Cessna 310 -- Linear Model

Graduate Research done by Jeff Scott
Advisor: Prof. Michael Selig
Applied Aerodynamics Group
Department of Aeronautical and Astronautical Engineering
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801

Last updated May 31, 2000

The linear aerodynamics model uses stability derivatives to approximate actual aircraft behavior. The Cessna 310 linear model is based on the following flight conditions (cruise):

Flight Conditions
Variable Variable
in Code 		Description Units Value(s) Source Notes
h Altitude altitude above sea level ft 8000 Roskam pg 487
Alpha angle of attack deg 0 Roskam pg 487
V V_true_kts velocity (true air speed) kts 185 Roskam pg 487 Mach 0.288
q Dynamic_pressure dynamic pressure lb/ft2 91.2 Roskam pg 487
C.G. - center of gravity location % 33 Roskam pg 487
CL CL lift coefficient - ? not available
CD CD drag coefficient - ? not available
Cm Cm pitching moment coefficient - ? not available

The data input into the simulator is listed in the following tables:

Geometry
Variable Variable
in Code 		Description Units Value(s) Source Notes
b bw wingspan ft 36.9 Roskam pg 487
cbar wing mean aerodynamic chord ft 4.79 Roskam pg 487
S Sw wing surface area ft2 175 Roskam pg 487

Control Surface Geometry
Variable Variable
in Code 		Description Units Value(s) Source Notes
emax demax maximum elevator deflection deg +20 - guess
emin demin minimum elevator deflection deg -20 - guess
amax damax maximum aileron deflection deg +20 - guess
amin damin minimum aileron deflection deg -20 - guess
rmax drmax maximum rudder deflection deg +20 - guess
rmin drmin minimum rudder deflection deg -20 - guess

Mass Data
Variable Variable
in Code 		Description Units Value(s) Source Notes
W Weight weight at flight condition lb 4600 Roskam pg 487 converted to Mass
[slug/ft3] in code
Ixx I_xx roll inertia slug ft2 8884 Roskam pg 487
Iyy I_yy pitch inertia slug ft2 1939 Roskam pg 487
Izz I_zz yaw inertia slug ft2 11001 Roskam pg 487
Ixz I_xz lateral cross inertia slug ft2 0 Roskam pg 487

Propulsion Data
Variable Variable
in Code 		Description Units Value(s) Source Notes
Tmax simpleSingleMaxThrust maximum thrust lb 500 Roskam pg 488 estimated from CTx
at cruise
Pmax - maximum power kW 426 David pg 250 max engine rating
not used in code

Aerodynamic Data
Variable Variable
in Code 		Description Units Value(s) Source Notes
CD0 CDo drag coefficient at =0 - 0.029 Roskam pg 488
CD CD_a drag curve slope 1/rad 0.16 Roskam pg 488
CDe CD_de drag due to elevator 1/rad 0 Roskam pg 488 e positive down
CL0 CLo lift coefficient at =0 - 0.288 Roskam pg 488
CL CL_a lift curve slope 1/rad 4.58 Roskam pg 488
CL CL_adot lift due to angle of attack rate 1/rad 5.3 Roskam pg 488
CLq CL_q lift due to pitch rate 1/rad 9.7 Roskam pg 488
CLe CL_de lift due to elevator 1/rad 0.81 Roskam pg 488 e positive down
Cm0 Cmo pitch moment coefficient at =0 - 0.07 Roskam pg 488
Cm Cm_a pitch moment due to angle of attack 1/rad -0.137 Roskam pg 488
Cm Cm_adot pitch moment due to angle of attack rate 1/rad -12.7 Roskam pg 488
Cmq Cm_q pitch moment due to pitch rate 1/rad -26.3 Roskam pg 488
Cme Cm_de pitching moment due to elevator 1/rad -2.26 Roskam pg 488 e positive down
CY CY_beta side force fue to sideslip angle 1/rad -0.698 Roskam pg 489
CYp CY_p side force due to roll rate 1/rad -0.141 Roskam pg 489
CYr CY_r side force due to yaw rate 1/rad 0.355 Roskam pg 489
CYa CY_da side force due to aileron 1/rad 0 Roskam pg 489 a positive
right aileron up
CYr CY_dr side force due to rudder 1/rad 0.23 Roskam pg 489 r positive left
Cl Cl_beta dihedral effect 1/rad -0.1096 Roskam pg 489
Clp Cl_p roll damping 1/rad -0.551 Roskam pg 489
Clr Cl_r roll moment due to yaw rate 1/rad 0.0729 Roskam pg 489
Cla Cl_da roll moment due to aileron 1/rad -0.172 Roskam pg 489 a positive
right aileron up
Clr Cl_dr roll moment due to rudder 1/rad 0.0192 Roskam pg 489 r positive left
Cn Cn_beta weathercock stability 1/rad 0.1444 Roskam pg 489
Cnp Cn_p adverse yaw 1/rad -0.0257 Roskam pg 489
Cnr Cn_r yaw damping 1/rad -0.1495 Roskam pg 489
Cna Cn_da yaw moment due to aileron 1/rad 0.0168 Roskam pg 489 a positive
right aileron up
Cnr Cn_dr yaw moment due to rudder 1/rad -0.1152 Roskam pg 489 r positive left

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