Calculating Boundary Layer Thickness

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SUMMARY

The discussion focuses on calculating the boundary layer thickness for a NACA 2412 airfoil, specifically under conditions simulating a Cessna 172. The user seeks an equation to determine the boundary layer thickness, defined as the distance from the surface to 99% of free-stream velocity, given a chord length of 1.3 m, a velocity of 65 m/s, and a kinematic viscosity of 1.8e-5 at 3000 m MSL. The relevant equation for calculating boundary layer thickness in this context is the Blasius solution for laminar flow, which can be expressed as δ = 5 * (ν * x / U)^(1/2), where δ is the boundary layer thickness, ν is the kinematic viscosity, x is the distance from the leading edge, and U is the free-stream velocity.

PREREQUISITES
  • Understanding of boundary layer theory
  • Familiarity with NACA airfoil specifications
  • Knowledge of fluid dynamics principles
  • Basic proficiency in applying equations related to laminar flow
NEXT STEPS
  • Research the Blasius boundary layer equation for laminar flow
  • Explore computational fluid dynamics (CFD) tools for boundary layer analysis
  • Study the effects of varying kinematic viscosity on boundary layer thickness
  • Investigate experimental methods for measuring boundary layer thickness in wind tunnel tests
USEFUL FOR

Aerospace engineers, fluid dynamics researchers, and students conducting experiments on airfoil performance and boundary layer characteristics.

waealu
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I am trying to calculate the thickness of the boundary layer for a NACA 2412 airfoil. I am working on constructing some wind tunnel tests that simulate a Cessna 172 (NACA 2412 airfoil). I am trying to determine the thickness of the boundary layer (distance from surface to 99% of free-stream velocity). What would the boundary layer thickness be (or what is the equation) for a NACA 2412 airfoil (chord length is about 1.3 m) with a velocity of 65 m/s at 3000m MSL (kinematic viscosity is about 1.8e-5).

Preferably, I am looking for an equation that would be able to calculate this.

Thank you.
 
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How did you jump from wind tunnel tests on a particular airfoil to that of a Cessna 172?
 
The Cessna 172 information is irrelevant. I am using the NACA 2412 airfoil model for my experiments. I just need to determine boundary layer thickness for that.
 

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