NACA 0015 Wing Pressure and Trailing Vortex Measurements i

148 Pages·2015·4.95 MB·English

https://ntrs.nasa.gov/search.jsp?R=19920001763 2019-04-11T11:11:37+00:00Z
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NACA 0015 Wing Pressure
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and Trailing Vortex
Measurements
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(NASA-TP-3IS1) _ACA 0015 WING PRESSURE AND N92-10981
TRAILING VORTEX MEASUREMENTS (NASA) 141 p
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NASA Technical Paper 3151
AVSCOM Technical Report 9I-A-003
NACA 0015 WING PRESSURE AND TRAILING VORTEX MEASUREMENTS
K. W. McAlister and R. K. Takahashi
November 1991
Pages 89-90: Figure 39 is out of sequence. It should come after Figure 38 (page 93).
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Issued 11-26-91

NASA
Technical
Paper
3151
AVSCOM
Technical
Report
NACA 0015 Wing Pressure
91-A-003
and Trailing Vortex
Measurements
1991
K. W. McAlister
and R. K. Takahashi
Aeroflightdynamics Directorate
USAARTA-A VSCOM
Ames Research Center
Moffett Field, California
National Aeronautics and
Space Administration
Office of Management
Scientific and Technical
Information Program

CONTENTS
Page
NOMENCLATURE ............................................................................. v
SUMMARY .................................................................................... I
INTRODUCTION .............................................................................. 1
TEST DESCRIPTION .......................................................................... 3
Facility and Model ......................................................................... 3
Pressure Measurements ..................................................................... 3
Velocity Measurements ..................................................................... 4
Vortex Locator ............................................................................. 4
Data Acquisition ........................................................................... 4
RESULTS AND DISCUSSION ................................................................... 5
Surface Pressure ........................................................................... 5
Wing Circulation .......................................................................... 8
Trailing Vortex ............................................................................ 9
CONCLUDING REMARKS ................................................................... 13
APPENDIX--WALL CORRECTIONS .......................................................... 15
Solid and Wake Blockage ................................................................. 15
2D Blockage Factor ....................................................................... 16
3D Blockage Factor ....................................................................... 17
2D Lift Interference ....................................................................... 17
3D Lift Interference ....................................................................... 18
REFERENCES ................................................................................ 20
TABLES ...................................................................................... 22
FIGURES ..................................................................................... 28
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NOMENCLATURE
W test-section width parallel to airfoil span
coordinate in free-stream direction
X
cross-sectional area of airfoil X coordinate along airfoil chord
Aa
Y coordinate along test-section width
(perpendicular to wing span)
parallel to airfoil span
Ap planform area of wing (cs for rectangular
coordinate along test-section height
wing) z
coordinate normal to airfoil chord
At cross-sectional area of tunnel (bh for
rectangular tunnel)
airfoil angle of attack
AR Aspect ratio, 2s/c a
b test-section breadth parallel to airfoil /3 compressibility factor, (1- M2u)1/2
span (double, if half-span model) F circulation
C airfoil chord 6 offset correction to solid blockage,
chord force coefficient, chord
defined by equation (A-14)
force/ Apqcc 8E mean lift interference parameter for
drag coefficient, drag/Apqcc elliptic spanwise loading
el
lift coefficient, liftlApqoo 60 upwash interference at a lifting line
Cm
moment coefficient, moment/cApqoo 61 upwash interference associated with
normal force coefficient, normal
streamline curvature due to finite chord
force/Apqoo A corrected - uncorrected value
c,
pressure coefficient, (p - Poo)/ qoo e blockage factor
d distance from airfoil to nearest wall
solid blockage due to angle of incidence,
ratio of ellipse chord to ellipse chord plus
defined by equation (A-15)
fin A test-section shape parameter, defined by
F function defined by equations (A-26)
equations (A- 18) and (A- 19)
h test-section height (perpendicular to
function of fitting ellipse, defined by
airfoil span) #
equation (4)
function of fitting ellipse, defined by u
fluid kinematic viscosity
equation (3) nh/b
M
Mach number P fluid density
P static pressure
quantity appearing in equation (2),
qco dynamic pressure, _pV_zl2 7-
, 2(c12
ratio of nose radius to airfoil chord cr span ratio, _-g g
r
Re Reynolds number, cVoe/u X span ratio, 2s/b
8 airfoil span (half-span, if mounted on
wall) Subscripts
SI function defined by equations (A-26) oo free-stream value
t airfoil thickness u uncorrected value
V velocity along airfoil surface b blockage-corrected value
y_ velocity in free-stream direction sc streamline-curvature-corrected value
v_ velocity in vertical direction 0 value of quantity at zero lift
V_ free-stream velocity
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