March 2005 NASA/TM-2005-213541 Aerodynamics of an Axisymmetric Missile Concept Having Cruciform Strakes and In-Line Tail Fins From Mach 0.60 to 4.63 Jerry M. Allen Langley Research Center, Hampton, Virginia https://ntrs.nasa.gov/search.jsp?R=20050160470 2020-04-08T20:08:05+00:00Z
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Aerodynamics of an Axisymmetric Missile Concept Having ...€¦ · Reliable control laws on missile configurations depend on accurate modeling of control fin loads over the missile’s
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Figure 19. First page of free-format ASCII SIF data file.
47
82 42 02 61 21 8 4 0 4-α, deg
2-
0
2
4
6
8
01
C FN
nuR
59
98
47
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
φ
0.0
0.09-
0.09
δ1
0.0
0.0
0.0
δ2
0.0
0.0
0.0
δ3
0.0
0.0
0.0
δ4
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-α, deg
02-
51-
01-
5-
0
5
01
51
C MP
(a) Configuration longitudinal loads.
Figure 20. Data repeatability assessment.
48
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
59
98
47
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
φ
0.0
0.09-
0.09
δ1
0.0
0.0
0.0
δ2
0.0
0.0
0.0
δ3
0.0
0.0
0.0
δ4
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
21-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 20. Continued.
49
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
Tai
l fin
CN
F
niF
342
niF rewoL
5.1-
0.1-
5.-
0
5.
0.1
5.1
Tai
l fin
CN
F
niF
124
niF reppU
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
Tai
l fin
CN
F
niF
413
niF tfeL
5.1-
0.1-
5.-
0
5.
0.1
5.1
Tai
l fin
CN
F
niF
231
niF thgiR
α, deg α, deg
(c) Tail fin normal force.
Figure 20. Continued.
50
82 42 02 61 21 8 4 0 4-51.-
01.-
50.-
0
50.
01.
51.
Tai
l fin
CH
M
niF
342
niF rewoL
51.-
01.-
50.-
0
50.
01.
51.
Tai
l fin
CH
M
niF
124
niF reppU
82 42 02 61 21 8 4 0 4-51.-
01.-
50.-
0
50.
01.
51.
Tai
l fin
CH
M
niF
413
niF tfeL
51.-
01.-
50.-
0
50.
01.
51.
Tai
l fin
CH
M
niF
231
niF thgiR
α, deg α, deg
(d) Tail fin hinge moment.
Figure 20. Continued.
51
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
Tai
l fin
CB
M
niF
342
niF rewoL
6.-
4.-
2.-
0
2.
4.
6.
Tai
l fin
CB
M
niF
124
niF reppU
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
Tai
l fin
CB
M
niF
413
niF tfeL
6.-
4.-
2.-
0
2.
4.
6.
Tai
l fin
CB
M
niF
231
niF thgiR
α, deg α, deg
(e) Tail fin bending moment.
Figure 20. Concluded.
52
82 42 02 61 21 8 4 0 4-2-
0
2
4
6
8
01
C FN
nuR
59
776
886
gifnoC
T-SL-NS
T-S on-NS
T on-S on-NS
hcaM
68.2
68.2
68.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
ffo
δ2
0.0
0.0
ffo
δ3
0.0
0.0
ffo
δ4
0.0
0.0
ffo
δP/δY/δR
0/0/0
0/0/0
ffo
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-02-
51-
01-
5-
0
5
01
51
C MP
α, deg α, deg
(a) Configuration longitudinal loads.
Figure 21. Configuration buildup.
53
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
59
776
886
gifnoC
T-SL-NS
T-S on-NS
T on-S on-NS
hcaM
68.2
68.2
68.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
ffo
δ2
0.0
0.0
ffo
δ3
0.0
0.0
ffo
δ4
0.0
0.0
ffo
δP/δY/δR
0/0/0
0/0/0
ffo
21-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 21. Continued.
54
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 1FN
nuR
59
776
886
gifnoC
T-SL-NS
T-S on-NS
T on-S on-NS
hcaM
68.2
68.2
68.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
ffo
δ2
0.0
0.0
ffo
δ3
0.0
0.0
ffo
δ4
0.0
0.0
ffo
δP/δY/δR
0/0/0
0/0/0
ffo
51.-
01.-
50.-
0
50.
01.
51.
C 1MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 1MB
α, deg α, deg
(c) Tail fin 1 loads.
Figure 21. Continued.
55
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 2FN
nuR
59
776
886
gifnoC
T-SL-NS
T-S on-NS
T on-S on-NS
hcaM
68.2
68.2
68.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
ffo
δ2
0.0
0.0
ffo
δ3
0.0
0.0
ffo
δ4
0.0
0.0
ffo
δP/δY/δR
0/0/0
0/0/0
ffo
51.-
01.-
50.-
0
50.
01.
51.
C 2MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 2MB
α, deg α, deg
(d) Tail fin 2 loads.
Figure 21. Continued.
56
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 3FN
nuR
59
776
886
gifnoC
T-SL-NS
T-S on-NS
T on-S on-NS
hcaM
68.2
68.2
68.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
ffo
δ2
0.0
0.0
ffo
δ3
0.0
0.0
ffo
δ4
0.0
0.0
ffo
δP/δY/δR
0/0/0
0/0/0
ffo
51.-
01.-
50.-
0
50.
01.
51.
C 3MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 3MB
α, deg α, deg
(e) Tail fin 3 loads.
Figure 21. Continued.
57
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 4FN
nuR
59
776
886
gifnoC
T-SL-NS
T-S on-NS
T on-S on-NS
hcaM
68.2
68.2
68.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
ffo
δ2
0.0
0.0
ffo
δ3
0.0
0.0
ffo
δ4
0.0
0.0
ffo
δP/δY/δR
0/0/0
0/0/0
ffo
51.-
01.-
50.-
0
50.
01.
51.
C 4MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 4MB
α, deg α, deg
(f) Tail fin 4 loads.
Figure 21. Concluded.
58
82 42 02 61 21 8 4 0 4-2-
0
2
4
6
8
01
C FN
nuR
59
28
38
48
58
68
78
88
98
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.5-
0.21-
0.22-
0.04-
0.54-
0.05-
0.86-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-02-
51-
01-
5-
0
5
01
51
C MP
α, deg α, deg
(a) Configuration longitudinal loads.
Figure 22. Effects of roll angle.
59
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
59
28
38
48
58
68
78
88
98
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.5-
0.21-
0.22-
0.04-
0.54-
0.05-
0.86-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/021-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 22. Continued.
60
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 1FN
nuR
59
28
38
48
58
68
78
88
98
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.5-
0.21-
0.22-
0.04-
0.54-
0.05-
0.86-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/051.-
01.-
50.-
0
50.
01.
51.
C 1MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 1MB
α, deg α, deg
(c) Tail fin 1 loads.
Figure 22. Continued.
61
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 2FN
nuR
59
28
38
48
58
68
78
88
98
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.5-
0.21-
0.22-
0.04-
0.54-
0.05-
0.86-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/051.-
01.-
50.-
0
50.
01.
51.
C 2MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 2MB
α, deg α, deg
(d) Tail fin 2 loads.
Figure 22. Continued.
62
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 3FN
nuR
59
28
38
48
58
68
78
88
98
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.5-
0.21-
0.22-
0.04-
0.54-
0.05-
0.86-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/051.-
01.-
50.-
0
50.
01.
51.
C 3MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 3MB
α, deg α, deg
(e) Tail fin 3 loads.
Figure 22. Continued.
63
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 4FN
nuR
59
28
38
48
58
68
78
88
98
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.5-
0.21-
0.22-
0.04-
0.54-
0.05-
0.86-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/051.-
01.-
50.-
0
50.
01.
51.
C 4MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 4MB
α, deg α, deg
(f) Tail fin 4 loads.
Figure 22. Concluded.
64
82 42 02 61 21 8 4 0 4-2-
0
2
4
6
8
01
C FN
nuR
4511
8211
5001
645
015
83
59
071
012
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
09.0
81.1
07.1
00.2
63.2
68.2
59.3
36.4
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-02-
51-
01-
5-
0
5
01
51
C MP
α, deg α, deg
(a) Configuration longitudinal loads.
Figure 23. Effects of Mach number.
65
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
4511
8211
5001
645
015
83
59
071
012
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
09.0
81.1
07.1
00.2
63.2
68.2
59.3
36.4
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/021-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 23. Continued.
66
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 1FN
nuR
4511
8211
5001
645
015
83
59
071
012
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
09.0
81.1
07.1
00.2
63.2
68.2
59.3
36.4
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/051.-
01.-
50.-
0
50.
01.
51.
C 1MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 1MB
α, deg α, deg
(c) Tail fin 1 loads.
Figure 23. Continued.
67
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 2FN
nuR
4511
8211
5001
645
015
83
59
071
012
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
09.0
81.1
07.1
00.2
63.2
68.2
59.3
36.4
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/051.-
01.-
50.-
0
50.
01.
51.
C 2MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 2MB
α, deg α, deg
(d) Tail fin 2 loads.
Figure 23. Continued.
68
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 3FN
nuR
4511
8211
5001
645
015
83
59
071
012
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
09.0
81.1
07.1
00.2
63.2
68.2
59.3
36.4
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/051.-
01.-
50.-
0
50.
01.
51.
C 3MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 3MB
α, deg α, deg
(e) Tail fin 3 loads.
Figure 23. Continued.
69
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 4FN
nuR
4511
8211
5001
645
015
83
59
071
012
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
09.0
81.1
07.1
00.2
63.2
68.2
59.3
36.4
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/0
0/0/051.-
01.-
50.-
0
50.
01.
51.
C 4MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 4MB
α, deg α, deg
(f) Tail fin 4 loads.
Figure 23. Concluded.
70
82 42 02 61 21 8 4 0 4-2-
0
2
4
6
8
01
C FN
nuR
83
572
666
gifnoC
T-SL-NS
T-SS-NS
T-S on-NS
hcaM
63.2
63.2
63.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
0.0
δ2
0.0
0.0
0.0
δ3
0.0
0.0
0.0
δ4
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-02-
51-
01-
5-
0
5
01
51
C MP
α, deg α, deg
(a) Configuration longitudinal loads.
Figure 24. Effects of strake length.
71
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
83
572
666
gifnoC
T-SL-NS
T-SS-NS
T-S on-NS
hcaM
63.2
63.2
63.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
0.0
δ2
0.0
0.0
0.0
δ3
0.0
0.0
0.0
δ4
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
21-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 24. Continued.
72
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 1FN
nuR
83
572
666
gifnoC
T-SL-NS
T-SS-NS
T-S on-NS
hcaM
63.2
63.2
63.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
0.0
δ2
0.0
0.0
0.0
δ3
0.0
0.0
0.0
δ4
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 1MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 1MB
α, deg α, deg
(c) Tail fin 1 loads.
Figure 24. Continued.
73
82 42 02 61 21 8 4 0 4-α, deg
5.1-
0.1-
5.-
0
5.
0.1
5.1
C 2FN
nuR
83
572
666
gifnoC
T-SL-NS
T-SS-NS
T-S on-NS
hcaM
63.2
63.2
63.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
0.0
δ2
0.0
0.0
0.0
δ3
0.0
0.0
0.0
δ4
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 2MH
82 42 02 61 21 8 4 0 4-α, deg
6.-
4.-
2.-
0
2.
4.
6.
C 2MB
(d) Tail fin 2 loads.
Figure 24. Continued.
74
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 3FN
nuR
83
572
666
gifnoC
T-SL-NS
T-SS-NS
T-S on-NS
hcaM
63.2
63.2
63.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
0.0
δ2
0.0
0.0
0.0
δ3
0.0
0.0
0.0
δ4
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 3MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 3MB
α, deg α, deg
(e) Tail fin 3 loads.
Figure 24. Continued.
75
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 4FN
nuR
83
572
666
gifnoC
T-SL-NS
T-SS-NS
T-S on-NS
hcaM
63.2
63.2
63.2
φ
0.0
0.0
0.0
δ1
0.0
0.0
0.0
δ2
0.0
0.0
0.0
δ3
0.0
0.0
0.0
δ4
0.0
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
0/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 4MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 4MB
α, deg α, deg
(f) Tail fin 4 loads.
Figure 24. Concluded.
76
82 42 02 61 21 8 4 0 4-2-
0
2
4
6
8
01
C FN
nuR
59
69
79
89
99
001
101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-02-
51-
01-
5-
0
5
01
51
C MP
α, deg α, deg
(a) Configuration longitudinal loads.
Figure 25. Effects of 2-fin pitch control deflections.
77
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
59
69
79
89
99
001
101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
21-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 25. Continued.
78
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 1FN
nuR
59
69
79
89
99
001
101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
51.-
01.-
50.-
0
50.
01.
51.
C 1MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 1MB
α, deg α, deg
(c) Tail fin 1 loads.
Figure 25. Continued.
79
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 2FN
nuR
59
69
79
89
99
001
101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
51.-
01.-
50.-
0
50.
01.
51.
C 2MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 2MB
α, deg α, deg
(d) Tail fin 2 loads.
Figure 25. Continued.
80
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 3FN
nuR
59
69
79
89
99
001
101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
51.-
01.-
50.-
0
50.
01.
51.
C 3MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 3MB
α, deg α, deg
(e) Tail fin 3 loads.
Figure 25. Continued.
81
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 4FN
nuR
59
69
79
89
99
001
101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.0
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
51.-
01.-
50.-
0
50.
01.
51.
C 4MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 4MB
α, deg α, deg
(f) Tail fin 4 loads.
Figure 25. Concluded.
82
82 42 02 61 21 8 4 0 4-2-
0
2
4
6
8
01
C FN
nuR
5611
0711
1711
2711
7611
8611
9611
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
06.0
06.0
06.0
06.0
06.0
06.0
φ
0.54-
0.54-
0.54-
0.54-
0.54-
0.54-
0.54-
δ1
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-02-
51-
01-
5-
0
5
01
51
C MP
α, deg α, deg
(a) Configuration longitudinal loads.
Figure 26. Effects of 4-fin pitch control deflections.
83
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
5611
0711
1711
2711
7611
8611
9611
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
06.0
06.0
06.0
06.0
06.0
06.0
φ
0.54-
0.54-
0.54-
0.54-
0.54-
0.54-
0.54-
δ1
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
21-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 26. Continued.
84
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 1FN
nuR
5611
0711
1711
2711
7611
8611
9611
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
06.0
06.0
06.0
06.0
06.0
06.0
φ
0.54-
0.54-
0.54-
0.54-
0.54-
0.54-
0.54-
δ1
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
51.-
01.-
50.-
0
50.
01.
51.
C 1MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 1MB
α, deg α, deg
(c) Tail fin 1 loads.
Figure 26. Continued.
85
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 2FN
nuR
5611
0711
1711
2711
7611
8611
9611
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
06.0
06.0
06.0
06.0
06.0
06.0
φ
0.54-
0.54-
0.54-
0.54-
0.54-
0.54-
0.54-
δ1
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
51.-
01.-
50.-
0
50.
01.
51.
C 2MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 2MB
α, deg α, deg
(d) Tail fin 2 loads.
Figure 26. Continued.
86
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 3FN
nuR
5611
0711
1711
2711
7611
8611
9611
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
06.0
06.0
06.0
06.0
06.0
06.0
06.0
φ
0.54-
0.54-
0.54-
0.54-
0.54-
0.54-
0.54-
δ1
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δ2
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ3
0.0
0.01
0.02
0.03
0.01-
0.02-
0.03-
δ4
0.0
0.01-
0.02-
0.03-
0.01
0.02
0.03
δP/δY/δR
0/0/0
0/0/01
0/0/02
0/0/03
0/0/01-
0/0/02-
0/0/03-
51.-
01.-
50.-
0
50.
01.
51.
C 3MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 3MB
α, deg α, deg
(e) Tail fin 3 loads.
Figure 26. Concluded.
87
82 42 02 61 21 8 4 0 4-2-
0
2
4
6
8
01
C FN
nuR
2111
0211
3211
4111
7111
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
91.1
91.1
91.1
81.1
81.1
φ
0.09-
0.09-
0.09-
0.09-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01-
0.02-
0.01
0.02
δ3
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01
0.02
0.01-
0.02-
δP/δY/δR
0/0/0
0/01/0
0/02/0
0/01-/0
0/02-/0
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-02-
51-
01-
5-
0
5
01
51
C MP
α, deg α, deg
(a) Configuration longitudinal loads.
Figure 27. Effects of yaw control deflections.
88
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
2111
0211
3211
4111
7111
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
91.1
91.1
91.1
81.1
81.1
φ
0.09-
0.09-
0.09-
0.09-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01-
0.02-
0.01
0.02
δ3
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01
0.02
0.01-
0.02-
δP/δY/δR
0/0/0
0/01/0
0/02/0
0/01-/0
0/02-/0
21-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 27. Continued.
89
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 1FN
nuR
2111
0211
3211
4111
7111
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
91.1
91.1
91.1
81.1
81.1
φ
0.09-
0.09-
0.09-
0.09-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01-
0.02-
0.01
0.02
δ3
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01
0.02
0.01-
0.02-
δP/δY/δR
0/0/0
0/01/0
0/02/0
0/01-/0
0/02-/0
51.-
01.-
50.-
0
50.
01.
51.
C 1MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 1MB
α, deg α, deg
(c) Tail fin 1 loads.
Figure 27. Continued.
90
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 2FN
nuR
2111
0211
3211
4111
7111
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
91.1
91.1
91.1
81.1
81.1
φ
0.09-
0.09-
0.09-
0.09-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01-
0.02-
0.01
0.02
δ3
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01
0.02
0.01-
0.02-
δP/δY/δR
0/0/0
0/01/0
0/02/0
0/01-/0
0/02-/0
51.-
01.-
50.-
0
50.
01.
51.
C 2MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 2MB
α, deg α, deg
(d) Tail fin 2 loads.
Figure 27. Continued.
91
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 3FN
nuR
2111
0211
3211
4111
7111
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
91.1
91.1
91.1
81.1
81.1
φ
0.09-
0.09-
0.09-
0.09-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01-
0.02-
0.01
0.02
δ3
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01
0.02
0.01-
0.02-
δP/δY/δR
0/0/0
0/01/0
0/02/0
0/01-/0
0/02-/0
51.-
01.-
50.-
0
50.
01.
51.
C 3MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 3MB
α, deg α, deg
(e) Tail fin 3 loads.
Figure 27. Continued.
92
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 4FN
nuR
2111
0211
3211
4111
7111
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
91.1
91.1
91.1
81.1
81.1
φ
0.09-
0.09-
0.09-
0.09-
0.09-
δ1
0.0
0.0
0.0
0.0
0.0
δ2
0.0
0.01-
0.02-
0.01
0.02
δ3
0.0
0.0
0.0
0.0
0.0
δ4
0.0
0.01
0.02
0.01-
0.02-
δP/δY/δR
0/0/0
0/01/0
0/02/0
0/01-/0
0/02-/0
51.-
01.-
50.-
0
50.
01.
51.
C 4MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 4MB
α, deg α, deg
(f) Tail fin 4 loads.
Figure 27. Concluded.
93
82 42 02 61 21 8 4 0 4-2-
0
2
4
6
8
01
C FN
nuR
59
601
401
29
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
δ1
0.0
0.01-
0.02-
0.03-
δ2
0.0
0.01
0.02
0.03
δ3
0.0
0.01
0.02
0.03
δ4
0.0
0.01-
0.02-
0.03-
δP/δY/δR
0/0/0
0/01/01
0/02/02
0/03/03
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-02-
51-
01-
5-
0
5
01
51
C MP
α, deg α, deg
(a) Configuration longitudinal loads.
Figure 28. Effects of pitch-yaw control deflections.
94
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
59
601
401
29
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
δ1
0.0
0.01-
0.02-
0.03-
δ2
0.0
0.01
0.02
0.03
δ3
0.0
0.01
0.02
0.03
δ4
0.0
0.01-
0.02-
0.03-
δP/δY/δR
0/0/0
0/01/01
0/02/02
0/03/03
21-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 28. Continued.
95
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 1FN
nuR
59
601
401
29
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
δ1
0.0
0.01-
0.02-
0.03-
δ2
0.0
0.01
0.02
0.03
δ3
0.0
0.01
0.02
0.03
δ4
0.0
0.01-
0.02-
0.03-
δP/δY/δR
0/0/0
0/01/01
0/02/02
0/03/03
51.-
01.-
50.-
0
50.
01.
51.
C 1MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 1MB
α, deg α, deg
(c) Tail fin 1 loads.
Figure 28. Continued.
96
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 2FN
nuR
59
601
401
29
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
δ1
0.0
0.01-
0.02-
0.03-
δ2
0.0
0.01
0.02
0.03
δ3
0.0
0.01
0.02
0.03
δ4
0.0
0.01-
0.02-
0.03-
δP/δY/δR
0/0/0
0/01/01
0/02/02
0/03/03
51.-
01.-
50.-
0
50.
01.
51.
C 2MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 2MB
α, deg α, deg
(d) Tail fin 2 loads.
Figure 28. Continued.
97
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 3FN
nuR
59
601
401
29
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
δ1
0.0
0.01-
0.02-
0.03-
δ2
0.0
0.01
0.02
0.03
δ3
0.0
0.01
0.02
0.03
δ4
0.0
0.01-
0.02-
0.03-
δP/δY/δR
0/0/0
0/01/01
0/02/02
0/03/03
51.-
01.-
50.-
0
50.
01.
51.
C 3MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 3MB
α, deg α, deg
(e) Tail fin 3 loads.
Figure 28. Continued.
98
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 4FN
nuR
59
601
401
29
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
68.2
68.2
68.2
68.2
φ
0.0
0.0
0.0
0.0
δ1
0.0
0.01-
0.02-
0.03-
δ2
0.0
0.01
0.02
0.03
δ3
0.0
0.01
0.02
0.03
δ4
0.0
0.01-
0.02-
0.03-
δP/δY/δR
0/0/0
0/01/01
0/02/02
0/03/03
51.-
01.-
50.-
0
50.
01.
51.
C 4MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 4MB
α, deg α, deg
(f) Tail fin 4 loads.
Figure 28. Concluded.
99
82 42 02 61 21 8 4 0 4-2-
0
2
4
6
8
01
C FN
nuR
5001
6001
5101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
81.1
81.1
91.1
φ
0.0
0.0
0.0
δ1
0.0
0.5
0.01
δ2
0.0
0.5
0.01
δ3
0.0
0.5
0.01
δ4
0.0
0.5
0.01
δP/δY/δR
0/0/0
5/0/0
01/0/0
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-02-
51-
01-
5-
0
5
01
51
C MP
α, deg α, deg
(a) Configuration longitudinal loads.
Figure 29. Effects of roll control deflections.
100
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
5001
6001
5101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
81.1
81.1
91.1
φ
0.0
0.0
0.0
δ1
0.0
0.5
0.01
δ2
0.0
0.5
0.01
δ3
0.0
0.5
0.01
δ4
0.0
0.5
0.01
δP/δY/δR
0/0/0
5/0/0
01/0/0
21-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 29. Continued.
101
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 1FN
nuR
5001
6001
5101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
81.1
81.1
91.1
φ
0.0
0.0
0.0
δ1
0.0
0.5
0.01
δ2
0.0
0.5
0.01
δ3
0.0
0.5
0.01
δ4
0.0
0.5
0.01
δP/δY/δR
0/0/0
5/0/0
01/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 1MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 1MB
α, deg α, deg
(c) Tail fin 1 loads.
Figure 29. Continued.
102
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 2FN
nuR
5001
6001
5101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
81.1
81.1
91.1
φ
0.0
0.0
0.0
δ1
0.0
0.5
0.01
δ2
0.0
0.5
0.01
δ3
0.0
0.5
0.01
δ4
0.0
0.5
0.01
δP/δY/δR
0/0/0
5/0/0
01/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 2MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 2MB
α, deg α, deg
(d) Tail fin 2 loads.
Figure 29. Continued.
103
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 3FN
nuR
5001
6001
5101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
81.1
81.1
91.1
φ
0.0
0.0
0.0
δ1
0.0
0.5
0.01
δ2
0.0
0.5
0.01
δ3
0.0
0.5
0.01
δ4
0.0
0.5
0.01
δP/δY/δR
0/0/0
5/0/0
01/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 3MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 3MB
α, deg α, deg
(e) Tail fin 3 loads.
Figure 29. Continued
104
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 4FN
nuR
5001
6001
5101
gifnoC
T-SL-NS
T-SL-NS
T-SL-NS
hcaM
81.1
81.1
91.1
φ
0.0
0.0
0.0
δ1
0.0
0.5
0.01
δ2
0.0
0.5
0.01
δ3
0.0
0.5
0.01
δ4
0.0
0.5
0.01
δP/δY/δR
0/0/0
5/0/0
01/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 4MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 4MB
α, deg α, deg
(f) Tail fin 4 loads.
Figure 29. Concluded.
105
82 42 02 61 21 8 4 0 4-2-
0
2
4
6
8
01
C FN
nuR
585
317
gifnoC
T-SS-NS
T-SS-NL
hcaM
07.1
57.1
φ
0.0
0.0
δ1
0.0
0.0
δ2
0.0
0.0
δ3
0.0
0.0
δ4
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
4.-
0
4.
8.
2.1
6.1
0.2
C FA
82 42 02 61 21 8 4 0 4-02-
51-
01-
5-
0
5
01
51
C MP
α, deg α, deg
(a) Configuration longitudinal loads.
Figure 30. Effects of nose size.
106
82 42 02 61 21 8 4 0 4-2.1-
8.-
4.-
0
4.
8.
2.1
C MR
nuR
585
317
gifnoC
T-SS-NS
T-SS-NL
hcaM
07.1
57.1
φ
0.0
0.0
δ1
0.0
0.0
δ2
0.0
0.0
δ3
0.0
0.0
δ4
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
21-
8-
4-
0
4
8
21
C MY
82 42 02 61 21 8 4 0 4-3-
2-
1-
0
1
2
3
C FS
α, deg α, deg
(b) Configuration lateral-directional loads.
Figure 30. Continued.
107
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 1FN
nuR
585
317
gifnoC
T-SS-NS
T-SS-NL
hcaM
07.1
57.1
φ
0.0
0.0
δ1
0.0
0.0
δ2
0.0
0.0
δ3
0.0
0.0
δ4
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 1MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 1MB
α, deg α, deg
(c) Tail fin 1 loads.
Figure 30. Continued.
108
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 2FN
nuR
585
317
gifnoC
T-SS-NS
T-SS-NL
hcaM
07.1
57.1
φ
0.0
0.0
δ1
0.0
0.0
δ2
0.0
0.0
δ3
0.0
0.0
δ4
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 2MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 2MB
α, deg α, deg
(d) Tail fin 2 loads.
Figure 30. Continued.
109
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 3FN
nuR
585
317
gifnoC
T-SS-NS
T-SS-NL
hcaM
07.1
57.1
φ
0.0
0.0
δ1
0.0
0.0
δ2
0.0
0.0
δ3
0.0
0.0
δ4
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 3MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 3MB
α, deg α, deg
(e) Tail fin 3 loads.
Figure 30. Continued.
110
82 42 02 61 21 8 4 0 4-5.1-
0.1-
5.-
0
5.
0.1
5.1
C 4FN
nuR
585
317
gifnoC
T-SS-NS
T-SS-NL
hcaM
07.1
57.1
φ
0.0
0.0
δ1
0.0
0.0
δ2
0.0
0.0
δ3
0.0
0.0
δ4
0.0
0.0
δP/δY/δR
0/0/0
0/0/0
51.-
01.-
50.-
0
50.
01.
51.
C 4MH
82 42 02 61 21 8 4 0 4-6.-
4.-
2.-
0
2.
4.
6.
C 4MB
α, deg α, deg
(f) Tail fin 4 loads.
Figure 30. Concluded.
REPORT DOCUMENTATION PAGE Form ApprovedOMB No. 0704-0188
2. REPORT TYPE
Technical Memorandum 4. TITLE AND SUBTITLE
Aerodynamics of an Axisymmetric Missile Concept Having Cruciform Strakes and In-Line Tail Fins From Mach 0.60 to 4.63
5a. CONTRACT NUMBER
6. AUTHOR(S)
Allen, Jerry M.
7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)
NASA Langley Research CenterHampton, VA 23681-2199
9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)
National Aeronautics and Space AdministrationWashington, DC 20546-0001
8. PERFORMING ORGANIZATION REPORT NUMBER
L-19027
10. SPONSOR/MONITOR'S ACRONYM(S)
NASA
13. SUPPLEMENTARY NOTESAllen, Langley Research Center, Hampton, VA.An electronic version can be found at http://ntrs.nasa.govA CD-ROM supplement for TM-2005-213541 is available upon request.
12. DISTRIBUTION/AVAILABILITY STATEMENTUnclassified - UnlimitedSubject Category 02Availability: NASA CASI (301) 621-0390
An experimental study has been performed to develop a large force and moment aerodynamic data set on a slender axisymmetric missile configuration having cruciform strakes and in-line control tail fins. The data include six-component balance measurements of the configuration aerodynamics and three-component measurements on all four tail fins. The test variables include angle of attack, roll angle, Mach number, model buildup, strake length, nose size, and tail fin deflection angles to provide pitch, yaw, and roll control. Test Mach numbers ranged from 0.60 to 4.63. The entire data set is presented on a CD-ROM that is attached to this paper. The CD-ROM also includes extensive plots of both the six-component configuration data and the three-component tail fin data. Selected samples of these plots are presented in this paper to illustrate the features of the data and to investigate the effects of the test variables.
15. SUBJECT TERMS
Experimental aerodynamics; Missile control fins; Wind tunnel tests; Subsonic/Transonic; Supersonic
18. NUMBER OF PAGES
115
19b. TELEPHONE NUMBER (Include area code)
(301) 621-0390
a. REPORT
U
c. THIS PAGE
U
b. ABSTRACT
U
17. LIMITATION OF ABSTRACT
UU
Prescribed by ANSI Std. Z39.18Standard Form 298 (Rev. 8-98)
3. DATES COVERED (From - To)
5b. GRANT NUMBER
5c. PROGRAM ELEMENT NUMBER
5d. PROJECT NUMBER
5e. TASK NUMBER
5f. WORK UNIT NUMBER
23-090-20-35
11. SPONSOR/MONITOR'S REPORT NUMBER(S)
NASA/TM-2005-213541
16. SECURITY CLASSIFICATION OF:
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