Is it possible to have 0 drag?

No, it is not possible to eliminate induced drag completely. Many parasite drag/induced drag graphs erroneously have induced drag approaching zero.

What is lift drag formula?

The lift to drag ratio (L/D) is the amount of lift generated by a wing or airfoil compared to its drag. The lift/drag ratio is used to express the relation between lift and drag and is determined by dividing the lift coefficient by the drag coefficient, CL/CD.

How do you calculate drag area?

The drag equation states that drag D is equal to the drag coefficient Cd times the density r times half of the velocity V squared times the reference area A. For given air conditions, shape, and inclination of the object, we must determine a value for Cd to determine drag.

What is no lift drag?

When you place that object at different angles of attack, you will find certain configurations that do not generate any lift at all. These configurations give you no-lift drag. A smooth sphere, for example, generates no lift at all however you face it into the airflow, but always generates drag.

Can you have drag without lift?

Technically, drag is not necessary for flight to be achieved. However, it is impossible to completely eliminate drag during flight without eliminating air. Air is needed to generate lift, so although drag is not completely necessary for flight, an airplane that achieve’s lift will always experience some form of drag.

Can a lift coefficient be zero?

is a dimensionless parameter which relates an aircraft’s zero-lift drag force to its size, speed, and flying altitude. value of 0.0161 for the streamlined P-51 Mustang of World War II which compares very favorably even with the best modern aircraft.

What is lift drag?

Lift and drag are aerodynamic forces that depend on the shape and size of the aircraft, air conditions, and the flight velocity. Lift is directed perpendicular to the flight path and drag is directed along the flight path. Under cruise conditions thrust is equal to drag. A low drag aircraft requires low thrust.

How do you solve a lift?

To calculate coefficient of lift: Multiply fluid pressure by velocity squared and divide the product by 2.

How do you calculate lift?

How do you calculate lift and drag coefficient?

The induced drag coefficient is equal to the square of the lift coefficient (Cl) divided by the quantity: pi (3.14159) times the aspect ratio (Ar) times an efficiency factor (e). The aspect ratio is the square of the span divided by the wing area.

Is parasite drag zero lift drag?

Parasitic drag is a combination of form drag and skin friction drag. It affects all objects regardless of whether they are capable of generating lift. Total drag on an aircraft is made up of parasitic drag and lift-induced drag.

What is airplane lift?

lift, upward-acting force on an aircraft wing or airfoil. The lift force arises because there is a zone of low air pressure on the top of the airfoil and a zone of high pressure on the bottom of the airfoil caused by the flow of air over the airfoil.

How do you find the drag coefficient at zero lift?

The total drag coefficient Cd is equal to the drag coefficient at zero lift Cdo plus the induced drag coefficient Cdi . The drag coefficient in this equation uses the wing area for the reference area. Otherwise, we could not add it to the square of the lift coefficient, which is also based on the wing area.

Does the reference area affect the drag coefficient?

As pointed out on the drag equation slide, the choice of reference area (wing area, frontal area, surface area.) will affect the actual numerical value of the drag coefficient that is calculated. When reporting drag coefficient values, it is important to specify the reference area that is used to determine the coefficient.

What is the drag coefficient of a plane?

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.

How do you calculate drag coefficient in a wind tunnel?

Cd = D / (q * A) The drag coefficient then expresses the ratio of the drag force to the force produced by the dynamic pressure times the area. This equation gives us a way to determine a value for the drag coefficient. In a controlled environment (wind tunnel) we can set the velocity, density, and area and measure the drag produced.