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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.
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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 40º |
| 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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