Concepedia

Development and validation of a combined rotor fuselage induced flow field computational method

NASA STI Repository (National Aeronautics and Space Administration) · 1980 · 14 citations · 9 references

Open access

Abstract

A potential-flow panel method has been modified to calculate the effects of a rotor wake on the time-averaged surface pressure and velocity distributions on a helicopter fuselage. The rotor-induced velocities are calculated by using a vortex-tube wake model. The calculated pressure distributions are found to compare well with experimental data obtained from tests of a wind-tunnel model. (Author)

References

9

Evaluation of the Induced-Velocity Field of an Idealized Helicopter Rotor

Robert P. Coleman, Arnold M Feingold, Carl W. Stempin · University of North Texas Digital Library (University of North Texas) · 1945 · 79 citations · Full text

Engineering, Aerospace Engineering, Aerodynamics +15

The problem of three-dimensional lifting potential flow and its solution by means of surface singularity distribution

John L. Hess · Computer Methods in Applied Mechanics and Engineering · 1974 · 65 citations

Natural Sciences, Physics, Computational Fluid Dynamics +10

Induced Velocities Near a Lifting Rotor With Nonuniform Disk Loading

H. H. Heyson, S. Katzoff · University of North Texas Digital Library (University of North Texas) · 1956 · 60 citations · Full text

Engineering, Aerospace Engineering, Aerodynamics +16

Fuselage surface pressure measurements of a helicopter wind-tunnel model with a 3.15-meter diameter single rotor

C. E. Freeman, Raymond E. Mineck · NASA Technical Reports Server (NASA) · 1979 · 57 citations

Engineering, Aerospace Engineering, Mechanical Engineering +15

The Free Wake Analysis A Method For The Prediction Of Helicopter Rotor Hovering Performance.

David R. Clark, Albert C. Leiper · 1969 · 44 citations

Engineering, Aerospace Engineering, Flight Dynamics +11