Pressure distributions from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel by William G. Johnson

Cover of: Pressure distributions from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel | William G. Johnson

Published by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va .

Written in English

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  • Aerodynamics, Transonic.,
  • Aerofoils.

Edition Notes

Book details

StatementWilliam G. Johnson, Jr., Acquilla S. Hill, and Otto Eichmann.
SeriesNASA technical memorandum -- 86370.
ContributionsHill, Acquilla S., Eichmann, Otto., United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL17659070M

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Get this from a library. Pressure distributions from high Reynolds number tests of a NASA SC(3)(B) airfoil in the Langley Meter Transonic Cryogenic Tunnel.

[William G Johnson; Acquilla S Hill; Otto Eichmann; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.]. Report presenting an experimental investigation of the pressure distribution about a circular cylinder at yaw angles of 0, 15, 30, 45, and 60 degrees and a variety of Reynolds numbers.

Testing indicated that for the range of Reynolds number near and above the critical value, the flow and force characteristics of a yawed circular cylinder cannot be determined Cited by: NASA/TP Reynolds Number Effects at High Angles of Attack David F.

Fisher, Brent R. Cobleigh, and Daniel W. Banks Dryden Flight Research Center Edwards, California Robert M. Hall and Richard W. Wahls NASA Langley Research Center Hampton, Virginia June   the pressure distribution varies with Reynolds Number.

Indications of changes in the character of the flow with Reynolds Number may also be deduced from the meas-ured pressure distributions. An extensive investigation of the pressure distribu-tion over one section of the N. airfoil has been carried out in the variable-density wind Cited by: Pressure distributions from high Reynolds number tests of a NASA SC(3)(B) airfoil in the Langley Meter Transonic Cryogenic Tunnel / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and.

NASA High-Reynolds Number Circulation Control Research - Overview of CFD and Pressure distributions from high Reynolds number tests of a NASA SC book Experiments (Invited) W. Milholen II, G.S. Jones †, and C.M. Cagle* NASA Langley Research Center, Hampton, VA, A new capability to test active flow control concepts and propulsion simulations at high Reynolds.

The parameters are viscosity η, density ρ and radius r. The suggested number of is used for the application to blood flow for the example of the r approach is to define a variable Reynolds number in terms of the maximum velocity for laminar flow in a tube by. and characterize the condition for turbulence as the condition when the Reynolds number reaches a critical.

obtained pressure data for the sharp leading edge are pre-sented without analysis in tabulated and graphical for-mats across a Reynolds number range of 6× to 36 x at a Mach number of and across a Mach number range of to at a Reynolds number of 6 x 10 b.

Normal-force and pitching-moment coefficientFile Size: 6MB. ABSTRACT: Force and surface pressure measurements on a 2D rough circular cylinder were carried out over a wide range of Reynolds numbers in the high-pressure wind tunnel in Göttingen.

The Reynolds number spanned values from subcritical up to high transcritical 15× ≤ Re ≤ 12× The cylinder had a mean relative surface roughness of kFile Size: 5MB.

Effects of leading-edge sweep on flutter characteristics of some delta-planform surfaces at a Mach number of / (Washington, D.C.: National Aeronautics and Space Administration: [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia ], ), by Robert C.

Goetz, Langley Research Center. The lift coefficient showed a wide variation with Reynolds number for the 6-percent flap mounted on the bottom surface at the percent-diameter station, varying from a low of about at a Reynolds number ofto a high of at a Reynolds number ofand then decreasing almost linearly to a value of at a Reynolds number of.

Flow past a circular cylinder at high Reynolds number diameter was Sft. The wind speeds were about m.p.h., which corre- sponds to Reynolds numbers of x lo6. Their mean value of C, for a group of observations is &and it. The work was performed in two unique facilities: the Superpipe and the High Reynolds number Test Facility (HRTF) that can obtain very high Reynolds numbers on Author: Alexander J Smits.

- J Fluid ME( voE 57 part 2 p p Printed in Great. Reynolds number, leaving the pressure gradient as the likel y cause of the discrepancy. Unfortunately, LES was supposed, precisely, to accurately render the effects of pressure gradients and. Mach number at a fixed Reynolds number is caused by the reduction in lift as Mach number is increased.

These aeroelastic distortions can be minimized when testing in the NTF by conducting, where possible, Reynolds number variations at a fixed dynamic pressure. Typically, wing washout caused by the modelFile Size: 7MB. Since the value of the suction peak on the leading edge depends on the nose radius, the deep stall angle varies with airfoil shape.

An example is given in Fig. Figure shows the associated pressure distributions for airfoil DU W just before and in deep stall. Timmer 24 derived a relation between the leading edge shape and the deep stall angle by correlating the. Heat-Transfer and Pressure Distributions on 60 degree and 70 degree Swept Delta Wings Having Turbulent Boundary Layers.

NASA Technical Note TN D [Murray, Jr., William M. & Stallings, Jr., Robert L. - NASA.] on *FREE* shipping on qualifying offers. Heat-Transfer and Pressure Distributions on 60 degree and 70 degree Swept Delta Wings Having Turbulent Author: Robert L. - NASA. Murray, Jr., William M. & Stallings, Jr.

The computational test rig is designed in order to allow the comparison between the results of the simulations and the measurements carried out in.A sketch of the test pipe is represented in Fig. test pipe is characterized by a diameter of m and a length of m, and was installed on the rig downstream of a flow conditioner and of a m long pipe with a 6-in ( m) Cited by: 12/30/12 GODDARD SPACE FLIGHT CENTER 5 Pre-SC12 Successes * Faster Raid Controllers * Faster Processors * 3-port 40GE NICs (2nd.

All the simulations were carried out with a high value of the Reynolds number; no attempt to use a turbulence modeling was made. A general introduction to the method is presented and used for the simulation of the flow around a fixed cylinder, obtaining results which demonstrated good agreement with known values from the literature.

Full text of "NASA Technical Reports Server (NTRS) Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley inch Hypersonic Tunnel at a Mach Number of " See other formats NACA TN NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS TECHNICAL NOTE INVESTIGATION.

INSTITUTE OF PHYSICS PUBLISHING MEASUREMENT SCIENCE AND TECHNOLOGY l. 13 () – PII: S(02) Static pressure correction in high Reynolds number fully developed turbulent pipe flow BJMcKeon and A J Smits Department of Mechanical and Aerospace Engineering, Princeton University, Princeton.

Reynolds-number effects in the adverse-pressure-gradient (APG) turbulent boundary layer (TBL) developing on the suction side of a NACA wing section are assessed in the present work. To this end, we conducted a well-resolved large-eddy sim-ulation of the turbulent flow around the NACA airfoil at a.

BOUNDARY-LAYER PRESSURE FLUCTUATIONS AT HIGH REYNOLDS NUMBERS ON A FREE-FLIGHT TEST VEHICLE by D. Roberts SUMMARY Measurements have been made of the boundary-layer pressure fluctuations on the body of a free-flight aerodynamic test vehicle powered by a solld-fuel rocket motor.

The high-resolution pressure spectra at different angle of attack clearly reveal the impact of leading edge vortex on the upper surface pressure distributions. The pressure measured by PSP also agrees well with the pressure tap results.

The center of pressure is therefore not a convenient location about which to specify the resultant forces acting on the airfoil as it is not fixed.

A common convention is to use a point specified at the airfoil quarter chord. This is a point located one quarter of the way along the chord from the leading edge. Moving the resultant lift and drag. Reynolds Number vs. Pressure Loss Due to Contraction for Contraction Ratio of 1/3 Reynolds Number Pressure Loss Due to Contraction Kays and London Femlab Fig.

9 Pressure Loss Due to the Abrupt Contraction Ratio of 1/3 vs Reynolds Number Both of the axes on the graph are log rhythmic. Back to Additional Photos Ordered by Tunnel Test Log.

The Republic PB Thunderbolt was one of the great fighters used by the U. Army Air Force in World War II, and crews praised its ability to absorb punishment.

EPPLER EA 6 (-1) AIRFOIL. NACA M3 AIRFOIL. WORTMANN FX GOE AIRFOIL. GOE AIRFOIL. #N#Polars for NACA AIRFOILS (nil) Xfoil prediction. at α=° Xfoil prediction.

Xfoil prediction. at α=° Xfoil prediction. Xfoil prediction. at α=° Xfoil prediction. where M is the Mach number, is the phase speed c p of shear layer disturbances, nondimensionalized by the freestream velocity U, γ is a phase lag, and n = 1,2, is the mode number.

This formula is usually attributed to Rossiter (), although a similar mechanism was known earlier for edge tones (Powell).This flow-acoustic resonance occurs in other Cited by: The first step to getting started in research is to find a faculty mentor.

The role of a mentor is to: assist in the development and articulation of a project idea and plan. help understand the methods and concepts of research and scholarship within your field. guide and train you in the skills and/or techniques needed to complete a project.

Center for Turbulence Research Annual Research Briefs 45 Prediction of high Reynolds number flow over a circular cylinder using LES with wall modeling. (NASA/HST); 18) Thackeray's Globules (NASA/HST); 19) Helix Nebula (NASA/Spitzer) This collection of activities is based on a weekly series of space science problems distributed to thousands of teachers during the school years.

The following books have been found by educators to be useful in teaching NDT. To recommend a book not on the list, send a message to the Webmaster using the link provided at. Modeling of a Sequential Two-Stage Combustor Paperback – J by R.

Hendricks (Author), Nasa Technical Reports Server (Ntrs) (Creator), Et Al (Creator) & 0 moreCited by: 3. Pressure Suit, RXA, Constant Volume, Litton Description This RXA Advanced Extra-Vehicular Suit is an experimental constant volume suit was manufactured by Litton Industries who made a series of "hard" suits during the early s.

Consider the F shown in Figureand also gracing the cover of this book. The chord length where the wing joins the center body is ft.

Consider the airplane making a high-speed pass at a velocity of ft/s at sea level (Mach ). Calculate the %(25). The near wake of a circular cylinder at high Reynolds number is investigated by means of 2D-PIV and stereoscopic PIV.

Phase-averaged measurements of the instantaneous fields have been performed. The linear stochastic estimation (LSE) has been adapted to estimate the phase-averaged quantities.

This avoids the long time acquisition and the large storage Cited by: An Investigation into Surface Temperature Distributions of High-B Pulsars Nobutoshi Yasutake DepartmentofPhysics,ChibaInstituteofTechnology, Shibazono, Narashino, Chiba, Japan [email protected] Kei Kotake DepartmentofAppliedPhysics,FacultyofScience,FukuokaUniversity, Nanakuma,Jonan.

Measurements on a large circular cylinder in a pressurized wind tunnel at Reynolds numbers from 10^6 to 10^7 reveal a high Reynolds number transition in which the drag coefficient increases from its low supercritical value to a value at R = × 10^6 and then becomes constant.

Also, for R > × 10^6, definite vortex shedding occurs, with Strouhal number Cited by: Inspired from earlier studies at high Reynolds-number on the high aspect-ratio aircraft wings, the wing chord has been used as the reference length-scale, even for the insect-scaled wings.

However, the flow structure on a typical low aspect-ratio insect wing is highly three-dimensional.APOLLO 14 PRELIMINARY SCIENCE REPORT PAGE 9 COLD-CATHODE-GAGE EXPERIMENT (LUNAR ATMOSPHERE DETECTOR) F.


E. Faller, C. 0. .

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