the same profile at a — 0 and M0 — 1.4 is (Cd)M0—1.4 — 0.02, the drag at M0 — 2. is given by © Springer Science+Business Media Dordrecht 2015

J. J. Chattot and M. M. Hafez, Theoretical and Applied Aerodynamics,

DOI 10.1007/978-94-017-9825-9_15

Aerodynamic coefficient

e/c

d/c

a

Ci

n

y

y

Cm, o

n

y

y

C

m, ac

n

y

n

Cd

n

n

n

Table 15.1 Subsonic flow

Подпись: 0.02 = 0.0113
Solutions to Problems
Подпись: 0.9798 1.732
Подпись: (Cd )M0=2

Aerodynamic coefficient

e/c

d/c

a

Ci

n

n

y

Cm, o

n

y

y

Cm, ac

n

y

n

Cd

y

y

y

Table 15.2 Supersonic flow

Подпись: Cd (a) Solutions to Problems Подпись: 0.289

At M0 = 2. if a — 5° then

The drag coefficient at M0 = 0.7 is

(Cd )M0=0.7 = 0

since this is a 2-D, inviscid, subsonic flow.

Leave a reply

You may use these HTML tags and attributes: <a href="" title=""> <abbr title=""> <acronym title=""> <b> <blockquote cite=""> <cite> <code> <del datetime=""> <em> <i> <q cite=""> <s> <strike> <strong>