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SPEED & OPERATION CABIN USEFUL LOAD SAVINGS SPECIFICATIONS OPTIONS SUPPLIERS HISTORY Aircraft PRESS ORIGINAL REPORT

 

MORRISON 6 SPECIFICATIONS

Engine Make Lycoming
Engine Model IO 720 A1BD
Rated BHP 400 @ 2650 rpm
Recommend TBO 1800 hrs.
Propeller Make Hartzell Constant Speed
Propeller Model HC-E3YR-1RF/F8468A-6R
Propeller Diameter 83"
Propeller Ground Clearance 9.75"
Length 29'-11"
Height 7'-2"
Wingspan 35'-10"
Wing Area 174 sq.ft.
STABILIZER Span 13'-0"
STABILIZER SQ FT 24.84
ELEVATORS SQ FT 20.09
VERTICAL FIN SQ FT 12.00
AILERON SQ FT 17.32
FLAPS SQ FT 29 sq ft.
WING AIR FOIL MODIFIED NACA 2412
Ailerons Frieze Type Wide - Chord
Flaps NACA Single Slotted
Wing Aspect Ratio 7.63
Wing Chord Root 64" Tip 42"
Diheadral 1 44'
Wing Loading 25.9 lb./sq.ft.
Power Loading 11.25 lb./hp
Span Loading 125.9 lb./ft.
Empty Weight One seat land VFR - 2197
6 seats - IFR - Autopilot - Radar 2501
Gross Weight 4500 lb.
Useful Load VFR - 2303  IFR - 1999

Angle of Incidence

     Wing Root +1 30'
     Wing Tip -1 30'
     Stabilizer -3 0'
     Engine -3 30'
Cabin Area
     Front Seats 52"
     Center Seats 52.5"
     Rear Seats 44"
     Rear Baggage 38"
     Cabin Height 49"
Seats 6
Doors
     Pilot Door 3' 4" x 3' 1"
     DOUBLE            Cargo Door 3' 2-1/2" x 3' 8-1/8"
Std. Fuel Capacity 90 gal.
Optional Fuel Capacity 140 gal. total
     Land Gear Options tail wheel, floats, skis
Controls duel control yokes
C/G Range moment @ 4500 lbs.
     Max Forward 33.0"
     Max Aft. 49.7"
Ref. Datum: Lower Front Face of Firewall
Airframe Constructions:
 

ALL SKINS  ARE MADE WITH 7781  E-GLASS PREPREG AND EPOXY RESIN CONTENT OF 36 TO 38 %, VACUUMED BAGGED AND COOKED AT 250, PLUS THE FIBERS IN THE PREPREG STAY IN A STRAIGHT LINE MAKING FOR A STRONGER SKIN . PREPREG = STRAIGHT LINE FIBERS = MAXIMUM STRENGTH. 36-38% EPOXY = LIGHTWEIGHT.

Nomex Core WRAPPED IN ADHESIVE

  DESIGNED FOR EASE OF ASSEMBLY. PRE-CURED GRAPHLITE  CARBON ROD PACKS  BUILT INTO THE STRUCTURE TO CARRY THE DESIGNED LOADS. THE ADVANTAGE OF THE RODS IS THAT THE FIBERS IN THE RODS ARE STRAIGHT AND WILL TEST OUT TO TINSEL STRENGTH  DESIGNED.
 

     CALCULATED DATA

MIH design as per part 23 Appendix A  
N/1 3.86 Ultimate 5.70
N/2 -1.96G Ultimate -2.85
Max Flaps Indicate
Vf Min 160mph 10 flaps
             115mph 40 flaps
Maneuvering Indicated Va Min 171 mph
Cruise Indicated Vc Min 206 mph
RED LINE VNE 248 MPH
Dive Indicated Vd Min 274 mph
Flap limitation takeoff 0 to 20
Flap limitation landing 0 to 40
CDO, Drag Coefficient .028
Flat Plate Drag 4.9 Aq. ft.
Clmax., max lift coefficient 2.04
Propeller Efficiency .87
VsF stall Flaps 62 mph @ 4500lb. gross
Max Rate of Climb @ 4500  GROSS WEIGHT  900 FPM
Cruise Climb 80% Power      110 mph
Performance @ 4500 Max Gross Weight With Stock Wing @ IO-720-A
     Take Off Run 900'
     Take Off to 50' 1800'
     Landing From 50' 1400'
     Landing Run 750'

 

 

 

 

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Copyright 2006 Steve Morrison
Last modified: August 05, 2008