3 edition of Wind-tunnel investigations of blunt-body drug reduction using forebody surface roughness found in the catalog.
Wind-tunnel investigations of blunt-body drug reduction using forebody surface roughness
by National Aeronautics and Space Administration, Dryden Flight Research Center, National Technical Information Service, distributor in Edwards, Calif, Springfield, VA
Written in English
|Other titles||Wind tunnel investigations of blunt body drug reduction using forebody surface roughness|
|Statement||Stephen A. Whitmore, Stephanie Sprague and Johnathan W. Naughton.|
|Series||[NASA technical memorandum] -- NASA/TM-2001-210390, NASA technical memorandum -- 210390.|
|Contributions||Sprague, Stephanie., Naughton, Jonathan W. 1964-, Hugh L. Dryden Flight Research Center.|
|The Physical Object|
The wide-accepted criteria for evaluation of the wind tunnel measurement quality are based on methodology of a few supposedly identical tests of the standard model. Wind tunnel data uncertainty is being considered in the form of test data repeatability. DAS Wind tunnel measurement quality in testing of a standard model Dijana Cited by: 1. For low speed flows, tufts or surface oil indicate the flow direction along the surface of a model. You can investigate some wind tunnel testing techniques by using our interactive tunnel testing applet. More experienced users can use the TunnelSys application programs to perform model design, testing, and performance post-processing.
A series of wind tunnel investigations were conducted at NASA Ames Research Center to de-termine the flow characteristics downstream of a set of wind tunnel inlet flow conditioning vanes. The purpose of these tests was to develop an un-derstanding of the flow mechanisms that con-tributed to the pressure loss and turbulence gen-erated by the File Size: 1MB. WIND TUNNEL TESTING: 2 - Alan G. Davenport Wind Engineering Group A GENERAL OUTLINE 2 THE MODELLING OF THE SITE AND THE WIND General The basic tool used is the Laboratory's Boundary Layer Wind Tunnel. This wind tunnel is designed with a very long test section, which allows extended models of upwind terrain to be placed in front of theFile Size: 1MB.
This paper presents wind tunnel investigations of the aerodynamic interference effects on the pressure distribution on a building adjacent to another one. Tests were carried out at the Aviation Institute in Warsaw. Models, made to scale, were set up behind a turbulent flow development by: Wind Tunnel Investigations of An Inclined Stay Cable With A Helical Fillet CHAPTER 2: EXPERIMENTAL CONDITIONS PROTOTYPE STAY CABLES. Over the last 20 years, structural engineers and architects have proposed the use of cable-stayed bridges for .
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For these tests, the forebody roughness of a blunt-based model was modiﬁed using micromachined surface overlays. As forebody roughness increases, boundary layer at the model aft thickens and reduces the shearing effect of external ﬂow on the separated ﬂow behind the base region, resulting in reduced base drag.
The wind-tunnel tests results conclusively demtmstrate the existence of a forebody drag-base drag t_plimal point. The data demonstrate that the base drag coefficient corresponding to the drag minimum lies betv, een andreferenced to the base area.
Most importantly, the data show a drag _Aerospace Size: 1MB. The wind-tunnel tests results conclusively demonstrate the existence of a forebody drag–. base drag optimal point. The data demonstrate that the base drag coefﬁcient corresponding to the drag.
wind-tunnel investigation blunt-body drag reduction using program office nasa sti program office technical information important role graphic presentation manuscript length space science nasa counterpart reference value institutional mechanism langley research center quick release report technical data technical finding lead center space science sti development activity theoretical analysis nasa sti database minimal annotation nasa program.
Wind-tunnel investigations of blunt-body drag reduction using forebody surface roughness (OCoLC) Online version: Whitmore, Stephen A. Wind-tunnel investigations of blunt-body drag reduction using forebody surface roughness (OCoLC) Material Type: Government publication, National government publication: Document Type: Book.
For these tests, the forebody roughness of a blunt-based model was modified using micomachined surface overlays. As forebody roughness increases, boundary layer at the model aft thickens and reduces the shearing effect of external flow on the separated flow behind the base region, resulting in reduced base drag.
Investigation of Drag Reduction on a Circular Cylinder using Microfiber Coating by Changing its Permeability. Drag Reduction on Blunt-Based Vehicles Using Forebody Surface Roughness.
Wind-tunnel investigations of blunt-body drag reduction using forebody surface by: Response surface modeling using multivariate orthogonal functions.
Eugene Morelli and; Wind-tunnel investigations of blunt-body drag reduction using forebody surface roughness. Stephen Whitmore, Stephanie Sprague and; Wind tunnel investigation of grid fin. Stability of easily hydrolyzable beta-cypermethrin based O/W type drug-loading microemulsion.
5 September | Journal of Dispersion Science and Technology, Vol. 40, No. 8 Wind-tunnel investigations of blunt-body drag reduction using forebody surface by: A wind tunnel study was performed on the FFA-W airfoil, which form a segment of a MW wind turbine blade, to examine the effect of fixed roughness height and position using a zigzag tape.
The hydrodynamic behaviour of riming frozen drops and riming simulated ice crystal plates was studied by means of a vertical wind tunnel. At all times the ice particles were freely suspended in the vertical airstream of the wind tunnel where temperature and liquid water content could be accurately by: Wind-tunnel investigations of blunt-body drag reduction using forebody surface roughness (OCoLC) Microfiche version: Whitmore, Stephen A.
Wind-tunnel investigations of blunt-body drug reduction using forebody surface roughness (OCoLC) Material Type: Document, Government publication, National government publication, Internet.
SEP6 'b~J S 21 AGARD-R AGARD REPORT No. c".• on Problems in Wind Tunnel Testing Techniques,DISTRIBUTION AND AVAILABILITY ON BACK COVER Property of File Size: 7MB.
A wind tunnel investigation of the internal circulation and shape of water drops falling at terminal velocity in air The internal circulation and the shape of water drops falling at terminal velocity in air of 20°C at sea level pressure, and nearly water saturated, were studied by means of a wind tunnel.
The surface Cited by: Summary. The generation of aeolian tones by a rough cylinder was investigated in a large wind tunnel at Reynolds numbers between 10 4 and 4 × 10 low Reynolds numbers, the measured sound pressure level agrees well with predictions for smooth cylinders, but it increases less rapidly with flow velocity at higher Reynolds : F.-R.
Grosche. For these tests, the forebody roughness of a blunt-based model was modified using micomachined surface overlays. As forebody roughness increases, boundary layer at the model aft thickens and. The present work investigates the influence of high-temperature gas effects on the laminar–turbulent transition induced by a patch of distributed roughness on a hemispherical capsule-like geometry.
A WIND-TUNNEL INVESTIGATION OF THE EFFECT OF BODY SHAPE ON SONIC-BOOM PRESSURE DISTRIBUTIONS By Harry W. Carlson, Robert J. Mack, and Ode11 A. Morris Langley Research Center SUMMARY Measurements of sonic-boom pressure distributions at distances of up to 20 body lengths from eight slender bodies of revolution have been made at Mach numbers of The turbulence drag reduction can be more obvious if using the flow control method of micro riblets on the fuselage surface of large passenger aircraft.
Combined with sub-transonic and supersonic wind tunnel equipment, in this paper, a set of experimental verification methods for micro riblets drag reduction of fuselage is developed.
Abstract. The intention of wind-tunnel experiments (or in general physical modelling, including water-tank experiments) is to reproduce the characteristics of the atmospheric boundary layer on a small geometric scale, typically between 1/ th and 1/ th of the real world.
In the previous chapters, numerical models were grouped into different classes depending on the scales they are Cited by:. Report presenting wind tunnel testing to investigate the possibility of reducing the hinge moments of a control surface by beveling the trailing edge.
Tests were made with a 9-percent-thick airfoil with a percent-chord plain flap. Results regarding the variations of lift and hinge moment, effect of shapes, and pitching moments are : Robert T.
Jones, Milton B. Ames.An investigation of anomalies observed in wind-tunnel force tests of a blunt-body con- figuration ( and scale models of the proposed Pioneer Venus small probe con- figuration) was conducted at Mach numbers from to in the Langley 8-foot transonic.Correction of Wind Tunnel Test Data for Additional Roughness Drag* Hidetoshi IIJIMA,1)† Masayoshi NOGUCHI,2) and Shinji NAGAI1) 1)Japan Aerospace Exploration Agency, Chofu, Tokyo –, Japan 2)Japan Aerospace Exploration Agency, Mitaka, Tokyo –, Japan A method to correct wind tunnel test data for the additional drag caused by roughness elements in a fully turbulent.