Longitudinal aerodynamic characteristics of a Sparrow 3 wing control missile model were measured through a range of separation distances relative to a flat plate surface that represented the parent-body configuration. Measurements were obtained with and without two dimensional circular arc protuberances attached to the flat plate surface. The tests were conducted at a Mach number of 2.86 and a Reynolds number per meter of 6.56 million. The behavior of these longitudinal characteristics with varying separation distance in the flow field created by the flat plate and protuberance was generally as would be expected on the basis of flow field boundaries determined from the second order approximation of Friedrich. In general, varying roll angle from 0 deg to 45 deg caused no significant effect on the store separation characteristics

Stallings, R. L., Jr.

English

NASA Technical Reports Server

fx£ DOhNASA Technical Memorandum 85713FU
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Aerodynamic Characteristics of
a Sparrow III Missile Model in
the Flow Field of a Generalized
Parent Body at Mach 2.86
oo
Robert L. Stallings, Jr.
FEBRUARY 1984
1
NASA
https://ntrs.nasa.gov/search.jsp?R=19840009066 2020-03-20T23:39:41+00:00Z
NASA Technical Memorandum 85713
Aerodynamic Characteristics of
a Sparrow III Missile Model in
the Flow Field of a Generalized
Parent Body at Mach 2.86
Robert L. Stallings, Jr.
Langley Research Center
Hampton, Virginia
NASA
National Aeronautics
and Space Administration
Scientific and Technical
Information Office
1984
INTRODUCTION
For high-speed fighters capable of supersonic weapons delivery, information
concerning the effect of store separation distance on the store aerodynamic charac-
teristics at supersonic speeds is required to insure safe store separation. Most of
the existing supersonic separation data were obtained during development of specific
airplane configurations and, therefore, have limited general application. The exist-
ing data are also somewhat cumbersome to model for theoretical test cases because of
the complexity of the parent-body flow field. In order to provide some basic store
aerodynamic data for a range of store separation distances at supersonic speeds, a
test program was initiated at the NASA Langley Research Center using existing models
consisting of a Sparrow III wing-control missile model (ref. 1) that represented the
store and a splitter plate that represented the parent aircraft. The splitter plate
was tested with and without circular-arc protuberances attached to its surface.
The tests were conducted in the low-speed test section of the Langley Unitary
Plan Wind Tunnel at a Mach number of 2.86 and a Reynolds number per meter of
6.56 x 106.
C. axial-force coefficient,
SYMBOLS
Axial force
Pitching moment
C pitcning-moment coefficient, |-
Normal force
C.- normal-force coefficient,
w qS
D store body diameter, 3.048 cm
h circular-arc protuberance height, cm
L store length, 54.86 cm
q free-stream dynamic pressure, Pa
S store body cross-sectional area, 7.297 x 10 m^
V,,, free-stream velocity vector, m/sec
X surface distance downstream from plate leading edge, cm
X value of X at location of protuberance leading edge, cm
X value of X at location of store nose, cm
AX increment in X from protuberance trailing edge to store nose, cm
Z perpendicular distance from plate surface to store axis of symmetry (store
separation distance), cm
4> store model roll angle, deg
APPARATUS AND METHODS
Wind Tunnel and Test Conditions
The tests were conducted in the Langley Unitary Plan Wind Tunnel. This facility
is a variable-pressure continuous-flow wind tunnel with two test sections that permit
a variation in Mach number from 1.5 to 4.6. Ahead of each test section is an asym-
metric nozzle that permits a continuous variation in Mach number from 1.5 to 2.9 in
the low Mach number test section and from 2.3 to 4.6 in the high Mach number test
section. The test sections are approximately 2.1 m long and have a cross-sectional
area of approximately 1.2 m . A complete description of the facility is given in
reference 2.
The free-stream test conditions were a Mach number of 2.86, a free-stream
Reynolds number per meter of 6.56 x 10 , a stagnation pressure of 98.54 kPa, and a
stagnation temperature of 339 K.
Models
The general arrangement of the store model and the splitter plate that repre-
sented the parent aircraft is shown in figure 1. Photographs of the store model and
splitter plate are shown in figure 2.
The store model geometry (f ig. 3) consisted of an ogive-cylinder body, cruciform
wings, and in-line tails. The wings had a trapezoidal planform and a diamond airfoil
section. The tails had a triangular planform and a modified diamond airfoil section.
Relative to the splitter plate surface, the model was tested at zero angle of attack,
zero angle of yaw, and roll angles of 0° and 45°.
The parent aircraft for the present test was represented by a vertical splitter
plate that extended from the floor to the ceiling of the test section and was approx-
imately 1 .8 m in length. Photographs of the plate are shown in figure 2 and basic
dimensions are given in figure 4(a) . In order to establish supersonic flow on the
back side of the flat plate, which was required to eliminate contamination of the
front surface due to spillage, the back side discharge area was increased by inclin-
ing the plate 1° relative to the free-stream flow, as shown in figure 4 ( a ) . Because
the flow over the plate is two-dimensional and the centerline of the store model is
always parallel to the flat-plate surface, the major effect of this 1° angle is a
small change in the local flow conditions on the plate. For example, the local Mach
number of the flat-plate flow field is 2.81 rather than 2.86 and the local nominalfi 6Reynolds number per meter is 6.72 x 10 rather than 6.56 x 10 . It should be noted
that all force and moment data reductions were based on free-stream conditions rather
than the local plate conditions.
Two-dimensional circular-arc protuberances were attached to the flat plate as
shown in figure 1 to perturb the flat-plate flow field in some tests. Photographs of
the flat-plate assembly with a protuberance attached at two different stations are
shown in figure 2. The basic dimensions of the circular-arc protuberances are given
in figure 4(b). Protuberances with thicknesses of 1.27 and 2.54 cm were constructed
and tested. Each protuberance was tested with its leading edge coincident with the
flat-plate leading edge and at a location 33.02 cm downstream of the plate leading
edge, as indicated in figure 1.
A boundary-layer transition strip consisting of randomly distributed No. 50 sand
(0.032 cm nominal height) in a 0.159-cm-wide band was applied to the flat plate
1.02 cm downstream from the leading edge. For the store model, transition strips
consisted of individually applied No. 40 sand elements (0.046 cm nominal height)
spaced about 0.184 cm between centers measured perpendicular to the airstream. The
strips were located on the wings and fins 1.02 cm streamwise downstream from the
leading edges and on the nose 3.05 cm downstream from the apex.
Measurements
Aerodynamic forces and moments of the store were measured with a six-component
strain gage balance. Since the forces and moments in the lateral plane were essen-
tially zero because of lateral flow symmetry, only the three components of data about
the longitudinal axis (€„, C , and C,) are presented. No corrections have been
applied to the present data for chamber pressure. Chamber pressures were measured
for part of the test conditions and were found to remain approximately constant at a
value corresponding to a chamber axial-force coefficient of 0.070, which is in good
agreement with results presented in reference 1.
RESULTS AND DISCUSSION
In order to facilitate discussion of the store separation data, estimates of the
boundaries of the protuberance flow field were determined from the second-order
inviscid approximation of Friedrich (ref. 3) and are shown in figure 5 relative to
the store separation matrix for the two protuberance heights and locations. Store
separation distances are shown for both the forward store station (Xg = 84.77 cm) and
the aft store station (X = 105.09 cm).
Figure 6 shows store aerodynamic characteristics (<|> = 0°) for the two protuber-
ance locations (X = 0 and 33.02) and the two store stations for each protuberance
location. The results presented in figures 6 (a) through 6(d) are for decreasing
values of AXgp ranging from the maximum separation distance of 59.37 cm to the
minimum separation distance of 6.03 cm. The data presented show that for
AXSp > 39.05 (figs. 6(a) and 6(b) ) and Z/D < 4, protuberance height has only minor
effects on the store separation characteristics. This trend indicates that the
variation in Cm and CN for this range of Z/D is a result of local interactions
between the store model and the flat plate rather than changes in the protuberance
flow field. The calculated flow boundaries for this range of Z/D and AXgp
presented in figures 5(a) and 5(b) show that the store model is located between the
flat-plate surface and the protuberance trailing-edge shock. Therefore, its
aerodynamic characteristics would not be expected to be significantly affected by the
protuberance flow field.
The flow boundaries presented in figures 5(a) and 5(b) indicate that for the aft
store station (AXg = 59.37) the store model penetrates the protuberance flow field
at Z/D » 5 or 6, and for the more forward store station (AXgp = 39.05), at
Z/D » 3.5 or 4. Once the store model penetrates the protuberance flow field, its
aerodynamic characteristics are affected by protuberance height, as shown, for
example, in figure 6(b) for AX = 39.05. As the nose of the store model enters the
protuberance flow field, it is exposed to an upwash region created by the flow
expanding over the rear half of the protuberance. This upwash region results in an
increase in the store pitching moment. For AXgp = 39.05 (fig. 6(b)), the increase
in C initially occurs at Z/D « 4, and for h = 1.27, a peak value is obtained at
Z/D » 8.
At Z/D » 8, the nose of the model is located in the vicinity of the flow field
where the local flow direction is parallel to the free-stream direction (fig. 5(a))
and the wings are just inside the trailing-edge shock. With further increases in
Z/D, the model nose is located in the downwash region created by the forward half of
the protuberance. Thus, a decrease in C results. Minimum values of C were
obtained at Z/D « 1 2. For the 1.27-cm protuberance, the store normal-force coef-
ficient for AXSp = 39.05 (fig. 6(b)) remained approximately constant at
4 < Z/D < 7. At Z/D » 7, the store model wing crosses the trailing-edge shock,
resulting in a sharp increase in CN. Peak values are measured at Z/D « 10. Also
for AXsp = 39.05, the store axial-force coefficients generally decrease with
increasing Z/D at Z/D < 5 and increase with further increases in Z/D at
5 < Z/D < 1 2. In general, the results of figure 6(b) show that at Z/D > 4, increas-
ing h results in an increase in the magnitude of the maximum store pitching-moment
coefficient and normal-force coefficient and a decrease in the value of Z/D at
which peak pitching-moment coefficient is measured. The results presented in figure
6(b) also show that increasing h results in a slight decrease in the value of
Z/D at which the model nose and the model wings cross the protuberance flow-field
trailing-edge shock, as indicated by the onset of the positive gradients in C
and C.,, respectively. Increasing h also results in a decrease in the minimum
measured value of C..
The results presented in figures 6(a) through 6(d) show that for a given pro-
tuberance height the trends with Z/D discussed for figure 6(b) are somewhat similar
for the range of AXgp tested, although there is a shift in the aerodynamic coef-
ficient distributions toward the plate surface with decreasing AXgp because of the
protuberance flow field approaching the plate surface. For the minimum store-
protuberance separation distance, AXgp = 6.03 (fig. 6(d)), a large portion of the
store model is contained within the protuberance flow field at the minimum test value
of Z/D. Therefore, for this minimum store-protuberance separation distance, pro-
tuberance height has a large effect on the store aerodynamic characteristics, in
contrast to the negligible effect shown previously for the maximum separation
distance.
The effect of roll angle on the store model separation characteristics is shown
in figure 7. In general, the results show no significant effect of roll angle for
the range of test variables.
The aerodynamic characteristics of the store model with and without the store
wings attached are presented in figure 8 for $ = 0°. The model tails were not
removed for either of these configurations. The results presented in figure 8(a) are
for the clean plate carriage configuration and show that the store wings make little
if any contributions to the store pitching-moment or normal-force coefficients - even
for values of Z/D < 4 - where the store model and flat-plate flow-field interac-
tions affect the store aerodynamic characteristics, as shown previously. The data
show the anticipated reduction in CA with removal of the wings. Presented in
figure 8(b) are data for h = 1.27 and AXsp = 26.35. These results show that in
the protuberance flow field the wings make significant contributions to both CN
and Cm« Similar trends are noted in figure 8(c) for AXsp = 6.03.
CONCLUDING REMARKS
Measurements of the longitudinal aerodynamic characteristics of a Sparrow III
missile model with wing controls have been obtained through a range of separation
distances relative to a flat-plate surface representing the parent-body configura-
tion. Data were obtained both with and without two-dimensional circular-arc pro-
tuberances attached to the flat-plate surface. the tests were conducted in the low
Mach number test section of the Langley Unitary Plan Wind Tunnel at a Mach number
of 2.86 and a Reynolds number per meter of 6.56 x 10 . The following results were
obtained from these tests:
1. The behavior of the store aerodynamic characteristics with varying separation
distance in the flow field created by the flat plate and protuberance was generally
as would be expected on the basis of flow-field boundaries determined from the
second-order approximation of Friedrich.
2. When the store model was located between the flat-plate surface and the pro-
tuberance trailing-edge shock, its aerodynamic characteristics were not affected by
protuberance height, although the interactions between the store model and the flat-
plate flow field created a small effect.
3. In general, varying roll angle from 0° to 45° caused no significant effect on
the store separation characteristics.
Langley Research Center
National Aeronautics and Space Administration
Hampton, VA 23665
December 18, 1983
REFERENCES
1. Monta, William J.: Supersonic Aerodynamic Characteristics of a Sparrow III Type
Missile Model With Wing Controls and Comparison With Existing Tail-Control
Results. NASA TP-1078, 1977.
2. Jackson, Charlie M., Jr.; Corlett, William A.; and Monta, William J.: Description
and Calibration of the Langley Unitary Plan Wind Tunnel. NASA TP-1905, 1981.
3. Lighthill, M. J.: Higher Approximations in Aerodynamic Theory. Princeton Univ.
Press, 1960.
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(a) X = 0; AX = 59.37 cm.P sp
Figure 6.- Effect of protuberance height on store separation characteristics,
<b = 0°.
17
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1.0 C«
20
(b) Xp = 0; AX = 39.05 cm.
Figure 6.- Continued.
18
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20
(c) X_ = 33.02 cm; AX = 26.35 cm.
P sp
Figure 6.- Continued.
19
14 16 18 20
(d) X_, = 33.02 cm; AX = 6.03 cm.
sp
Figure 6.- Concluded.
20
m o
1.0 C,
20
(a) h = 0; Xg = 84.77 cm.
Figure 7.- Effect of roll angle on store separation characteristics.
21
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1.0 CA
(b) h = 2.54 cm; AX = 59.37 cm.
sp
Figure 7.- Continued.
22
6 8 10 12
(c) h = 2.54 cm; AX = 6.03 cm.
sp
Figure 7.- Concluded.
23
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18 20
(a) h = 0; Xg = 84.77 cm.
Figure 8.- Store separation characteristics with and without wings. <|> = 0°,
24
10 12 14 16 18 20
(b) h = 1.27 cm; AX = 26.35 cm.
sp
Figure 8.- Continued.
25
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(c) h = 1.27 cm; AX = 6.03 cm.
sp
Figure 8.- Concluded.
26
1. Report No.
NASA TM-85713
2. Government Accession No. 3. Recipient's Catalog No.
4. Title and Subtitle
AERODYNAMIC CHARACTERISTICS OF A SPARROW III MISSILE
MODEL IN THE FLOW FIELD OF A GENERALIZED PARENT BODY
AT MACH 2.86
5. Report Date
February 1984
6. Performing Organization Code
505-43-23-02
7. Author(s)
Robert L. Stallings, Jr.
8. Performing Organization Report No.
L-15705
10. Work Unit No.
9. Performing Organization Name and Address
NASA Langley Research Center
Hampton, VA 23665
11. Contract or Grant No.
12. Sponsoring Agency Name and Address
National Aeronautics and Space Administration
Washington, DC 20546
13. Type of Report and Period Covered
Technical Memorandum
14. Sponsoring Agency Code
15. Supplementary Notes
16. Abstract
Longitudinal aerodynamic characteristics of a Sparrow III wing-control missile model
were measured through a range of separation distances relative to a flat-plate sur-
face that represented the parent-body configuration. Measurements were obtained with
and without two-dimensional circular-arc protuberances attached to the flat-plate
surface. The tests were conducted at a Mach number of 2.86 and a Reynolds number per
meter of 6.56 * 10 . The behavior of these longitudinal characteristics with varying
separation distance in the flow field created by the flat plate and protuberance was
generally as would be expected on the basis of flow-field boundaries determined from
the second-order approximation of Friedrich. In general, varying roll angle from 0°
to 45° caused no significant effect on the store separation characteristics.
17. Key Words (Suggested by Author(s))
Store separation
Aerodynamic characteristics
Supersonic
18. Distribution Statement
Unclassified - Unlimited
Subject Category 02
19. Security Oassif. (of this report!
Unclassified
20. Security Classif. (of this page)
Unclassified
21. No. of Pages
27
22. Price
A03
For sale by the National Technical Information Service, Springfield, Virginia 22161
NASA-Langley, 1984


Aerodynamic characteristics of a Sparrow 3 missile model in the flow field of a generalized parent body at Mach 2.86

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