Use this engineering calculation for a transparent preliminary estimate or independent arithmetic check when geometry, materials, loads, operating conditions, and units are defined consistently.

Density Kg Per M3 (kg/m³)

Required number input.

Speed Meters Per Second (m/s)

Required number input.

Lift Coefficient

Required number input.

Reference Area Square Meters (m²)

Required number input.

Steady lift ½ρv²ClA using supplied signed lift coefficient and reference area. The tool evaluates the supplied inputs together and returns the named outputs below; it does not infer omitted operating conditions or change the units shown.^[1]

Lift Newtons (N)

The resulting lift newtons returned as a number.

• Lift, drag, Mach, and wing relations depend on air properties, Reynolds and Mach numbers, geometry, angle of attack, configuration, compressibility, ground effect, and validated aerodynamic coefficients. Simple coefficients should not be extrapolated beyond their source data.
• Use finite inputs in the displayed units and preserve more precision than the final presentation requires. Independently verify safety-critical, financial, compliance, or production decisions.

Check assumptions against drawings, measurements, current material data, and the applicable design code. Apply required load combinations and safety factors, then obtain qualified review and testing for consequential designs.

• Drag Force

  Steady aerodynamic or hydrodynamic drag ½ρv²CdA using supplied reference area and drag coefficient.

• Heat Exchanger LMTD Method

  Steady heat-exchanger duty Q=U A ΔTlm for a supplied overall coefficient, reference area and already-corrected LMTD.

• Wing Lift Coefficient

  Aerodynamic lift coefficient from measured lift divided by dynamic pressure times wing reference area.