## What is the drag coefficient of a NACA 0012?

NACA 0012 drag coefficient at a Reynolds number of 179,000 A coefficient of 0.7065 sounds much too low for an angle of 10°. We previously discussed a theoretical technique called Thin Airfoil Theory that matches reality quite well for airfoils below the stall angle.

## How do you calculate the coefficient of lift?

The lift coefficient is defined as: CL = L/qS , where L is the lift force, S the area of the wing and q = (rU2/2) is the dynamic pressure with r the air density and U the airspeed. Similarly, the drag coefficient is written as: CD = D/qS , where D is the drag force and the other symbols have the same meaning.

**What is the NACA number?**

(425) 602-6222 x4.

**What is the chord length of NACA 0012?**

1.0 m

NACA 0012 airfoil profile. Chord length is 1.0 m.

### What is the maximum camber of the NACA 2415 airfoil?

For the NACA 2415 airfoil, the maximum camber is 2%, the position of the maximum camber is 0.4c, and the thickness is 15%. This example is displayed in below.

### What do the numbers mean in the lift coefficient series?

The number “6” indicating the series. One digit describing the distance of the minimum pressure area in tenths of the chord. The subscript digit gives the range of lift coefficient in tenths above and below the design lift coefficient in which favorable pressure gradients exist on both surfaces.

**Is the flowfield of NACA 23018 airfoil with Gurney flap one-equation?**

CONCLUSION A computational study of the flowfieldpast NACA 23018 airfoil with Gurney flap has been conductedin detail using the commercial code Fluentwith the one-equation turbulence model of Spalart-Allmaras. Computational results are found to agree reasonably well with available experimental data.

**What is a NACA 1234 airfoil?**

For example, the NACA 1234-05 is a NACA 1234 airfoil with a sharp leading edge and maximum thickness 50% of the chord (0.5 chords) from the leading edge. In addition, for a more precise description of the airfoil all numbers can be presented as decimals.

#### What is a good coefficient of lift?

Lift Coefficient: Incidence The value of C L max is a very important airfoil characteristic because it determines the minimum speed at which an airplane can fly. A typical value for the type of airfoil section mentioned is about 1.5.

#### Why is NACA 0012 used?

NACA 0012 airfoil is chosen to model and simulate processes of computational fluid dynamics. Analyzes to obtain velocity and pressure distribution on the wing surface were performed using ANSYS Fluent software. Also, the drag and lift coefficients were calculated according to variable relative velocities.

**What is design coefficient of lift?**

The design lift coefficient determines the camber line of the airfoil. It is chosen such that the flow hits the airfoil exactly parallel to the start of the camber line when at the design lift coefficient. For a NACA 23015 this would be a lift coefficient of 0.15 x 2 = 0.3.

**What is the lift coefficient of a Boeing 747?**

0.52

A Boeing 747 is flying at an altitude of 12,192 meters and has a velocity of 265.5 m/s. The aircraft has a wing area of 510.97 m2. The coefficient of lift is 0.52 and the density is of air at 12,192 meters is approximately 0.30267 kg/m3. The weight of the 747 is 2,833,500 N (637,000 pounds).

## What does the lift coefficient tell us?

The lift coefficient then expresses the ratio of the lift force to the force produced by the dynamic pressure times the area.

## What does NACA 2412 airfoil mean?

Two digits describing maximum thickness of the airfoil as percent of the chord. For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord.

**What does NACA and NASA stand for?**

The National Advisory Committee for Aeronautics (NACA) came into being, much like its successor organization, the National Aeronautics and Space Administration (NASA), in response to the success of others.

**How do you find the coefficient of design lift?**

The lift coefficient Cl is equal to the lift L divided by the quantity: density r times half the velocity V squared times the wing area A. The lift coefficient then expresses the ratio of the lift force to the force produced by the dynamic pressure times the area.

### What is the lift formula?

The lift equation states that lift L is equal to the lift coefficient Cl times the density r times half of the velocity V squared times the wing area A. For given air conditions, shape, and inclination of the object, we have to determine a value for Cl to determine the lift.