modeler.h - mainline in DATCOM-Modeler

/* modeler.h */
/*
 *=============================================================================
 *
 *
 *  Copyright (C) 2009  Anders Gidenstam (anders(at)gidenstam.org)
 *  Copyright (C) 2009  Ronald Jensen    (ron(at)jentronics.com)
 *  http://www.gidenstam.org
 *  http://www.jentronics.com
 *
 *  This program is free software; you can redistribute it and/or modify
 *  it under the terms of the GNU General Public License as published by
 *  the Free Software Foundation; either version 3 of the License, or
 *  (at your option) any later version.
 *
 *  This program is distributed in the hope that it will be useful,
 *  but WITHOUT ANY WARRANTY; without even the implied warranty of
 *  MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
 *  GNU General Public License for more details.
 *
 *  You should have received a copy of the GNU General Public License
 *  along with this program; if not, write to the Free Software
 *  Foundation, Inc., 59 Temple Place, Suite 330, Boston, MA  02111-1307  USA
 *=============================================================================
 */

#ifndef MODELER_H
/* Flight Conditions */

/* Optional Inputs */
struct OPTINS {
  double ROUGFC, /* Surface Roughness Factor */
         SREF, /* Reference Area, value of theoretical wing */
         CBARR, /* Longitudinal Reference Value.  MAC. */
         BLREF; /* Lateral Reference Length.  Wing Span. */
/*  char pad[4]; */
} ;

/* SYNTHS Reference Parameters*/
struct SYNTHS {
  double XCG, ZCG,
         XW, ZW, ALIW,
         XH, ZH, ALIH,
         XV, ZV,
         XVF, ZVF,
         SCALE,
         HINAX;
  int    VERTUP;
/*  char[4] pad; */
} ;

/* Body Geometric Data */
struct BODY {
  int    NX;      /* Number of longitudinal body stations at which data is specified, max of 20 */
  double X[20];   /* Array(20) Longitudinal distance measured from arbitray location */
  double S[20];   /* Array(20) Cross sectional area at station. See note above. */
  double P[20];   /* Array(20) Periphery at station Xi. See note above. */
  double R[20];   /* Array(20) Planform half width at station Xi. See note above. */
  double ZU[20];  /* Array(20) Z-coordinate at upper body surface at station Xi
                   *           (positive when above centerline)
                   *           [Only required for subsonic asymmetric bodies] */
  double ZL[20];  /* Array(20) Z-coordinate at lower body surface at station Xi
                   *           (negative when below centerline)
                   *           [Only required for subsonic asymmetric bodies] */
  double BNOSE;   /* Nosecone type  1.0 = conical (rounded), 2.0 = ogive (sharp point)
                   *           [Not required in subsonic speed regime] */
  double BTAIL;   /* Tailcone type  1.0 = conical, 2.0 = ogive, omit for lbt = 0
                   *           [Not required in subsonic speed regime] */
  double BLN;     /* Length of body nose
                   *           Not required in subsonic speed regime */
  double BLA;     /* Length of cylindrical afterbody segment, =0.0 for nose alone
                   *           or nose-tail configuration
                   *           Not required in subsonic speed regime */
  double DS;      /* Nose bluntness diameter, zero for sharp nosebodies
                   *           [Hypersonic speed regime only] */
  int ITYPE;      /* 1.0 = straight wing, no area rule
                   * 2.0 = swept wing, no area rule (default)
                   * 3.0 = swept wing, area rule */
  int METHOD;     /* 1.0 = Use existing methods (default)
                   * 2.0 = Use Jorgensen method */
} ;

/* Wing Planform Variables */
struct WGPLNF {
  double   CHRDR,  /* Chord root */
           CHRDBP, /* Chord at breakpoint. Not required for straight tapered planform. */
           CHRDTP, /* Tip chord */
           SSPN,   /* Semi-span theoretical panel from theoretical root chord */
           SSPNE,  /* Semi-span exposed panel, */
           SSPNOP, /* Semi-span outboard panel. Not required for straight tapered planform. */
           SAVSI,  /* Inboard panel sweep angle */
           SAVSO,  /* Outboard panel sweep angle */
           CHSTAT, /* Reference chord station for inboard and outboard panel sweep angles, fraction of chord */
           TWISTA, /* Twist angle, negative leading edge rotated down (from exposed root to tip) */
           SSPNDD, /* Semi-span of outboard panel with dihedral */
           DHDADI, /* Dihedral angle of inboard panel */
           DHDADO; /* Dihedral angle of outboard panel. If DHDADI=DHDADO only input DHDADI */
  int      TYPE;   /* 1.0 - Straight tapered planform
                      2.0 - Double delta planform (aspect ratio <= 3)
                      3.0 - Cranked planform (aspect ratio > 3) */
/*  char[4] pad; */
} ;

/* Horizontal Tail Planform Variables */
struct HTPLNF {
  char pad[4];
} ;

/* Vertical Tail Planform Variables */
struct VTPLNF {
  char pad[4];
} ;

/* Vertical Fin Planform Variables */
struct VFPLNF {
  char pad[4];
} ;

/* Jet Power Parameters */
struct JETPWR{
  char pad[4];
} ;

/* Propeller Power Parameters */
struct PROPWR{
  double AIETLP, /* Angle of incidence of engine thrust axis */
         NENGSP, /* Number of engines 1 or 2 */
         THSTCP, /* Thrust Coefficient */
         PHALOC, /* Axial (X) location of propeller hub */
         PHVLOC, /* Vertical (Z) location of propeller hub */
         PRPRAD, /* Propeller radius */
         BWAPR3, /* Blade width at 0.3 radius */
         BWAPR6, /* Blade width at 0.6 radius */
         BWAPR9, /* Blade width at 0.9 radius */
         NOPBPE, /* Number of propeller blades per engine */
         BAPR75, /* Blade angle at 0.75 radius */
         YP;     /* Lateral (Y) location of engine */
  int    CROT;   /* True = counter rotating propeller */
} ;

/* Twin Vertical Panels */
struct TVTPAN{
  char pad[4];
} ;

/* Airfoil */
/*************************
 *
 * This structure contains data
 * calculated from the input NACA
 * number or airfoil geometric data.
 *
 *************************/
struct AIRFOIL{
	int COUNT;    /* Number of entries */
	double *DATAX; /* data elements */
	double *DATAY;
};

typedef struct RIB3D {
	int count;  /* Number of entries */
        double *X; /* data elements */
        double *Y;
	double *Z;
} RIB3D;



#define MODELER_H
#endif

1	/* modeler.h */
2	/*
3	*=============================================================================
4	*
5	*
6	* Copyright (C) 2009 Anders Gidenstam (anders(at)gidenstam.org)
7	* Copyright (C) 2009 Ronald Jensen (ron(at)jentronics.com)
8	* http://www.gidenstam.org
9	* http://www.jentronics.com
10	*
11	* This program is free software; you can redistribute it and/or modify
12	* it under the terms of the GNU General Public License as published by
13	* the Free Software Foundation; either version 3 of the License, or
14	* (at your option) any later version.
15	*
16	* This program is distributed in the hope that it will be useful,
17	* but WITHOUT ANY WARRANTY; without even the implied warranty of
18	* MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
19	* GNU General Public License for more details.
20	*
21	* You should have received a copy of the GNU General Public License
22	* along with this program; if not, write to the Free Software
23	* Foundation, Inc., 59 Temple Place, Suite 330, Boston, MA 02111-1307 USA
24	*=============================================================================
25	*/
26
27	#ifndef MODELER_H
28	/* Flight Conditions */
29
30	/* Optional Inputs */
31	struct OPTINS {
32	double ROUGFC, /* Surface Roughness Factor */
33	SREF, /* Reference Area, value of theoretical wing */
34	CBARR, /* Longitudinal Reference Value. MAC. */
35	BLREF; /* Lateral Reference Length. Wing Span. */
36	/* char pad[4]; */
37	} ;
38
39	/* SYNTHS Reference Parameters*/
40	struct SYNTHS {
41	double XCG, ZCG,
42	XW, ZW, ALIW,
43	XH, ZH, ALIH,
44	XV, ZV,
45	XVF, ZVF,
46	SCALE,
47	HINAX;
48	int VERTUP;
49	/* char[4] pad; */
50	} ;
51
52	/* Body Geometric Data */
53	struct BODY {
54	int NX; /* Number of longitudinal body stations at which data is specified, max of 20 */
55	double X[20]; /* Array(20) Longitudinal distance measured from arbitray location */
56	double S[20]; /* Array(20) Cross sectional area at station. See note above. */
57	double P[20]; /* Array(20) Periphery at station Xi. See note above. */
58	double R[20]; /* Array(20) Planform half width at station Xi. See note above. */
59	double ZU[20]; /* Array(20) Z-coordinate at upper body surface at station Xi
60	* (positive when above centerline)
61	* [Only required for subsonic asymmetric bodies] */
62	double ZL[20]; /* Array(20) Z-coordinate at lower body surface at station Xi
63	* (negative when below centerline)
64	* [Only required for subsonic asymmetric bodies] */
65	double BNOSE; /* Nosecone type 1.0 = conical (rounded), 2.0 = ogive (sharp point)
66	* [Not required in subsonic speed regime] */
67	double BTAIL; /* Tailcone type 1.0 = conical, 2.0 = ogive, omit for lbt = 0
68	* [Not required in subsonic speed regime] */
69	double BLN; /* Length of body nose
70	* Not required in subsonic speed regime */
71	double BLA; /* Length of cylindrical afterbody segment, =0.0 for nose alone
72	* or nose-tail configuration
73	* Not required in subsonic speed regime */
74	double DS; /* Nose bluntness diameter, zero for sharp nosebodies
75	* [Hypersonic speed regime only] */
76	int ITYPE; /* 1.0 = straight wing, no area rule
77	* 2.0 = swept wing, no area rule (default)
78	* 3.0 = swept wing, area rule */
79	int METHOD; /* 1.0 = Use existing methods (default)
80	* 2.0 = Use Jorgensen method */
81	} ;
82
83	/* Wing Planform Variables */
84	struct WGPLNF {
85	double CHRDR, /* Chord root */
86	CHRDBP, /* Chord at breakpoint. Not required for straight tapered planform. */
87	CHRDTP, /* Tip chord */
88	SSPN, /* Semi-span theoretical panel from theoretical root chord */
89	SSPNE, /* Semi-span exposed panel, */
90	SSPNOP, /* Semi-span outboard panel. Not required for straight tapered planform. */
91	SAVSI, /* Inboard panel sweep angle */
92	SAVSO, /* Outboard panel sweep angle */
93	CHSTAT, /* Reference chord station for inboard and outboard panel sweep angles, fraction of chord */
94	TWISTA, /* Twist angle, negative leading edge rotated down (from exposed root to tip) */
95	SSPNDD, /* Semi-span of outboard panel with dihedral */
96	DHDADI, /* Dihedral angle of inboard panel */
97	DHDADO; /* Dihedral angle of outboard panel. If DHDADI=DHDADO only input DHDADI */
98	int TYPE; /* 1.0 - Straight tapered planform
99	2.0 - Double delta planform (aspect ratio <= 3)
100	3.0 - Cranked planform (aspect ratio > 3) */
101	/* char[4] pad; */
102	} ;
103
104	/* Horizontal Tail Planform Variables */
105	struct HTPLNF {
106	char pad[4];
107	} ;
108
109	/* Vertical Tail Planform Variables */
110	struct VTPLNF {
111	char pad[4];
112	} ;
113
114	/* Vertical Fin Planform Variables */
115	struct VFPLNF {
116	char pad[4];
117	} ;
118
119	/* Jet Power Parameters */
120	struct JETPWR{
121	char pad[4];
122	} ;
123
124	/* Propeller Power Parameters */
125	struct PROPWR{
126	double AIETLP, /* Angle of incidence of engine thrust axis */
127	NENGSP, /* Number of engines 1 or 2 */
128	THSTCP, /* Thrust Coefficient */
129	PHALOC, /* Axial (X) location of propeller hub */
130	PHVLOC, /* Vertical (Z) location of propeller hub */
131	PRPRAD, /* Propeller radius */
132	BWAPR3, /* Blade width at 0.3 radius */
133	BWAPR6, /* Blade width at 0.6 radius */
134	BWAPR9, /* Blade width at 0.9 radius */
135	NOPBPE, /* Number of propeller blades per engine */
136	BAPR75, /* Blade angle at 0.75 radius */
137	YP; /* Lateral (Y) location of engine */
138	int CROT; /* True = counter rotating propeller */
139	} ;
140
141	/* Twin Vertical Panels */
142	struct TVTPAN{
143	char pad[4];
144	} ;
145
146	/* Airfoil */
147	/*************************
148	*
149	* This structure contains data
150	* calculated from the input NACA
151	* number or airfoil geometric data.
152	*
153	*************************/
154	struct AIRFOIL{
155	int COUNT; /* Number of entries */
156	double DATAX; / data elements */
157	double *DATAY;
158	};
159
160	typedef struct RIB3D {
161	int count; /* Number of entries */
162	double X; / data elements */
163	double *Y;
164	double *Z;
165	} RIB3D;
166
167
168
169	#define MODELER_H
170	#endif

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