Finite‐State Induced‐Flow Model for Rotors in Hover and Forward Flight
- 1 October 1989
- journal article
- Published by AHS International dba Vertical Flight Society in Journal of the American Helicopter Society
- Vol. 34 (4), 5-17
- https://doi.org/10.4050/jahs.34.5
Abstract
No abstract availableThis publication has 10 references indexed in Scilit:
- Technical Note: Dynamic Inflow for Practical ApplicationsJournal of the American Helicopter Society, 1988
- A new approach to finite state modelling of unsteady aerodynamicsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1986
- Unsteady aerodynamics in time and frequency domains for finite time arbitrary motion of rotary wings in hover and forward flightPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1984
- The Use of Actuator‐Disc Dynamic Inflow for Helicopter Flap‐Lag StabilityJournal of the American Helicopter Society, 1983
- A Prescribed Wake Lifting Surface Hover Performance AnalysisJournal of the American Helicopter Society, 1977
- The Wake Geometry of a Hovering Helicopter Rotor and Its Influence on Rotor PerformanceJournal of the American Helicopter Society, 1972
- An Actuator-Disc Analysis of Helicopter Wake Geometry and the Corresponding Blade ResponsePublished by Defense Technical Information Center (DTIC) ,1970
- AN ACTUATOR DISC THEORY FOR THE SHED WAKE AT LOW TIP SPEED RATIOSPublished by Defense Technical Information Center (DTIC) ,1965
- Rotor blade harmonic air loadingAIAA Journal, 1964
- A Two-Dimensional Approximation to the Unsteady Aerodynamics of Rotary WingsJournal of the Aeronautical Sciences, 1957