// zero, then re-initialize coefficients by reading in the coefficient file.
{
static int init = 0;
- static SCALAR elevator_drela, aileron_drela, rudder_drela;
+ //static SCALAR elevator_drela, aileron_drela, rudder_drela;
SCALAR C_ref;
SCALAR B_ref;
SCALAR Cl_r_mod,Cn_p_mod;
SCALAR CL_drela,CD_drela,Cx_drela,Cy_drela,Cz_drela,Cl_drela,Cm_drela,Cn_drela;
SCALAR QS;
+ /*
SCALAR G_11,G_12,G_13;
SCALAR G_21,G_22,G_23;
SCALAR G_31,G_32,G_33;
SCALAR U_body_X,U_body_Y,U_body_Z;
SCALAR V_body_X,V_body_Y,V_body_Z;
SCALAR W_body_X,W_body_Y,W_body_Z;
+ */
SCALAR P_atmo,Q_atmo,R_atmo;
// set the parameters
void basic_gear()
{
-char rcsid[] = "junk";
+//char rcsid[] = "junk";
#define NUM_WHEELS 4
// char gear_strings[NUM_WHEELS][12]={"nose","right main", "left main", "tail skid"};
void c172_gear()
{
-char rcsid[] = "$Id$";
+//char rcsid[] = "$Id$";
#define NUM_WHEELS 4
// char gear_strings[NUM_WHEELS][12]={"nose","right main", "left main", "tail skid"};
/*
Clp = -0.4704,
Clr = 0.1665,
Cyb = -1169.8/(146.69*146.69*157.5/2.0*0.00238),
- Cyp = -0.0342,
+ // Cyp = -0.0342, (unused)
Cnb = 11127.2/(146.69*146.69*157.5/2.0*0.00238)/30.0,
Cnp = -0.0691,
Cnr = -0.0930,
- Cyf = -14.072/(146.69*146.69*157.5/2.0*0.00238),
- Cyps = 89.229/(146.69*146.69*157.5/2.0*0.00238),
- Clf = -5812.4/(146.69*146.69*157.5/2.0*0.00238)/30.0, //%Clda ?
- Cnf = -853.93/(146.69*146.69*157.5/2.0*0.00238)/30.0, //%Cnda ?
- Cnps = -1149.0/(146.69*146.69*157.5/2.0*0.00238)/30.0, //%Cndr ?
+ // Cyf = -14.072/(146.69*146.69*157.5/2.0*0.00238), (unused)
+ // Cyps = 89.229/(146.69*146.69*157.5/2.0*0.00238), (unused)
+ // Clf = -5812.4/(146.69*146.69*157.5/2.0*0.00238)/30.0, //%Clda ? (unused)
+ // Cnf = -853.93/(146.69*146.69*157.5/2.0*0.00238)/30.0, //%Cnda ? (unused)
+ // Cnps = -1149.0/(146.69*146.69*157.5/2.0*0.00238)/30.0, //%Cndr ? (unused)
Cyr = 1.923/(146.69*146.69*157.5/2.0*0.00238),
Cx0 = -0.4645/(157.5*0.3048*0.3048),
Cm0 = 0.0959,
Clda = -5812.4/(146.69*146.69*157.5/2.0*0.00238)/30.0, // Clf
- Cnda = -853.93/(146.69*146.69*157.5/2.0*0.00238)/30.0, // Cnf
+ // Cnda = -853.93/(146.69*146.69*157.5/2.0*0.00238)/30.0, // Cnf (unused)
Cndr = -1149.0/(146.69*146.69*157.5/2.0*0.00238)/30.0, // Cnps
/*
void cherokee_gear()
{
-char rcsid[] = "$Id$";
+// char rcsid[] = "$Id$";
/*
* Aircraft specific initializations and data goes here
OUTPUTS:
--------------------------------------------------------------------------*/
-static char rcsid[] = "$Id$";
+// static char rcsid[] = "$Id$";
#include <string.h>
#include <stdio.h>
void ls_stamp( void ) {
- char rcsid[] = "$Id$";
+ // char rcsid[] = "$Id$";
char revid[] = "$Revision$";
char dateid[] = "$Date$";
struct tm *nowtime;
#define SWAP(a,b) {temp=(a);(a)=(b);(b)=temp;}
-static char rcsid[] = "$Id$";
+// static char rcsid[] = "$Id$";
int *nr_ivector(long nl, long nh)
}
void navion_gear( SCALAR dt, int Initialize ) {
-char rcsid[] = "$Id$";
+// char rcsid[] = "$Id$";
/*
* Aircraft specific initializations and data goes here
int FlapData::readIn (ifstream* f){
int i,j,k,l;
- int count=0;
+ //int count=0;
char numstr[200];
f->getline(numstr,200);