What has happened to the thickness to chord ratio of the wings as jet fighters start to be designed for flight at supersonic speeds?
If a thinner airfoil section is used, the flow speeds around the airfoil will be less than those for the thicker airfoil. As the speeds have increased, the thickness-chord ratios have decreased. The F-104 (fig. 89(b)) was designed to achieve the minimum possible wave drag but was penalized with low subsonic lift.
How does thickness affect lift?
Increasing the thickness will increase the lift. Increasing the area will increase the lift. Increasing the camber will increase the lift. A symmetric airfoil, or even a flat plate at angle of attack, will generate lift.
What is wing thickness ratio?
In aeronautics, the thickness-to-chord ratio, sometimes simply chord ratio or thickness ratio, compares the maximum vertical thickness of a wing to its chord. It is a key measure of the performance of a wing planform when it is operating at transonic speeds.
What is chord and span?
The distance from the leading edge to the trailing edge is called the chord, denoted by the symbol c. The ends of the wing are called the wing tips, and the distance from one wing tip to the other is called the span, given the symbol s.
How is the thickness to chord ratio calculated?
Thickness to chord ratio is depicted by τ and camber to chord ratio by ω (see Fig 2 ). The solution is exact for τ → 0 and practically valid for slender airfoils (τ < 0.1), and includes a symmetrical airfoil (ω = 0, known as “Guderley’s cusp”) but also cambered wing sections with a ratio ω/τ up to 0.5.
How is the chord length of a rectangular wing determined?
For a rectangular wing, the chord length at every location along the span is the same. For most other planforms, the chord length varies along the span. The wing area, A, is the projected area of the planform and is bounded by the leading and trailing edges and the wing tips.
How is the chord length of an aircraft determined?
Usually, the chord length is greatest where the wing joins joins the aircraft’s fuselage (called the root chord) and decreases along the wing toward the wing’s tip (the tip chord ). Most jet aircraft use a tapered swept wing design.
How is the mean chord of a wing defined?
Standard mean chord (SMC) is defined as wing area divided by wing span: where S is the wing area and b is the span of the wing. Thus, the SMC is the chord of a rectangular wing with the same area and span as those of the given wing. This is a purely geometric figure and is rarely used in aerodynamics.