;***************************************************************************************************************
;*Water handling*

;The real UWD had poor water handling. For maximum realism manoeuvre on the water with asymmetric power only.
;Water rudders were not available in the real UWD but they are provided for use in FS2002
;Extend and retract water rudders with SHIFT + W
;Do not exceed 15 knots with water rudders extended or you may fracture a float strut leading to loss of control.

;***************************************************************************************************************

[fltsim.0]
title=Gotha UWD
sim=GOTHA-UWD
model=
panel=
sound=
texture=
checklists=
ui_manufacturer=Gothaer Waggonfabrik A.G.
ui_type=G-1 Ursinus Wasser Doppeldecker
ui_variation=Kreigsmarine Nr120
description=The Gotha Ursinus long-range maritime reconnaissance seaplane was the original design from which the Gotha Grossflugzeug series was developed. Designed by Oskar Ursinus in 1914 and built under licence by the Gothaer Waggonfabrik it was not delivered until February 1916. 

[General]
performance=Two 172 hp 6-cyl Mercedes D.III\nCruise climb at full throttle\nTrim with throttle\nReduce rpm to obtain level flight\n

[WEIGHT_AND_BALANCE]
reference_datum_position=0.000000,0.000000,0.000000
empty_weight_CG_position=0.000000,0.000000,0.000000
max_number_of_stations=3
;MTOW=6225
empty_weight=4260			

station_load.0=650,-1.5,0,0 		;crew plus parabellum and ammo

;*********************************************************************************************************************
;
;Torpedo trials and training aircraft - when carrying torpedo only 2 crew and reduced fuel

;Normal fuel and oil=290Kg = 639lbs / 5.9 = 108 USG

;Maximum fuel and oil was 1145lbs as in G-I but use of more than 290Kg depended on sea state

;in these FDE normal fuel is loaded with 3 crew for coastal patrol

;*********************************************************************************************************************

;Moments of Inertia			;all approx
empty_weight_roll_MOI=75000
empty_weight_pitch_MOI=28000
empty_weight_yaw_MOI=52000
empty_weight_coupled_MOI=0.000000


[fuel]
;Max tankage 194 USG including oil but default load is 108 USG allowing operation from the sea with modest swell
;German aviation fuel in 1916 about 55 Octane and had density about 5.9lbs per US gallon (set in air file)
;Oil tanks included in the fuel tankage as these engines consumed significant amounts of oil per flight
;
center1=1,0,0,100,8			;100 can be increased up to 186 if weather conditions permit
fuel_type=1.000000
number_of_tank_selectors=1

[GeneralEngineData]
engine_type=0
Engine.0=6.000000,-5.000000,0.500000
Engine.1=6.000000,5.000000,0.500000
fuel_flow_scalar=1.10000			;including oil consumption

[piston_engine]
;2 x Mercedes D.III class 3 engines each 172hp at 1420 rpm for combat
;
cylinder_displacement=150.3			;huge cylinders
compression_ratio=4.73				
number_of_cylinders=6
max_rated_rpm=1420
max_rated_hp=172					;combat rating
fuel_metering_type=1
cooling_type=0
normalized_starter_torque=0.300000
turbocharged=0
max_design_mp=0.000000
min_design_mp=0.000000
critical_altitude=0.000000
emergency_boost_type=0
emergency_boost_mp_offset=0.000000
emergency_boost_gain_offset=0.000000
fuel_air_auto_mixture=0
auto_ignition=0
max_rpm_mechanical_efficiency_scalar=1.000000
idle_rpm_mechanical_efficiency_scalar=1.000000
max_rpm_friction_scalar=1.000000
idle_rpm_friction_scalar=1.000000

[propeller]
propeller_type=1
propeller_diameter=8.25
propeller_blades=2
propeller_moi=8.7
beta_max=25
beta_min=25
min_gov_rpm=1400.000000
prop_tc=0.100000
gear_reduction_ratio=1.000000
fixed_pitch_beta=25.0
low_speed_theory_limit=80.000000
prop_sync_available=0
prop_deice_available=0
prop_feathering_available=0
prop_auto_feathering_available=0
min_rpm_for_feather=0.000000
beta_feather=0.000000
power_absorbed_cf=0.000000
defeathering_accumulators_available=0
prop_reverse_available=0
minimum_on_ground_beta=0.000000
minimum_reverse_beta=0.000000


[airplane_geometry]
wing_area=882.6
wing_span=72.2			
wing_root_chord=6.12
wing_dihedral=2.8
wing_incidence=6.0
wing_twist=0
oswald_efficiency_factor=0.6
wing_winglets_flag=0
wing_sweep=0.000000
wing_pos_apex_lon=0.000000
wing_pos_apex_vert=0.000000
htail_area=167.000000
htail_span=25.833333
htail_pos_lon=-34.166667
htail_pos_vert=0.000000
htail_incidence=0.000000
htail_sweep=0.000000
vtail_area=97.000000
vtail_span=11.229426
vtail_sweep=0.000000
vtail_pos_lon=-35.666667
vtail_pos_vert=1.500000
elevator_area=71.810000
aileron_area=102.900000
rudder_area=33.950000
elevator_up_limit=27.501974
elevator_down_limit=20.626481
aileron_up_limit=19.480565
aileron_down_limit=14.896903
rudder_limit=23.491270
elevator_trim_limit=60
spoiler_limit=59.988681
spoilerons_available=0
aileron_to_spoileron_gain=0.000000
min_ailerons_for_spoilerons=0.000000
min_flaps_for_spoilerons=0.000000

//4  Impact Damage Threshold      (Feet Per Minute)
//5  Brake Map                   (0=None, 1=Left, 2=Right)
//6  Wheel Radius                (feet)
//7  Steer Angle                         (degrees)
//8  Static Compression          (feet)  (0 if rigid) 
//9  Max/Static Compression Ratio
//10 Damping Ratio / Water Rudder Effectiveness  (0=Undamped, 1=Critically Damped) / 1.0 = normal


[contact_points]
point.0=4,15,8  ,-7.7,1575,0,0,0,0.5,2.5,0.7,0,0,0,0,0
point.1=4,15,-8 ,-7.7,1575,0,0,0,0.5,2.5,0.7,0,0,1,0,0
point.2=4,-15,-8,-7.1,1575,0,0,0,0.5,2.5,0.7,0,0,2,0,0
point.3=4,-15,8 ,-7.1,1575,0,0,0,0.5,2.5,0.7,0,0,3,0,0
point.4=2,-1.66,-36.0,-0.666,1574,0,0,0,0,0.000000,0.000000,0.000000,0.000000,5.000000,0.000000,0.000000
point.5=2,-1.66,36.0,-0.666,1574,0,0,0,0,0,0.000000,0.000000,0.000000,6.000000,0.000000,0.000000
point.6=2,-35.6,0,0,1574,0,0,0,0.000000,0.000000,0.000000,0.000000,0.000000,9.000000,0.000000,0.000000
point.7=2,6.666,0,-0.666,1574,0,0,0,0,0.000000,0.000000,0.000000,0.000000,4.000000,0.000000,0.000000
point.8=5, -15, -8, -8, 1800, 0, 0, 20, 0,  0, 1, 1, 1, 0, 0, 0
point.9=5, -15,  8, -8, 1800, 0, 0, 20, 0,  0, 1, 1, 1, 0, 0, 0

static_pitch=0.2
static_cg_height=7.6

[Reference Speeds]		;all IAS
flaps_up_stall_speed=40
full_flaps_stall_speed=40
cruise_speed=48

[keyboard_response]
elevator=150.000000,250.000000
aileron=150.000000,250.000000
rudder=150.000000,250.000000

[autopilot]					;for beta testing only
autopilot_available=0			
use_no_default_bank=1
use_no_default_pitch=1 
flight_director_available=0
default_vertical_speed=100.000000
autothrottle_available=0
autothrottle_arming_required=0
autothrottle_takeoff_ga=0
autothrottle_max_rpm=0.000000
pitch_takeoff_ga=8.000000


[direction_indicators]
direction_indicator.0=1,0

[Views]
eyepoint=-5,0,6.2