## What is the drag coefficient of an airfoil?

The drag coefficient is a number which aerodynamicists use to model all of the complex dependencies of drag on shape, inclination, and some flow conditions. The drag coefficient Cd is equal to the drag D divided by the quantity: density r times reference area A times one half of the velocity V squared.

**What NACA 0015?**

The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.

### Which aircraft uses NACA 4412?

The NACA 4412 has been used in sports plane. The example includes AAI-AA2 mamba aircraft, aeronca series aircraft like aeronca 65-tac defender, aeronca 11ac chief etc while the S1223 is an airfoil used in heavy lift cargo planes [2].

**What is a good drag coefficient?**

Typical drag coefficients The average modern automobile achieves a drag coefficient of between 0.25 and 0.3. Sport utility vehicles (SUVs), with their typically boxy shapes, typically achieve a Cd=0.35–0.45. The drag coefficient of a vehicle is affected by the shape of body of the vehicle.

## Is a higher drag coefficient better?

A low coefficient is conducive to high top speed and low fuel consumption, while a higher drag coefficient is generally found in cars searching for high cornering speeds influenced by downforce. It shows that a car’s coefficient of drag can be found by analysing the drag force acting on the car at a given speed.

**How do you read NACA 5 Series?**

NACA Five-Digit Series: The first digit, when multiplied by 3/2, yields the design lift coefficient (cl) in tenths. The next two digits, when divided by 2, give the position of the maximum camber (p) in tenths of chord. The final two digits again indicate the maximum thickness (t) in percentage of chord.

### How does the NACA 0015 airfoil perform for lift and drag analysis?

The NACA 0015 airfoil was analyzed for the lift, drag and moment coefficients as planned. The measured values determined from lab data agree correctly with the theoretical values for the lift, drag and quarter chord moment. A stabilizing or restoring moment was observed after the stall occurred.

**What is the value of lift and drag coefficient?**

LIFT AND DRAG COEFFICIENTS Lift coefficient is a dimensionless quantity which is defined as = 2 (1) 2

## What are the factors that affect the accuracy of NACA results?

up to 1. 60. Reduction of Data The test data have been reduced to standard NACA coefficient form. Factors which could affect the accuracy of these results, together with the corrections applied, are discussed in the following paragraphs. Tunnel-wall interference.

**What is the NACA 0015?**

The NACA 0015 is a symmetrical airfoil with a 15% thickness to chord ratio. Symmetric airfoils are used in many applications including aircraft vertical stabilizers, submarine fins, rotary and some fixed wings. A 2D wing section is analyzed at low speeds for lift, drag and moment characteristics.