Improving Performance of HP.115 Simulator Model: Challenges and Solutions

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SUMMARY

The discussion focuses on improving the performance of the Handley Page HP.115 simulator model using the Merlin MP521 and Excalibur II model editor. The user reports achieving a maximum speed of only 180 knots and a vertical speed of 800 ft/min, indicating significant performance issues. Despite converting 3D data to 2D airfoil data and correcting induced drag, the drag coefficient (Cd) remains too high. The user seeks solutions to accurately approach the correct Cd values and enhance overall flight performance.

PREREQUISITES
  • Understanding of aerodynamic principles, specifically lift and drag coefficients (Cl, Cd, Cm).
  • Familiarity with Computational Fluid Dynamics (CFD) analysis techniques.
  • Experience with 3D to 2D airfoil data conversion processes.
  • Knowledge of flight simulation software, particularly Excalibur II.
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  • Research methods to accurately calculate drag coefficients for delta wing designs.
  • Explore advanced CFD tools for more precise aerodynamic analysis.
  • Investigate optimization techniques for flight simulation models in Excalibur II.
  • Learn about the effects of angle of attack on lift and drag in slender delta wings.
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Aerospace engineers, flight simulation developers, and students involved in aerodynamic modeling and performance optimization of aircraft simulations.

Babb
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Hi everyone,

In my project work, I have to "rebuild" the Handley Page HP.115 aircraft, using the simulator in my university. It is a Merlin MP521 and I am using the Excalibur II model editor. The aircraft was used to test the slender delta wing planform at low speeds as part of the Concorde development program. So my model flies, but the overall performance is very bad. I can barely reach the maximum speed of about 180 knots, the vertical speed is maximum 800ft/min without loosing speed and it is not possible to recap the flight profile of the original: High angles of attack at low speeds. I got my Cl, Cd, Cm over alpha data from a student who made a CFD analysis of the wing. I already converted the 3D data to 2D airfoil data and corrected the induced drag but the performance is still bad.

Are there a possiblity to approach the correct Cd values? I guess the drag is still far to high.
Or any other assumptions which could fix these problems.

Thanks and Cheers
Babb
 
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