V/STOL Aircraft Aerodynamic Prediction Methods Investigation. Volume 1. Theoretical ...

238 Pages·2012·7.96 MB·English

AD-752 557
V/STOL AIRCRAFT AERODYNAMIC PREDICTION
METHODS INVESTIGATION. VOLUME I. THEO-
RETICAL DEVELOPMENT OF PREDICTION
METHODS
Peter T. Wooler, et al
Northrop Corporation
Prepared for:
Air Force Flight Dynamics Laboratory
January 1972
DISTRIBUTED BY:
National Technical Information Service
U. S. DEPARTMENT OF COMMERCE
5285 Port Royal Road, Springfield Va. 22151
AFFDL-TR-72-M
V/STOL AIRCRAFT AERODYNAMIC
PREDICTION METHODS INVESTIGATION
Volume 1. Theoretical Development of Prediction Methocs
(cid:127))m P.T. Wooler
H.C. Kao
M.F. Schwendemnann
H.R. Wasson
H. Ziegler
Northrop Corporation
Aircraft Division
TECHNICAL REPORT AFFDL-TR-72-26, Volume I
January 1972
r-- r
Approved for public relea; distribution unlimited. ,LF
NATIONA/(cid:127) L TECHNICNAL tl V))
INFOR,MATIO? SErPVICE jih.'- ;
AIR FORCE FLIGHT DYNAMICS LABORATORY
AIR FORrU SYSTEMS COMMAND
WRIGHT-PATTERLON AIR FORCE BASE, OHIO 48433
(I//
NOTICE
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is not to be regarded by implication or otherwise as in any manner licensing the
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manufacture, use, or sell any patented invention that may in any way be related
thereto.
I
Copies of this report should net be returned unless return is required by security con-
slderations, contractual obligations, or notice on a specific document.
I'
AIR FORCE/56780/30 November 1972 --300
Unclassified
secuuitt Classification
DOCUMENT CONTROL DATA.- R & D
(Seoiwity Classificationo f title,.b ody of obetteed "~ indeuing or* ,,fatiae mse be entered when the 0owroll repart Is elassifiel~
I )RIGINATINS ACTIVITYV(Coopomrebeeu*4) 2Za. REPORT SEC JRITY CLASSIFICAT.ON
N~orthrop Corpcration IUnclasssfie'ri
Aircraft Division
Sb. GROUP
Hawthorne, California
3 REPORT TITLE
V/STOL AIRCRAFT AFROD-NAMIC PREDICTION METrHODS INVESTIGATION -
Volume I
A
DESCRIPTIVE NOTES (Ty'pe afreport and Iulunive datee)
Final Report - 1 May 1969 to 31 January 1972
S PAVe TtHeOrR IITaI .f (PWhato rooslse, r otiddle 110filf last na00) Howard R. Wasson
Hsiao C,~ Kao Henry Ziegler
Myles F. Schwendemann_____
* MEPORT DATE 118. TOTAL NO OFP AGES 7b. NO. OF REFS
Januar~y 1972 2-3Z2 50
S.CONTRACT OR GRANT NO S.ORIGINATOP'S REPORT NUMOERISI15
F33615-69-C-1602
5.PROJIECT NO0 NOR 72-9, Volume 1
698 BT
~.TasA No. 698 BT 01
9b. OTHER REPORT NOMS (Any Other ntinlbONO rfior may be .easloed
at____________________ AFFrL-TR-72-26, Volume 1
10 OISTAIISUIION STATEMENT
Approved for public release,, distributior. unlimited.,
of
SUPPLEMENTARY NOTES III SPONdSORING MILITARY ACTIVITY
Air rorce Flight Dynamics Laboratc ry
IWright-Patterson-
1 i r Force Base
Ohio 45433
ISASSTR^CT
Analytical engineering methods are developed for use in predicting the static and lynamic
stability and control derivatives and force and moment c.-)efficients of lift-jet, lift-fan,
and vectored thrust V/sTOL aircraft in the hover and transition flight regimes. The
methods teke into account the strong power effects,. large variations in angle of attack
and sideslip, and changes in aircraft geometry that are associated with high disk loaded
V/STOL aircraft operating in the aforementioned flight regimes,~ The aircraft
configurations studied have a conventional wing, fuselage and empennage. The pre-
diction methods are suitable for use by design personnel during the preliminary design
and evaluation of V/STOL aircraft of the type previously mentioned.
This report c2onsists of four volumes. The theoretical development of the prediction .iethods
is presented in this volume. The methods are applied to a number of V//STOL configurations
in Volume 11. Details of the c~rmputei: programs ahsociated with the prediction methods are
given in Volume 111. The results of a literature survey are present~d in Volume IV,
Details 01 illustrations in
this document may be better
j stiggied Onl microfiche
~ DD , Nov__J_473_1_Inc
__I______fied
Unclassified
Se-curity Classification
-4 LINK A LINK a LINK C
KIEV 00OLE WT ROLL WT ROLE WT
V/STOL Aircraft
XV-5A
V/STOL Stability and Control
Aerodynamic Characteristics (Subsonic)
Forces (Normal Force, Lift, Side Force)
Moments (Pitching, Rolling, Yawing)
Rotary Derivatives
V/STOL Aerodynamics
Nonlinear Aerodynamics
Wing Stall
Separated Flows
V/STOL Transitional Flight
Engine Wake Effects
Jet Exhaust Fields
Jet Interference Effects
Jet i,. Cross Flow
Jet Path
Multiple Jets
Jet Interaction
Power Effects
Fngine Inlet Effects
Vortices
Computer Programs
"(cid:127)Q
S G-.ernmtnt Printing Office 1972 759-488/;,' (, ,.
V/STOL AIRCRAFT AERODYNAMIC
PREDICTION METHODS INVESTIGATI(cid:127)k
Vclume I
Theoretical Development of Prediction Methods
P.T. Wooler
P.C. Kao
M.F. Schwendemann
H.R. Wasson
H. Ziegler
Approved for public release; distribution unlimited.
FOREWORD
This report summarizes the work accomplished by the Aircraft Division of
Northrop Corporation, Hawthorne, California for the Air Force Flight Dynamics
Laborat-,-y, AFSC, Wright Patterson Air Force Base, Ohio, and USAF Contract
No. F33615-69-C-1602 (Proict 698 BT). This document constitutes the Final Report
under the contract.
This work was accomplished during the period 1 May 1969 to 31 January 1972,
and this report was released by the authors in January 1972. The Air Force Pv:oject
Engineers were Mr. Robert Nicholson and Mr. Henry W. Woolard of the Con'rol
Criteria Branch, Flight Control Division, AFFDL. Their assistance in inc- itoring
the work and providing data is greatly appreciated.
The authors gratefully acknowledge the assistance and cooperatiou ,.i '.ASA
Langley Research Ccter personnel during the w:.id tunnel model testing in the NASA
Langley V/STOL tunnel.
Special recognition is due Mr. Richard J. Margason of NASA Langley Research
Center who, besides being actively irvolved in the testing at Langlel , has made valu-
able co3ntributions to other areas of thu investigation.
Various people at Northrop's AirLraft Division contributed to the inies'igation,
particularly the following persons in the areas designated:
Lynn B. ?'ricke Developed empirical methods for the wing. Was Test
Engineer for the wind tunnel testing of the component
model.
Hslao C. Kao Developed the transformation method for estimating
power effects on wings and fuselages. Developed the
empirical method for the body.
Myles F. Schwendemann Developed the method for estimating engine inlet effects.
Provided prediction method wir.d tunnel tez(cid:127)ting interface
for the configuration m'dei. Participated in the hover
analysis.
ii
Martin F. Silady Assembled the V/STOL bibliography and was responsible
!or the literature survey.
Howard R. Wasson Developed the method for mapping general sections.
Developed the nonlinear body prediction method. Assisted
with the development of the perturbation method.
Peter T. Wooler Directed the technical effort and developed the nonlinear
wing prediction method,
Henry Ziegler Developed the jet flow field prediction method. Per-
iormed the analysis of wing power effects employing
li.fting surface theory.
Contributions have also been made by U. A.G. Brynjestad to this study in a num-
ber of areas, particularly the literature search and perturbation method development;
by M. S. Cahn in the development cf the method for mapping general sections and per-
turbation method development; by members of the Northrop Aerosciences Laboratories
in respect to model design, fabrication, testing and data reduction - especially
T. Comerinsky, F. W. Peitzman, E. G. Kontos and W. S. Ramos.
This report contains no classified information.
This technical report has been reviewed and is 3pproved.
TB.: Westbrook
Chief, Control Criteria Branch
Flight Control Division
Air Force Flight Dynamics Laboratory
iii
ABSTRACT
Analytical engineering methods are developed for use in predicting the static
a'J dynamic stability and control derivatives and force and moment coefficients of
lift-jet, lift-fan, and vectored thrust V/STOL aircraft in the hover and transition
flight regimes. The methods take into account the strong power effects, large
variations in angle of atta&ck and sideslip, and changes in aircraft geometry that are
associated with high disk :oaded V/STOL aircraft operating in the aforementioned
flight regimes. The aircraft configurations studied have a conventional wing,
fuselage and empennage. The prediction methods are suitable for use bh desi.,-;l
personnel during the preliminary design and evaluation of V/STOL aircraft of the
type previously mentioned.
This report consists of four volumes. The theoretical development of the
prediction methods is presented in this volume. The methods are applind to a number
of V/STOL configurations in Volume II. Details of the computer programs associated
with the prediction methods are given in Volume III. The results o1 a literature
survey are presented in Volume IV.
Preceding page blank
v
TABLE OF CONTENTS
Section Page
I INTRODUCTION . ....................................
i1. PURPOSE 2......................................2
2. TECHNICAL APPROACH ........................ .......... 2
3. REPORT ORGANIZATION. ................................ 3
1 JETFLOWFIE LDTHEORY.. .M.D........................... 5
1. SINGLE JET ANALYTICAL MODEL......................... 7
a. Normally Exhausting Jet 7.........................7
(1) Equations of M.otion ......................... 9
(2) Inm gration of the Equations of Motion ............... 11
(3) Determination of Empirical Parameters ............. 14
(4) Calculation of the Induced Velocity Field ............. 16
b. Arbitrary Jet Direction .......................... 23
2. COMPARISONS OF SINGLE JET-COMPUTATIONS
WITH TEST DATA .................. ............. 26
a. JetCenterlin,, .................... ......... ...... 26
b. InducedPressurcs .... ............. ....... ......... 31
3. MULTIPLE JET ANALYTICAL MODEL ................. 42
a. Two-Jet Computations .......................... 42
b. Determination of Empirical Parameters ................. 45
(1) Effective Dynamic Pressure for Downstream Jets ..... 45
(2) Jet Decay Characteristics ..................... 49
(3) Geormetry of Merged Jet ...................... 56
4. COMPARISON OF TWO-JET CALCULATIONS
WITH TEST DATA ................................ 57
5. APPLICATIONS TO MORE COMPLEX CONFIGURATIONS ..... 72
III MAPPING METHOD FOR ARBITRARY CROSS SECTION ........... 77
1. COMPUTATION OF COMPLEX POTENTIAL FOR
VORTEX FLOW . ................................. 78
2. %'2OMPUTATION OF DERIVATIVE OF MAPPING
FUNCTION WITH CORNERS .......................... 82
COMPUTATION OF MAPPING Fi -ICTION .................. 83
. SAMPLE CALCULATIONS OF MAPPINGS ................ 84
vii Preceding page blank