Predicting lift on an Aerofoil with varying Angles of Attack

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Discussion Overview

The discussion revolves around predicting lift on an aerofoil in relation to varying angles of attack. Participants explore the complexities of calculating lift coefficients and seek methods to incorporate angle of attack into their predictions, particularly in the context of a school-based experiment involving a wind tunnel and cambered aerofoils.

Discussion Character

  • Exploratory
  • Technical explanation
  • Homework-related

Main Points Raised

  • One participant states the lift formula L = (1/2) d v² s CL and expresses confusion over variations of the lift coefficient that account for angle of attack.
  • Another participant shares a link to thin airfoil theory, suggesting it may provide relevant information.
  • A different participant mentions the complexity of obtaining an accurate model for lift prediction and provides a link to a program that generates airfoil performance data.
  • Another tool for airfoil analysis is suggested through a link to a Java-based application.
  • A participant questions how to account for stall in their calculations, indicating uncertainty about its relevance to their predictions.

Areas of Agreement / Disagreement

Participants express varying levels of understanding and approaches to the problem, with no consensus on a specific formula or method to incorporate angle of attack into lift predictions. The discussion remains unresolved regarding the best way to account for stall.

Contextual Notes

Participants acknowledge the complexity of modeling lift and the potential variations in lift coefficients based on different assumptions. There is also uncertainty about the relevance of stall in the context of their predictions.

Who May Find This Useful

This discussion may be useful for students and researchers interested in aerodynamics, particularly those exploring lift predictions in experimental settings or those facing similar challenges in modeling airfoil performance.

Tom 77
I am conducting a school based EEI and have found issues in predicting lift on an aerofoil with respect to angle of attack.I understand the formula for lift is L = (1/2) d v2 s CL. I also understand there are many confusing variations to the calculation for the lift coefficient but i am yet to find one that takes the angle of attack into account.

The idea of the experiment is to find the optimum angle of attack to velocity ratio in a wind tunnel acting on a cambered aerofoil and i would like to predict the lift per angle prior to testing, then to reveal the differences and use results for error. Is there a formula i can use to calculate the predicted lift of an Aerofoil which incorporates the angle of attack. I really appreciate any advice or support. Thanks
 
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Tom 77 said:
I am conducting a school based EEI and have found issues in predicting lift on an aerofoil with respect to angle of attack.I understand the formula for lift is L = (1/2) d v2 s CL. I also understand there are many confusing variations to the calculation for the lift coefficient but i am yet to find one that takes the angle of attack into account.
https://en.wikipedia.org/wiki/Airfoil#Thin_airfoil_theory
 
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