1#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
2#
3# Aircraft:
4# 1903 Wright Flyer
5#
6# File name:
7# wrightFlyer1903-nl-v1
8#
9# ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
10#
11# Author:
12#
13# Michael Selig
14# http://www.aae.uiuc.edu/m-selig
15# 2002/02/27   initial setup
16# 2002/03/08   various refinements, focusing on the pitching moment behavior
17# 2002/12/21   more updates
18#              - additional wing hard points
19#              - adding in engine curve (model)
20#
21#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
22#
23# References:
24#
25#  - Culick, F.E.C. and Jex, H.R., "Aerodynamics, Stability and
26#    Control of the 1903 Wright Flyer," Proceedings of The Wright
27#    Flyer: An Engineering Perspective, National Air and Space Museum,
28#    Smithsonian Institution, 1985.
29#
30#  - Jex, H.R. and Culick, F.E.C., "Flight Control Dynamics of the
31#    1903 Wright Flyer," 12th AIAA Atmospheric Flight Mechanics
32#    Conference, AIAA Paper 85-1804-CP, 1985.
33#
34#  - Jex, H, Grimm, R., Latz, J.P., and Hange, C., "Full-Scale 1903
35#    Wright Flyer Wind Tunnel Test Results From the NASA Ames Research
36#    Center", AIAA 38th Aerospace Sciences Meeting, AIAA Paper
37#    2000-0512, 2000.
38#
39#  - Various other sources including
40#    http://www.wrightflyer.org/Papers/papers.html
41#    http://www.aae.uiuc.edu/m-selig/uiuc_lsat.html (low Re data)
42#
43#  - Additional models and updates
44#    http://www.aae.uiuc.edu/m-selig/apasim.html
45#
46#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
47#
48# Notes:
49# '[]' these items below still to do
50#
51#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
52
53# initializations
54init use_V_rel_wind_2U
55init use_dyn_on_speed_curve1
56init dyn_on_speed  2
57init dyn_on_speed_zero 1
58init use_Alpha_dot_on_speed 2   # [ft/sec] speed below which Alpha_dot is set to zero
59init use_gamma_horiz_on_speed 10 # [ft/sec] speed above which Gamma_horiz_deg is used in chase view [1]
60
61# geometry
62geometry bw   40.3      # [ft]
63geometry cbar  6.2      # [ft]
64geometry Sw  518        # [ft^2]
65
66# canard
67controlSurface de  20   20 # [deg]
68# wing warping (delta_w)
69controlSurface da 8.5  8.5 # [deg]
70# Per discussion w/ Fred Culick,
71# 11 inches up and 11 inch down movement is given on the Smithsonian plans.
72# With a 74-inch chord, this gives 8.5 deg up and 8.5 deg down of wing warping.
73# Rudder coupling of Flyer: coupling between wing warp and rudder is delta_r = 2.5 * delta_w
74# But w/ auto-coordination flag set to true in FGFS code, the amount of rudder used
75# is delta_r_used = delta_r_spec/2, so here the max limits must be 1:5.
76controlSurface dr 42.5 42.5 # [deg]
77
78# if enable-auto-coordination is not used w/ FGFS startup options, then use
79# where 30 deg rudder can be used with 12 deg aileron (2.5:1)
80#controlSurface dr 30 30 # [deg]
81
82mass Weight    750      # [lb]
83# mass moments estimates from Culick paper
84mass I_xx     1318      # [slug-ft^2]
85mass I_yy      271      # [slug-ft^2]
86mass I_zz     1343      # [slug-ft^2]
87mass I_xz        0      # [slug-ft^2]
88
89#  Apparent mass terms
90#  F_Z_aero += -(0.269 * Mass) * W_dot_body;
91#  M_l_aero += -(0.59  * I_xx) * P_dot_body;
92#  M_m_aero += -(0.14  * I_yy) * Q_dot_body;
93mass Mass_appMass_ratio  .269
94mass I_xx_appMass_ratio  .590
95mass I_yy_appMass_ratio  .14
96
97
98# [] max thrust estimate
99#engine simpleSingleModel 171 -5  88    # [lb] [fps]  [lb/fps]
100engine simpleSingleModel 165 -5  88    # [lb] [fps]  [lb/fps]
101# where token3 - static thrust in [lb]
102#       token4 - speed at which thrust goes to zero [ft/sec]
103#       token5 - slope dT/dV at the speed at which thrust goes to zero [lb/fps]
104#engine simpleSingle  171  # [lb]
105
106# lift curve
107CL CLfade CLfade.dat  0 1
108
109# drag polar
110CD CDfa   CDfa.dat    0 1
111
112# moment contributions
113Cm Cmfa   Cmfa2.dat   0 1
114Cm Cmfade Cmfade6.dat 0 1 1
115Cm Cm_q     -3.5         # [/rad], estimate
116
117# da negative right aileron TEU
118CY CY_beta   -.321       # [/rad], -.0056/deg
119CY CY_da     -.636       # [/rad], -.0111/deg
120CY CY_dr     0.241       # [/rad], 0.0042/deg
121# [] mss - update rotary derivatives
122CY CY_p      0.0         # [/rad], placeholder
123CY CY_r      0.3         # [/rad], placeholder
124
125Cl Cl_beta   0.0212      # [/rad], 0.00037033/deg
126Cl Cl_da    -0.1317      # [/rad], -.0023/deg
127Cl Cl_dr     0.007       # [/rad], 0.000125/deg
128# [] mss - update rotary derivatives
129Cl Cl_p     -0.5         # [/rad], placeholder
130Cl Cl_r      0           # [/rad], placeholder
131
132Cn Cn_beta   0.0335      # [/rad], 0.0005853/deg
133Cn Cn_dr    -0.039       # [/rad], -.0069/deg
134Cn Cn_da     0.024       # [/rad], 0.000421/deg
135# [] mss - update rotary derivatives
136Cn Cn_p     -0.06        # [/rad], placeholder
137Cn Cn_r     -0.15        # [/rad], placeholder
138
139# nose wheel (must be position 0 if present)
140gear Dx_gear     0     6.5      # x-offset from CG [ft]
141gear Dy_gear     0     0        # y-offset from CG [ft]
142gear Dz_gear     0     4.5      # z-offset from CG [ft]
143gear cgear       0   300        # damping [lbs/ft/sec]
144gear kgear       0   600        # springiness [lbs/ft]
145gear muGear      0     0        # rolling coefficient
146gear strutLength 0    -0.5      # gear travel [ft] (not yet used)
147
148# right gear (must be position 1 if present)
149gear Dx_gear     1    -8.5      # [ft]
150gear Dy_gear     1     3.25     # [ft]
151gear Dz_gear     1     4        # [ft]
152gear cgear       1   300        # [lbs/ft/sec]
153gear kgear       1   600        # [lbs/ft]
154gear muGear      1     0        # rolling coefficient
155gear strutLength 1     2.5      # gear travel [ft] (not yet used)
156
157# left gear (must be position 2 if present)
158gear Dx_gear     2    -8.5      # [ft]
159gear Dy_gear     2    -3.25     # [ft]
160gear Dz_gear     2     4        # [ft]
161gear cgear       2   300        # [lbs/ft/sec]
162gear kgear       2   600        # [lbs/ft]
163gear muGear      2     0        # rolling coefficient
164gear strutLength 2     2.5      # gear travel [ft] (not yet used)
165
166# right wing
167gear Dx_gear     3    -4        # [ft]
168gear Dy_gear     3    21        # [ft]
169gear Dz_gear     3     3.0      # [ft]
170gear cgear       3   400        # [lbs/ft/sec]
171gear kgear       3   800        # [lbs/ft]
172gear muGear      3     0.0      # rolling coefficient
173gear strutLength 3     2.5      # gear travel [ft] (not yet used)
174
175# left wing
176gear Dx_gear     4    -4        # [ft]
177gear Dy_gear     4   -21        # [ft]
178gear Dz_gear     4     3.0      # [ft]
179gear cgear       4   400        # [lbs/ft/sec]
180gear kgear       4   800        # [lbs/ft]
181gear muGear      4     0.0      # rolling coefficient
182gear strutLength 4     2.5      # gear travel [ft] (not yet used)
183
184# right wing
185gear Dx_gear     5     3        # [ft]
186gear Dy_gear     5    21        # [ft]
187gear Dz_gear     5     3.0      # [ft]
188gear cgear       5   400        # [lbs/ft/sec]
189gear kgear       5   800        # [lbs/ft]
190gear muGear      5     0.0      # rolling coefficient
191gear strutLength 5     2.5      # gear travel [ft] (not yet used)
192
193# left wing
194gear Dx_gear     6     3        # [ft]
195gear Dy_gear     6   -21        # [ft]
196gear Dz_gear     6     3.0      # [ft]
197gear cgear       6   400        # [lbs/ft/sec]
198gear kgear       6   800        # [lbs/ft]
199gear muGear      6     0.0      # rolling coefficient
200gear strutLength 6     2.5      # gear travel [ft] (not yet used)
201
202*
203