NAZCA-TR-22-001
渦格子法プログラム「AVL」の使い方
滝敏美

2021/03/03
1.

目的
模型グライダーの運動を解析するには機体の空力微係数を計算する必要がある．渦格子法（Vortex Lattice Method）を用いると機体の空力微係数を正確に計算することができる．本資料では，MIT が公開している渦格子法プログラム「AVL」を使って機体の空力微係数を計算する方法を示す．
目次
1.

目的........................................................................................................................................... 12.

参考資料................................................................................................................................... 1

3.

成果........................................................................................................................................... 1

4.

AVL ........................................................................................................................................... 2

5.

AVL の使い方 .......................................................................................................................... 2

5.1

モデル化................................................................................................................................... 2

5.2モデルの例............................................................................................................................... 2

5.3

AVL の実行 ............................................................................................................................ 145.4

計算結果のまとめ................................................................................................................. 24

2.

参考資料

[1] M. Drela and H. Youngren, “AVL 3.36 User Primer,” 2012.
[2] K. Budziak, “Aerodynamic Analysis with Athena Vortex Lattice (AVL),” Hamburg University ofApplied Sciences, 2015.
[3] NAZCA-TR-20-012「T-4 フリーフライト模型グライダーの設計」
3.

成果
T-4 グライダー（参考資料[2]）を例にとって「AVL」を使った空力微係数の計算方法を示した．


胴体もモデル化し，胴体の影響を考慮した横の空力微係数も計算できた．



主翼の翼型として，平板とした場会とゲッチンゲン 417a とした場合の２つのケースについて計算した．

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4.

AVL
「AVL」は MIT が開発し，公開している航空機の空気力を渦格子法で計算するプログラム

である．非粘性，非圧縮性を仮定している．
5.

AVL の使い方

5.1 モデル化翼
スパン方向に台形のパネルをつないで翼の平面形をモデル化する．翼型を上面と下面の座標で与える．計算には翼型の中心線の値が使用される．翼型のデータを入力しない場合には平板翼となる．


胴体
胴体の側面形を平板でモデル化する．すべての翼と胴体をつながったものとしてモデル化

する．
5.2 モデルの例
T-4 グライダーの三面図を図 5-1 に示す．
重心位置は主翼の前縁から 75 mm 後ろ（35% MAC）
である．主翼と水平尾翼の面積と平均空力翼弦の計算を表 5-1 に示す．
主翼の翼型は，平板翼の場合とゲッチンゲン 417a 翼の場合の２ケースを考える．水平尾翼と垂直尾翼は平板翼とする．
主翼と尾翼の上反角は 0 度とする．主翼の取付角は 0 度とする．水平尾翼の取付角は，平板主翼の場合-3 度，ゲッチンゲン 417a 翼型主翼の場合 xx 度とする．
胴体は平板である（図 5-2）
．胴体の AVL モデルは，STA 148 で前後に，WL-16 で上下に分割して４つのパネルで表す（図 5-3）．
T-4 グライダーの AVL モデルを図 5-4，図 5-5 に示す．主翼と水平尾翼の AVL モデル詳細を図 5-6 に，胴体と垂直尾翼の AVL モデル詳細を図 5-7 に示す．モデルのデータとその説明
を表 5-2 に示す．

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単位：mm
図 5-1 T-4 グライダーの三面図

図 5-2 T-4 グライダーの胴体形状

3/24

表 5-1 主翼と水平尾翼の面積と平均空力翼弦の計算
主翼
翼幅

b

432 mm

半翼幅b/2

216 mm

翼弦長，翼根c_r

120 mm

翼弦長，翼端c_t

54 mm

翼端の後退長e_t

テーパー比

lambda

翼面積

S

アスペクト比AR4.965517

平均空力翼弦c_bar

91.17241 mm

平均空力翼弦の位置

y_bar

94.34483 mm

e_bar

43.24138 mm

後退角

 一般の翼の場合：翼面積：平均空力翼弦

99 mm

1/4 c

0.45
37584 mm^2

 テーパー翼の場合：テーパー比LAMBDA 0.364845 radian
LAMBDA 20.90408 degree

水平尾翼
翼幅

b

174 mm

半翼幅

b/2

87 mm

翼弦長，翼根c_r

72 mm

翼弦長，翼端c_t

36 mm

翼端の後退長

e_t

48 mm

テーパー比

lambda

0.5

翼面積

S_h

アスペクト比AR

平均空力翼弦

c_bar

56 mm

平均空力翼弦の位置

y_bar

38.66667 mm

e_bar

21.33333 mm

後退角

1/2 c

：後退角 L9396 mm^23.222222

LAMBDA 0.421419 radian
LAMBDA 24.14554 degree

図 5-3 胴体パネル
4/24

図 5-4 T-4 グライダーの AVL モデル – 平板主翼とゲッチンゲン 417a 主翼

図 5-5 T-4 グライダーの AVL モデル

5/24

図 5-6 主翼と水平尾翼の AVL モデル詳細

図 5-7 垂直尾翼と胴体の AVL モデル詳細

6/24

表 5-2 AVL 入力データファイルの例，T-4_new.avl
データの名称
T-4, Flat Wing
#Mach「#」はコメント行で無視される
0.0#IYsym IZsym Zsym
釣り合い計算をしないので，慣性データは無視
0
0
0.0
#Sref
Cref
Bref
主翼面積，平均空力翼弦，翼幅37584.0 91.0
432.0
#Xref
Yref
Zref
75.0
0.0
-9.0
力，モーメントの基準点（この場合は重心位置）
#CDp
0.060
形状抵抗
#
#
#====================================================================SURFACE
主翼
Wing
パネル分割
#Nchordwise Cspace Nspanwise Sspace
8
1.0
16
1.0
#
COMPONENT
他の面とつなぐ1#
YDUPLICATEy = 0 の面に対称0.0
断面位置（前縁の座標）とそ#の長さ（翼弦長）
，ねじれ角
ANGLE
取付角
0.0
#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
0.
0.
0.0
120.0 0.0 00##------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
99.0
216.0 0.0
54.0
0.0 0
0
#
#====================================================================
水平尾翼
SURFACE
H-stab
#Nchordwise Cspace Nspanwise Sspace
6
1.0
10
1.0
#
7/24

胴体とつながっている
COMPONENT1#YDUPLICATE
0.0#
オフセットの量
TRANSLATE
250.0 0.0 -16.0
#
ANGLE
取付角
-3.0
#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
0.0
0.0
0.0
72.0
0.0 0
0
#
#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
48.0
87.0 0.0
36.0
0.0 0
0
#
#====================================================================SURFACE
垂直尾翼
V-stab
#Nchordwise Cspace Nspanwise Sspace
6
1.0
12
1.0
#
胴体とつながっている
COMPONENT
1#
TRANSLATE
0.0 0.0 0.0
#
ANGLE
0.0
#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
148.0 0.0
5.0
145.0 0.0 00##------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
225.0 0.0
21.0
73.0
0.0 0
0
#
SECTION
8/24

#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
280.0 0.0
84.0
36.0
0.0 0
0
#
#====================================================================SURFACE
胴体前部上側Fuselage-upper,forward#Nchordwise Cspace Nspanwise Sspace
12
1.0
8
1.0
#
主翼，尾翼とつながっている
COMPONENT
1#
TRANSLATE
0.0 0.0 0.0
#
ANGLE
0.0
#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace-115.0 0.0 -16.0 263.0 0.0 00#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace-85.0 0.0
0.0
233.0 0.0 00#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace-74.0 0.0
5.0
222.0 0.0 00#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace-60.0 0.0
10.0
110.0 0.0 00#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace-30.0 0.0
17.0
35.0
0.0 0
0
#------------------------------------------------------------#====================================================================SURFACE
胴体後部上側Fuselage-upper,aftward#Nchordwise Cspace Nspanwise Sspace
12
1.0
6
1.0
#
主翼，尾翼とつながっている
COMPONENT
1
9/24

#
TRANSLATE
0.0 0.0 0.0
#
ANGLE
0.0
#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
148.0 0.0
-16.0 174.0 0.0 00#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
148.0 0.0
0.0
148.0 0.0 00#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
148.0 0.0
5.0
144.0 0.0 00#====================================================================#====================================================================SURFACE
胴体前部下側Fuselage-lower,forward#Nchordwise Cspace Nspanwise Sspace
12
1.0
6
1.0
#
COMPONENT
主翼，尾翼とつながっている
1#
TRANSLATE
0.0 0.0 0.0
#
ANGLE
0.0
#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace-115.0 0.0 -16.0 263.0 0.0 00#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace-164.0 0.0-26.0 312.0 0.0 00#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace-180.0 0.0-38.0 328.0 0.0 00#------------------------------------------------------------10/24

SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace-160.0 0.0-52.0 308.0 0.0 00#------------------------------------------------------------#====================================================================SURFACE胴体後部下側Fuselage-Lower,aftward#Nchordwise Cspace Nspanwise Sspace
12
1.0
6
1.0
#
COMPONENT
主翼，尾翼とつながっている
1#
TRANSLATE
0.0 0.0 0.0
#
ANGLE
0.0
#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
148.0 0.0
-16.0 176.0 0.0 00#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
148.0 0.0
-26.0 146.0 0.0 00#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
148.0 0.0
-38.0 96.0
0.0 00#====================================================================SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
148.0 0.0
-52.0 66.0
0.0 00#====================================================================

主翼の翼型がゲッチンゲン 417a の場合の主翼のデータを以下に示す．
#====================================================================SURFACE
Wing#Nchordwise Cspace Nspanwise Sspace
8
1.0
16
1.0
#
COMPONENT
11/24

1
#
YDUPLICATE
0.0
#
ANGLE
0.0
#------------------------------------------------------------SECTION
#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
0.
0.
0.0
120.0 0.0 0
0#
AIRFOIL1.00.0
後縁→上面の座標値→前縁→
0.9
0.024
下面の座標値→後縁
0.8
0.04250.7
0.0545
0.6
0.064
0.5
0.07
0.4
0.07350.3
0.07150.2
0.063
0.15 0.057
0.1
0.04850.075 0.0415
0.05 0.0325
0.025 0.022
0.0125 0.0155
0.0
0.0
0.0125 -0.014
0.025 -0.01
0.05
0.001
0.075 0.0105
0.1
0.01850.15
0.0275
0.2
0.034
0.3
0.04250.4
0.0445
0.5
0.041
0.6
0.035
0.7
0.02550.8
0.01350.9-0.00151.0
0.0#------------------------------------------------------------SECTION
12/24

#Xle
Yle
Zle
Chord Ainc Nspanwise Sspace
99.0
216.0 0.0
54.0
0.0 0
0
#
AIRFOIL
1.0
0.0
0.9
0.024
0.8
0.04250.7
0.0545
0.6
0.064
0.5
0.07
0.4
0.07350.3
0.07150.2
0.063
0.15 0.057
0.1
0.04850.075 0.0415
0.05 0.0325
0.025 0.022
0.0125 0.0155
0.0
0.0
0.0125 -0.014
0.025 -0.01
0.05
0.001
0.075 0.0105
0.1
0.01850.15
0.0275
0.2
0.034
0.3
0.04250.4
0.0445
0.5
0.041
0.6
0.035
0.7
0.02550.8
0.01350.9-0.00151.0
0.0#====================================================================

13/24

5.3 AVL の実行
AVL の実行例を表 5-3 に示す．

14/24

表 5-3 AVL の実行例

実行ファイル avl.exe と入力データファイル T-4_new.avl を同じフォルダーに入れておく．
avl.exe を実行すると，===================================================
Athena Vortex Lattice Program
Version 3.37
Copyright (C) 2002 Mark Drela, Harold Youngren
This software comes with ABSOLUTELY NO WARRANTY,
subject to the GNU General Public License.
Caveat computor=============================================================================================================
Quit
Exit program
.OPER
.MODE
.TIME

Compute operating-point run cases
Eigenvalue analysis of run cases
Time-domain calculations

LOAD f Read configuration input file
MASS f Read mass distribution file
CASE f Read run case file
CINI
Clear and initialize run cases
MSET i Apply mass file data to stored run case(s).PLOP
Plotting options
NAME s Specify new configuration nameAVLc> load T-4_new.avl

Reading file: T-4_new.avl

データファイル名を入力...

Configuration: T-4, Flat Wing
Building surface: Wing
Building duplicate image-surface: Wing (YDUP)

15/24

Building surface: H-stab
Building duplicate image-surface: H-stab (YDUP)
Building surface: V-stab
Building surface: Fuselage-upper,forward
Building surface: Fuselage-upper,aftward
Building surface: Fuselage-lower,forward
Building surface: Fuselage-Lower,aftward
Mach =

0.0000 (default)

0 Bodies
9 Solid surfaces
90 Strips
760 Vortices
0 Control variables
0 Design parameters
Initializing run cases...
AVL

解析を始めるc> oper

Operation of run case 1/1: -unnamed==========================================================
variable-----------A lpha
B eta
R oll rate
P itch rate
Y aw rate------------

->
->
->
->
->

constraint-----------------------alpha
=
0.000
beta
=
0.000
pb/2V
=
0.000
qc/2V
=
0.000
rb/2V
=
0.000
------------------------

C1 set level or banked horizontal flight constraints
C2 set steady pitch rate (looping) flight constraints
M odify parameters"#" select run case+ add new run case

L ist defined run cases
S ave run cases to file
16/24

- delete run caseN ame current run case

F etch run cases from file
W rite forces to fileeX ecute run case

I nitialize variables

G eometry plot

T refftz Plane plot

ST stability derivatives
SB body-axis derivatives
RE reference quantities
DE design changes
O ptions

FT
FN
FS
FE
FB
HM
VM

.OPER (case 1/1)

total forces
surface forces
strip forces
element forces
body forces
hinge moments
strip shear,momentc> g

モデル図の作成=========================================
K eystroke mode
V iewpoint
A nnotate plot
O ptions
H ardcopy plot
S elect surfaces
Z oom
U nzoom
CH ordline
CN tlpoint
BO ound leg
LO ading

TF
TF

CA amberF
TR ailing legs F
NO rmal vector F
AX es, xyz ref. T

Geometry plot command: v

モデル図の角度の変更

Enter viewpoint azimuth,elevation angles:-90 0
X-window size changed to 11.00" x 8.06"=========================================
K eystroke mode
V iewpoint
A nnotate plot
O ptions
H ardcopy plot
S elect surfaces
Z oom
U nzoom
CH ordline
CN tlpoint
BO ound leg
LO ading

TF
TF

CA amberF
TR ailing legs F
NO rmal vector F
AX es, xyz ref. T

17/24

-45.

20.

モデル図の新しい角度の入力
側面図

Geometry plot command: ca

モデル図にキャンバーを描く=========================================
K eystroke mode
V iewpoint
A nnotate plot
O ptions
H ardcopy plot
S elect surfaces
Z oom
U nzoom
CH ordline
CN tlpoint
BO ound leg
LO ading

TF
TF

CA amberT
TR ailing legs F
NO rmal vector F
AX es, xyz ref. T
モデル図の作成メニューから出る

Geometry plot command: リターンキー

Operation of run case 1/1: -unnamed==========================================================
variable-----------A lpha
B eta
R oll rate
P itch rate
Y aw rate------------

->
->
->
->
->

constraint-----------------------alpha
=
0.000
beta
=
0.000
pb/2V
=
0.000
qc/2V
=
0.000
rb/2V
=
0.000
------------------------

C1 set level or banked horizontal flight constraints
C2 set steady pitch rate (looping) flight constraints
M odify parameters"#" select run case+ add new run case- delete run caseN ame current run case

L ist defined run cases
S ave run cases to file
F etch run cases from file
W rite forces to fileeX ecute run case

I nitialize variables

G eometry plot

T refftz Plane plot

ST stability derivatives
SB body-axis derivatives
RE reference quantities
DE design changes
O ptions

FT
FN
FS
FE
FB
HM

total forces
surface forces
strip forces
element forces
body forces
hinge moments
18/24

VM
.OPER (case 1/1)

strip shear,moment
迎角を未知数とする

c> a

constraintvalue- - - - - - - - - - - - - - - - -> A
alpha
= 0.000Bbeta= 0.000
R
pb/2V= 0.000P
qc/2V= 0.000Y
rb/2V= 0.000
CCL= 0.000
S
CY= 0.000
RM Cl roll mom = 0.000
PM Cm pitchmom = 0.000
YM Cn yaw mom = 0.000
Select new

揚力係数 CL を拘束値とする

constraint,value for alphaEnter specified CL
0.6

:

c> c

0.000
揚力係数の値を入力する

Operation of run case 1/1: -unnamed==========================================================
variable-----------A lpha
B eta
R oll rate
P itch rate
Y aw rate------------

->
->
->
->
->

constraint-----------------------CL= 0.6000
beta
=
0.000
pb/2V
=
0.000
qc/2V
=
0.000
rb/2V
=
0.000
------------------------

C1 set level or banked horizontal flight constraints
C2 set steady pitch rate (looping) flight constraints
M odify parameters"#" select run case+ add new run case- delete run caseN ame current run case

L ist defined run cases
S ave run cases to file
F etch run cases from file
W rite forces to fileeX ecute run case

I nitialize variables

G eometry plot

T refftz Plane plot
19/24

ST stability derivatives
SB body-axis derivatives
RE reference quantities
DE design changes
O ptions

FT
FN
FS
FE
FB
HM
VM

total forces
surface forces
strip forces
element forces
body forces
hinge moments
strip shear,moment.OPER (case 1/1)c> x計算を実行する
Building normalwash AIC matrix...
Factoring normalwash AIC matrix...
Building source+doublet strength AIC matrix...
Building source+doublet velocity AIC matrix...
Building bound-vortex velocity matrix...
iter d(alpha) d(beta)d(pb/2V) d(qc/2V)d(rb/2V)
1 0.836E+01 -0.000E+00 -0.000E+00 -0.000E+00 0.000E+00
2 0.750E-01 -0.000E+00 -0.000E+00 -0.000E+00 0.000E+00
3 0.206E-04 -0.000E+00 -0.000E+00 -0.000E+00 0.000E+00--------------------------------------------------------------Vortex Lattice Output -- Total Forces
ここから計算結果
Configuration: T-4, Flat Wing
# Surfaces =9# Strips = 90
# Vortices = 760
Sref = 37584.
Xref = 75.000

Cref = 91.000
Yref = 0.0000

Bref = 432.00
Zref = -9.0000

Standard axis orientation, X fwd, Z down
Run case: -unnamedAlpha =Beta =
Mach =

8.43358
0.00000
0.000

pb/2V = -0.00000
qc/2V = 0.00000
rb/2V = -0.00000

p'b/2V =-0.00000

r'b/2V =-0.00000

CXtot = 0.00357
CYtot = -0.00002
CZtot = -0.60603

Cltot = -0.00000
Cmtot = 0.00956
Cntot = 0.00002

Cl'tot =0.00000

Cn'tot =0.00002

CLtot =
CDtot =
CDvis =

CDind = 0.0253468

0.60000
0.08535
0.06000

20/24

CLff
CYff

=
=

0.603850.00000

CDff= 0.0234063
e =0.9987| Trefftz| Plane--------------------------------------------------------------Operation of run case 1/1: -unnamed==========================================================
variable-----------A lpha
B eta
R oll rate
P itch rate
Y aw rate------------

->
->
->
->
->

constraint-----------------------CL= 0.6000
beta
=
0.000
pb/2V
=
0.000
qc/2V
=
0.000
rb/2V
=
0.000
------------------------

C1 set level or banked horizontal flight constraints
C2 set steady pitch rate (looping) flight constraints
M odify parameters"#" select run case+ add new run case- delete run caseN ame current run case

L ist defined run cases
S ave run cases to file
F etch run cases from file
W rite forces to fileeX ecute run case

I nitialize variables

G eometry plot

T refftz Plane plot

ST stability derivatives
SB body-axis derivatives
RE reference quantities
DE design changes
O ptions

FT
FN
FS
FE
FB
HM
VM

.OPER (case 1/1)

total forces
surface forces
strip forces
element forces
body forces
hinge moments
strip shear,moment
空力微係数の計算

c> stEnter filename, or <return> for screen outputs> リターンキー--------------------------------------------------------------計算結果の画面表示
Vortex Lattice Output -- Total Forces
ここから計算結果

Configuration: T-4, Flat Wing
21/24

# Surfaces =9# Strips = 90
# Vortices = 760
Sref = 37584.
Xref = 75.000

Cref = 91.000
Yref = 0.0000

Bref = 432.00
Zref = -9.0000

Standard axis orientation, X fwd, Z down
Run case: -unnamedAlpha =Beta =
Mach =

8.43358
0.00000
0.000

pb/2V = -0.00000
qc/2V = 0.00000
rb/2V = -0.00000

p'b/2V =-0.00000

r'b/2V =-0.00000

CXtot = 0.00357
CYtot = -0.00002
CZtot = -0.60603

Cltot = -0.00000
Cmtot = 0.00956
Cntot = 0.00002

Cl'tot =0.00000

Cn'tot =0.00002

CLtot =
CDtot =
CDvis =
CLff =CYff =

CDind = 0.0253468
CDff = 0.0234063
e =0.99870.60000
0.08535
0.06000
0.603850.00000| Trefftz| Plane--------------------------------------------------------------Stability-axis derivatives...

z' force CL |y force CY |x' mom. Cl'|y mom. Cm |z' mom. Cn'|alpha---------------CLa = 4.303687
CYa = -0.000241
Cla = 0.000044
Cma = -0.630064
Cna = 0.000219

beta---------------CLb = -0.000018
CYb = -0.912051
Clb = -0.107165
Cmb = 0.000012
Cnb = 0.171093

z' force CL |y force CY |x' mom. Cl'|y mom. Cm |z' mom. Cn'|roll rate p'---------------CLp = -0.000027
CYp = 0.271661
Clp = -0.367850
Cmp = 0.000018
Cnp = -0.091606

pitch rate q'---------------CLq = 7.418351
CYq = -0.000069
Clq = 0.000008
Cmq = -9.889862
Cnq = 0.000067

22/24

yaw rate r'---------------CLr = 0.000002
CYr = 0.527129
Clr = 0.132098
Cmr = -0.000002
Cnr = -0.235210

Neutral point Xnp = 88.322487
Clb Cnr / Clr Cnb=

1.115278( > 1 if spirally stable )Operation of run case 1/1: -unnamed==========================================================
variable-----------A lpha
B eta
R oll rate
P itch rate
Y aw rate------------

->
->
->
->
->

constraint-----------------------CL= 0.6000
beta
=
0.000
pb/2V
=
0.000
qc/2V
=
0.000
rb/2V
=
0.000
------------------------

C1 set level or banked horizontal flight constraints
C2 set steady pitch rate (looping) flight constraints
M odify parameters"#" select run case+ add new run case- delete run caseN ame current run case

L ist defined run cases
S ave run cases to file
F etch run cases from file
W rite forces to fileeX ecute run case

I nitialize variables

G eometry plot

T refftz Plane plot

ST stability derivatives
SB body-axis derivatives
RE reference quantities
DE design changes
O ptions

FT
FN
FS
FE
FB
HM
VM

.OPER (case 1/1)
.AVL c> q

total forces
surface forces
strip forces
element forces
body forces
hinge moments
strip shear,momentc> リターンキー

メニューから出る

AVL を終了する

23/24

5.4 計算結果のまとめ
T-4 グライダー（平板主翼）の AVL 計算結果を表 5-4，図 5-8 に示す．釣り合い迎角は 9.30
度でそのときの揚力係数は 0.665 である．Cmは-0.635 である．

表 5-4 解析結果のまとめ，T-4 グライダー（平板主翼）
T-4 平板主翼
alpha

Cmtot

CLtot

CDtot

CLa

Cma

CYb

Clb

Cnb

CYp

Clp

Cnp

CLq

Cmq

CYr

Clr

Cnr

(degree)

Xnp
(mm)

5.79

0.03820.4

0.07144.37 -0.613 -0.903 -0.088 0.1591

0.174 -0.371 -0.0619

7.51 -10.0

0.548

0.098

-0.2346

87.8

7.11

0.02410.5

0.0776

4.34 -0.622 -0.908 -0.098 0.1649

0.223 -0.370 -0.0767

7.46

-9.9

0.539

0.115

-0.2350

88.0

8.43

0.00960.6

0.08544.30 -0.630 -0.912 -0.107 0.1711

0.272 -0.368 -0.0916

7.42

-9.9

0.527

0.132

-0.2352

88.3

9.30

0.00000.665

0.09114.28 -0.635 -0.915 -0.113 0.1754

0.303 -0.367 -0.1014

7.39

-9.9

0.518

0.143

-0.2353

88.5

9.77

-0.00520.7

0.0945

4.26 -0.637 -0.916 -0.116 0.1778

0.320 -0.366 -0.1067

7.37

-9.8

0.513

0.149

-0.2353

88.6

11.12

-0.02030.8

0.1051

4.21 -0.642 -0.919 j

0.18500.368 -0.364 -0.1219

7.31

-9.8

0.497

0.167

-0.2352

88.9

12.50

-0.0357

0.9

0.11724.15 -0.646 -0.922 -0.134 0.1928

0.416 -0.362 -0.1373

7.25

-9.7

0.478

0.184

-0.2349

89.2

13.89

-0.051510.13084.08 -0.648 -0.924 -0.142 0.2011

0.464 -0.359 -0.1529

7.19

-9.7

0.457

0.202

-0.2344

89.4

8

9

10

1.1

1

Cm
CL
CD

0.9

0.8

全機 CL，CD，
Cm

0.7

0.6

0.5

0.4

0.3

0.2

0.1

0
0

1

2

3

4

5

6

7

-0.1

-0.2

迎角  （度）図 5-8 T-4 平板主翼グライダーの縦の空力係数
24/24