3 edition of Modern airfoil ice accretions found in the catalog.
Modern airfoil ice accretions
by National Aeronautics and Space Administration, National Technical Information Service, distributor in Washington, DC, [Springfield, Va
Written in English
|Statement||Harold E. Addy, Jr., Mark G. Potapczuk, and David W. Sheldon.|
|Series||NASA technical memorandum -- 107423|
|Contributions||Potapczuk, Mark G., Sheldon, David W., United States. National Aeronautics and Space Administration.|
|The Physical Object|
NAVIER-STOKES ANALYSIS OF AIRFOILS WITH LEADING EDGE ICE ACCRETIONS Mark G. Potapczuk University of Akron Akron, Ohio ABSTRACT A numerical analysis of tile flowfield characteristics and the performance degra,h_t ion of an airfoil with leading edge ice accretions was performed. The important fluid dynamic processes were identified and. dimensional tailplane model.8 The NASA Modern Airfoils Program9 currently provides the best airfoil performance data set at flight Reynolds and Mach numbers, but due to size limitations in the NASA Low-Turbulence Pressure Tunnel (LTPT) used for the aerodynamic testing, the ice accretions were obtained on a 3-foot (m) chord airfoil.
Ice accretions and aerodynamic effects on a multi-element airfoil under SLD conditions Understanding the degradation of the aerodynamic performance of lifting surfaces under icing environments, and designing proper IPS, are challenging tasks . The airfoil was a natural laminar airfoil (NLF) and the ice is considered as the glaze accretion. The experimental measurements were carried out using hot-wire anemometry at Reynolds number of × 10 6 and angle of attack ranging from 0° to 6°.
For the large droplet case, the ice accretion shown in Fig. 2 occurs between the x/c= and protuberances tested by Jacobs. The maximum height of 3/4 inch seen in the large-droplet tanker test ice accretions has a k/c = based on an airfoil chord at the aileron midspan location of ft. The purpose of this paper is to analyse an actual representation of ice accretions, which are important during the certification process.,Ice accretion experiments are conducted in a low-speed subsonic wind tunnel testing facility to evaluate the influence of various ice shapes around the airfoil sections. Ice accumulation changes the shapes of local airfoil sections and thereby affects the.
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Ice Accretions on Modern Airfoils Investigated The modern airfoil project is complete, and final reports will be published in January In addition, Glenn’s Icing Branch is planning follow-on tests to investigate the aerodynamic performance of other iced airfoils.
These tests are to include detailed flow. Modern airfoil ice accretions (OCoLC) Material Type: Government publication, National government publication, Internet resource: Document Type: Book, Internet Resource: All Authors / Contributors: Harold E Addy; Mark G Potapczuk; David W Sheldon; United States.
National Aeronautics and Space Administration. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Cited by: Experiments were applied on the clean airfoil, runback ice, horn ice, and spanwise ridge ice at a Reynolds number of × over angles of attack from -8° to 20°, and then results are compared.
American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Cited by: Research pre is also briefly reviewed. Following this review, our current knowledge of iced airfoil aerodynamics is presented from a flowfield-physics perspective.
This article identifies four classes of ice accretions: roughness, horn ice, streamwise ice, and spanwise-ridge ice.
The ice accretion and aerodynamic testing in the Modern Airfoils Program is described in more detail for the NLF airfoil by Addy and Chung and for the GLC airfoil by Addy et al.
In both of these studies, the aerodynamic effects of the ice accretion castings were compared to a smoothed, “2D” version of the ice shape.
The rime ice accretions on a NACA aerofoil at 0° and 4° angles-of-attack have been investigated and there is agreement between the simulated results and previously published experimental data.
The change of the pressure coefficient along the iced aerofoil is also analysed. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Ice Accretion Prediction for Single Airfoil and Multi-Element Airfoil 1 November | Applied Mechanics and Materials, Vol.
Numerical simulation of ice accretion prediction on multiple element airfoil. With growing ice accretion, the drag of the aerofoil increases due to the profile shape alteration, even if the profile shape tends to be replicated, and due to the attack angle variation, diminishing the power output of the turbine.
At the iced cross-section of the blade, the augmented chord length at the LE can lead to: (a) an increase of the bending moment at the blade root. Past research on airfoil aerodynamics in icing are reviewed. This review emphasizes the time period after the NASA Lewis workshop that initiated the modern icing research program at NASA and the current period after the ATR accident where aerodynamics research has been more aircraft safety focused.
Research pre is also briefly reviewed.  Harold E A, Mark G P, David W S. Modern airfoil ice accretions. AIAA paperGoogle Scholar  Frank T L, Abdollah K. Effects of ice accretions on aircraft aerodynamics. Prog Aerosp Sci,castings of ice accretions formed on a swept GLC airfoil1. The experiment is the first part (icing test) of a two-part experiment to study the aerodynamic effects of 3D ice accretions.
A 28o swept GLC airfoil was designed and fabricated. Its geometry is representative of a modern business aircraft wing.
The airfoil. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA The flow field over a NREL S airfoil subjected to different ice accretions has been investigated by particle image velocimetry for angles of attack ranging from \(-4^\circ \) to \(16^\circ.
Icing tests were conducted to document ice shapes formed on three different two-dimensional airfoils and to study the effects of the accreted ice on aerodynamic performance.
The models tested were representative of airfoil designs in current use for commercial transport, business jet, and general aviation aircraft.
The models were subjected to a range of icing conditions in an icing wind tunnel. Ice accretions and icing effects for modern airfoils. [Harold E Addy; NASA Glenn Research Center.] Home.
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Research pre is also briefly reviewed. Following this review, our current knowledge of iced airfoil aerodynamics is presented from a flowfield-physics perspective.
This section identifies four classes of ice accretions: roughness, rime ice, horn ice, and spanwise ridge ice. Ensuring the safety of airplane flight in icing conditions is an important and active arena of research in the aerospace community.
Notwithstanding the research, development, and legislation aimed at certifying airplanes for safe operation, an analysis of the effects of icing uncertainties on certification quantities of interest is generally lacking.
methods13;17through extensive ice accretion tests. Thus, a series of tests were planned as part of the ongoing research effort in support of NASA’ s Modern Airfoil Ice Accretion programFor this pur-pose, an airfoil similar to that found on a modern business jet main wing section,shown inFig.1a,rid.– The purpose of this paper is to describe a methodology for predicting the effects of glaze ice geometry on airfoil aerodynamic coefficients by using neural network (NN) prediction.
Effects of icing on angle of attack stall are also discussed., – The typical glaze ice geometry covers ice horn leading‐edge radius, ice height, and ice horn position on airfoil surface.
Helicopter icing - Volume Issue - Y. Cao, K. Chen.