Holooly Plus Logo
Holooly Plus Logo

Question 5.1: Develop an expression for the aspect ratio Develop an expres......

Develop an expression for the aspect ratio
Develop an expression for the aspect ratio of a delta wing in terms of the leading edge sweep angle (\Lambda_{\mathrm{{LE}}}).

Step-by-Step
The 'Blue Check Mark' means that this solution was answered by an expert.
Learn more on how do we answer questions.
Report Answer

Referring to the sketch of the delta wing in Fig. 5.6, the wing area is

S={\frac{b c_{r}}{2}}

and the tan \Lambda_{\mathrm{LE}} is given by

\tan\Lambda_{\mathrm{LE}}={\frac{c_{r}}{(b/2)}}

Solving this second expression for {c}_{r}. and substituting it into the expression for the wing area, we obtain

S={\frac{b^{2}}{4}}\tan\Lambda_{\mathrm{LE}}

Substituting this expression for the wing area into the expression for the aspect ratio,

A R={\frac{b^{2}}{S}}={\frac{4}{\tan\Lambda_{\mathrm{LE}}}} (5.1)

Screenshot 2023-06-22 131047

Related Answered Questions

Question: 5.7

The pilot of an F-16 wants to maintain steady, level (i.e., in a constant altitude, horizontal plane) unaccelerated flight. Recall from the discussion at the start of this chapter, for flight in a horizontal plane, where the angles are small, the lift must balance the weight and the thrust supplied ...

Verified Answer:

The first step is to use straight lines to generat...
Question: 5.6

The pilot of an F-16 wants to maintain a constant altitude of 30,000 ft flying at idle power. Recall from the discussion at the start of the chapter, for flight in a horizontal plane (i.e., one of constant altitude), where the angles are small, the lift must balance the weight of the aircraft, ...

Verified Answer:

Let us first calculate the lower limit for the spe...
Question: 5.4

Calculate the local skin friction at a point 0.5 m from the leading edge of a flat-plate airfoil flying at 60 mIs at a height of 6 km. ...

Verified Answer:

Refer to Table 1.2 to obtain the static properties...
Question: 5.3

Consider tests of an unswept wing that spans the wind tunnel and whose airfoil section is NACA 23012. Since the wing model spans the test section, we will assume that the flow is two dimensional. The chord of the model is 1.3 m. The test section conditions simulate a density altitude of 3 km. The ...

Verified Answer:

First, we need to calculate the section lift coeff...
Question: 5.5

Estimate the subsonic parasite-drag coefficient This example will show how the subsonic parasite-drag coefficient for the F-16 can be estimated at a specific altitude. It is important to note that, unlike other aerodynamic coefficients, the subsonic drag coefficient is a function of altitude and ...

Verified Answer:

The first task is to estimate the wetted area of t...
Question: 5.2

Calculate the wing-geometry parameters for the Space Shuttle Orbiter To calculate the wing-geometry parameters for the Space Shuttle Orbiter, the complex shape of the actual wing is replaced by a swept, trapezoidal wing, as shown in Fig. 5.9. For the reference wing of the Orbiter, the root chord ...

Verified Answer:

(a) The area for the trapezoidal reference wing is...