Experimental Data Base for Computer Program Assessment

612 Pages·2016·16.77 MB·English

NORTH ATLANTIC TREATY ORGANIZATION
ADVISORY GROW FOR AEROSPACE RESEARCH AND DEVELOPMENT
(ORGANISATION DU TRAlTE DE L'ATLANTIQUE NORD)
AGARD Advisory Report No. 138
EXPERIMENTAL DATA BASE FOR COMPUTER
PROGRAM ASSESSMENT
REPORT OF THE FLUID DYNAMICS PANEL
WORKING GROUP 04
THE MISSION OF AGARD
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Published May 1979
Copyright O AGARD 1979
All Rights Reserved
ISBN 92-835-1323-1
Printed by Technical Editing and Reproduction Ltd
Harford House, 7-9 Charlotte St, London, WIP IHD
AGARD Advisory Report No.138 AGARD-AR-I 38 AGARD Advisory Report No.138 AGARD-AR-138
Advisory Group for Aerospace Research and Advisory Group for Aerospace Research and
Development, NATO Development, NATO
EXPERIMENTAL DATA BASE FOR COMPUTER EXPERIMENTAL DATA BASE FOR COMPUTER
PROGRAM ASSESSMENT Report of the Fluid Aerodynamic characteristics PROGRAM ASSESSMENT - Report of the Fluid Aerodynamiccharacteristics
-
Dynamics Panel Working Group 04 Computer programs Dynamics Panel Working Group 04 Computer programs
Published May 1979 Assessments Published May 1979 Assessments
642 pages Mathematical models 642 pages Mathematical models
Data processing Data processing
The economical advantages of applying transonic flow The economical advantages of applying transonic flow
Aerodynamic configurations Aerodynamic configurations
technology to aircraft design has created a large number technology to aircraft design has created a large number
of computational methods to predict and analyse of computational methods to predict and analyse
transonic flows. The proof of validity and the transonic flows. The proof of validity and the
refinement of such methods depend primarily on refinement of such methods depend primarily on
experimental results. Consequently errors inherent to experimental results. Consequently errors inherent to
data generated by any individual test facility may enter data generated by any individual test facility may enter
the computer codes thus restricting their applicability. the computer codes thus restricting their applicability.
P.T.O. P.T.O.
AGARD Advisory Report No.138 AGARD-AR-I 38 AGARD Advisory Report No.] 38 AGARD-AR-138
Advisory Group for Aerospace Research and Advisory Group for Aerospace Research and
Development, NATO Development, NATO
EXPERIMENTAL DATA BASE FOR COMPUTER EWERIMENTAL DATA BASE FOR COMPUTER
PROGRAM ASSESSMENT Report of the Fluid Aerodynamic characteristics PROGRAM ASSESSMENT - Report of the Fluid Aerodynamic characteristics
-
Dynamics Panel Working Group 04 Computer programs Dynamics Panel Working Group 04 Computer programs
Published May 1979 Assessments Published May 1979 Assessments
642 pages Mathematical models 642 pages Mathematical models
Data processing Data processing
The economical advantages of applying transonic flow The economical advantages of applying transonic flow
Aerodynamic configurations Aerodynamic configurations
technology to aircraft design has created a large number technology to aircraft design has created a large number
of computational methods to predict and analyse of computational methods to predict and analyse
transonic flows. The proof of validity and the transonic flows. The proof of validity and the
refinement of such methods depend primarily on refinement of such methods depend primarily on
experimental results. Consequently errors inherent to experimental results. Consequently errors inherent to
data generated by any individual test facility may enter data generated by any individual test facility may enter
the computer codes thus restricting their applicability. the computer codes thus restricting their applicability.
P.T.O. P.T.O.
To aid in the development and refinement of computational methods and to improve To aid in the development and refinement of computational methods and to improve
their applicability and compatibility an EXPERIMENTAL DATA BASE was their applicability and compatibility an EXPERIMENTAL DATA BASE was
established, presenting selected test results and detailed geometric descriptions of established, presenting selected test results and detailed geometric descriptions of
respresentative airfoil, wing, wing-body and bodyalone confwrations. In addition, respresentative airfoil, wing, wing-body and body-alone configurations. In addition,
the basic limitations of the available data as well as suggestions for future tests designed the basic limitations of the available data as well as suggestions for future tests designed
to reduce these limitations are discussed in detail. to reduce these limitations are discussed in detail.
ISBN 92-835-1323-1 ISBN 92-835-1323-1
To aid in the development and refinement of computational methods and to improve To aid in the development and refinement of computational methods and to improve
their applicability and compatibility an EXPERIMENTAL DATA BASE was their applicability and compatibility an EXPERIMENTAL DATA BASE was
established, presenting selected test results and detailed geometric descriptions of established, presenting selected test results and detailed geometric descriptions of
respresentative airfoil, wing, wing-body and body-alone configurations. In addition, respresentative airfoil, wing, wing-body and body-alone configurations. In addition,
the basic limitations of the available data as well as suggestions for future tests designed the basic limitations of the available data as well as suggestions for future tests designed
to reduce these limitations are discussed in detail. to reduce these limitations are discussed in detail.
ISBN 92-835-1323-1 ISBN 92-835-1323-1
<$
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AGARD-AR-138 ISBN 92-835-1323-1 UNCLASSIFIED
S.Originator Advisory Group for Aerospace Research and Development
North Atlantic Treaty Organization
7 rue Ancelle, 92200 Neuilly sur Seine, France
6.Title
EXPERIMENTAL DATA BASE FOR COMPUTER PROGRAM ASSESSMENT -
Report of the Fluid Dynamics Panel Working Group 04
7.Resented at
8. Author(s) 9.Date
Various May 1979
10.Author's Address 11.Pages
Various 624 pages
12.DistributionStatement This document is distributed in accordance with AGARD
policies and regulations, which are outlined on the
Outside Back Covers of all AGARD publications
13.Keywords/Descriptors
Aerodynamic characteristics Mathematical models
Computer programs Data processing
Assessments Aerodynamic configurations
14. Abstract
The economical advantages of applying transonic flow technology to aircraft design
has created a large number of computational methods to predict and analyse transonic
flows. The proof of validity and the refinement of such methods depend primarily
on experimental results. Consequently errors inherent to data generated by any
individual test facility may enter the computer codes thus restricting their applicability.
To aid in the development and refinement of computational methods and to improve
their applicability and compatibility an EXPERIMENTAL DATA BASE was established,
presenting selected test results and detailed geometric descriptions of representative
airfoil, wing, wing-body and body-alone configurations. In addition, the basic limitations
of the available data as well as suggestions for future tests designed to reduce these
limitations are discussed in detail.
The economical advantages of applying transonic flow technology to aircraft design has
created a large number of computational methods to predict and analyse transonic flows.
The proof of validity and the refinement of such methods depend primarily on experimental
results. Consequently errors inherent to data generated by any individual test facility may
enter the computer codes thus restricting their applicability.
To aid in the development and refinement of computational methods and to improve
their applicability and compatibility an EXPERIMENTAL DATA BASE was established,
presenting selected test results and detailed geometric descriptions of representative airfoil,
wing, wing-body and body-alone confgurations. In addition, the basic limitations of the
available data as well as suggestions for future tests designed to reduce these limitations
are discussed in detail.
Professor Dr. J.BARCHE
Chairman
Fluid Dynamics Panel Working
Group 04
CONTENTS
Page
PREFACE
by J.Barche iii
Reference
INTRODUCTION AND OVERVIEW OF CONFIGURATIONS
by J.Barche
LIMITATIONS OF AVAILABLE DATA
by T.W.Binion
RECOMMENDATIONS FOR FUTURE TESTING
by K.G.Winter and L.H.Ohman
CONCLUDING REMARKS
by J.Barche
APPENDIX A - 2-D CONFIGURATIONS
by J .Sloof
NACA 0012 AIRFOIL
by J.J.Thibert, M.Grandjacques and L.H.Ohman
NLR QE 0.1 1 - 0.75 - 1.375 AIRFOIL
by NLR and NAE
SUPERCRITICAL AIRFOIL CAST 7 SURFACE PRESSURE, WAKE AND BOUNDARY
LAYER MEASUREMENTS
by EStanewsky, W.Puffert, R.MuUer and T.E.B.Bateman
NLR 7301 AIRFOIL
by NLR Amsterdam
AIRFOIL SKF 1 .l. WITH MANEUVER FLAP
by E.Stanewsky and J .J .Thibert
AEROFOIL RAE 2822 - PRESSURE DISTRIBUTIONS, AND BOUNDARY LAYER
AND WAKE MEASUREMENTS
by P.H.Cook, M.A.McDonald and M.C.P.Firmin
PRESSURE DISTRlBUTlONS FOR AIRFOIL NAE 75-036-113: 2 AT REYNOLDS
NUMBERS FROM 14 TO 30 MILLION
by NAEINRC
SUPERCRITICAL AIRFOIL MBB-A3-SURFACE PRESSURE DISTRIBUTIONS,
WAKE AND BOUNDARY CONDITION MEASUREMENTS
by G.Bucciantini. M.S.Oggiano and M.Onorato
EXPERIMENTAL INVESTIGATION OF A 10 PERCENT THICK NASA SUPERCRITICAL
AIRFOIL SECTION
by C.D.Harris
APPENDIX B - 3-D CONFIGURATIONS
by P.J.Bobbitt
PRESSURE DISTRIBUTIONS ON THE ONERA-M6-WING AT TRANSONIC MACH
NUMBERS
by V.Schmitt and F.Charpin
TRANSONIC MEASUREMENTS ON THE 'ONERA AFV D' VARIABLE SWEEP WING IN
THE 'ONERA S2 MA' WIND TUNNEL
by F.Manie and J.C. Raynal
Reference
MBB.AVA PILOT-MODEL WITH SUPERCRITICAL WINC-SURFACE PRESSURE
AND FORCE MEASUREMENTS
by H.Korner, W.Lorenz-Meyer, A.Heddergott and A.Eberle
PRESSURE DISTRlBUTION MEASURED IN THE RA 8ft x 6ft TRANSONIC WIND TUNNEL
ON RAE WING "A" IN COMBINATION WITH AN AXI-SYMMETRIC BODY AT MACH
NUMBERS OF 0.4,0.8 and 0.9
by D.A.Treadgold, A.F.lones and K.H.Wilson
PRESSURE DISTRIBUTIONS MEASURED ON AN NASA SUPERCRITICAL-WING RESEARCH
AIRPLANE MODEL
by C.D.Harris and D.W.Bartlett
APPENDIX C - BODY-ALONE CONFIGURATIONS
by T.W.Binion
1.5 D OGIVE - CIRCULAR CYLINDER BODY, LID = 21.5
by K.Hartmann
MBB- BODY OF REVOLUTION N0.3
by W.Lorenz-Meyer and F.Aulehla
PRESSURE DISTRIBUTION DATA FOR A 1OoCONECYLINDER AT ZERO INCIDENCE
IN THE MACH NUMBER RANGE 0.91 to 1.22
by the High Speed Aerodynamics Laboratory NAE/NRC
ONERA CALIBRATION MODEL C5
by X.Vaucheret
1. INTRODUCTION AND OVERVIEW OF CONFIGURATIONS
by
Jiirgen Barche
DFVLR-AVA, Sunsenstr. lo, D-3400 Gottingen
1.1 Objectives and Scope of Work
The well-known economical advantages of applying transonic flow technology to aircraft
design has created a world-wide interest in methods predicting and analysing such flows.
Consequently, a large number of computer codes exist today reflecting past and present
theoretical and numerical standards in the solution of the basic flow equations. Since
proof of validity and refinements of computational methods are primarily based on experi-
mental results, erros inherent to data generated by any individual test facility may
easily enter a computational method thus restricting its general applicability and com-
patibility.
To improve the applicability of transonic technology to practical aircraft design the
AGARD Fluid Dynamics Panel (FDP) established the Specialist Working Group WG 04:
EXPERIMENTAL DATA BASE FOR COMPUTER PROGRAM ASSESSMENT
with the
OBJECTIVES
"To assess, screen and identify the highest quality 2-D (section) and 3-D
(wing-body) data available, particularly in the transonic speed regime,
which is urgently needed as reference data in the development and refinement
of costly computer programs for aircraft design. Data will be analysed with
consideration for relevancv to oeometric confiourations suitable for analvtic
comparison needs, test~ i~ nstrumentation,~ pr~~o cedu2 re~s~ , conditions~ ~, corrections,
and adequacy of range of test variables.''
As a consequence of the urgent need for the Data Base a period of only one year was given
the Group to accomplish its task. To guide the Working Group FDP defined the
SCOPE OF WORK
"The Group will recommend at the earliest possible date the best 2-D and 3-0
data available, if acceptable as a base data set, and provide detailed geometric
descriptions of models. The Group will define required additional testing to
establish adequacy of and confidence in the data. A programme of action will be
recommended including which facilities should be utilized to obtain the needed
data in an expedient manner without excessive demands on any one country or faci-
lity. The final selected data will be published as an AGARD report."
1.2 Group Members and Meetings
To assess, screen and identify the highest quality data available for the Data Base and
to assemble these data into a final report specialists in theoretical and experimental
transonic flow research have been nominated by the delegates of the Fluid Dynamics Panel.
The WG thus formed had the following members:
T.W. Binion ARO-AEDC USA
G. Bucciantini Aeritalia Italy
P.J. Bobbitt NASA-Langley USA
H. Korner DFVLR-Braunschweig Germany
M. Monnerie ONERA France
L.H. Uhman NAE Canada
J. Slooff NLR Netherlands
E. Stanewsky DNLR-Wttingen Germany
H. Viviand ONERA France
K.G. Winter RAE-Bedf ord UK
The Group was chaired by
J. Barche DFVLR-Gottingen Germany
and assisted by numerous specialists from industry and research institutes of various
countries.
To accomplish the tasks two meetings were arranged. The first one was held at AGARD-Head-
quartes at Neuilly, France, during Dec. 8 through Dec. 10, 1976. Here evaluation criteria
were established, and configurations and data previously submitted by the members were
reviewed and a pre-selection carried out according to these criteria. The second meeting
was hosted by ONERA at Modane from Sept. 22 through Sept. 24, 1977. Topics of this meet-
ing were the final selection of configurations and data to be included in the Data Base,