Mensa XE (Extra Efficiency) High Efficiency Family Airplane

1
Mensa XE (Extra Efficiency)High Efficiency
Family Airplane

• Michael Duffy
• Due December 11th, 2007
• Georgia Tech AE 6343 Aircraft Design I, Project
  2

Presented to Prof. Dimitri N. Mavris Honor Code
Statement I the above signed certify that I
have abided by the honor code of the Georgia
Institute of Technology and followed the
collaboration guidelines as specified in the
project description for this assignment."
2
Introduction
3
Introduction - Requirements

• Mensa XE is a High Efficiency Family Airplane
• A four seat, low-cost, high efficiency family
  aircraft. 20 year entry into service.
• Design Mission
• Payload 22 Pax baggage (400 240 160 lbs
  800 lbs total)
• Block Fuel Burn gt 30 miles per gallon
• Range 700 miles (608.3 nm)
• Loiter 45 minutes, end of mission
• Performance Requirements
• Cruise Speed gt 200 mph (174 knots)
• TOFL 3000 ft, over 50 ft obstacle
• V_stall lt 61 kts Stall
• V_TO gt 1.1 V_stall Takeoff
• V_CL gt 1.2 V_stall Climb
• V_A gt 1.3 V_stall Approach
• V_TD gt 1.15 V_stall Touchdown
• Climb 300 fpm _at_SLS
• Miscellaneous Requirements
• Glass cockpit flight instruments
• VOR/ILS/GPS navigation w/on-board map

Source (1)
4
Introduction Mensa XE

• Range 700 miles
• Cruise 200 mph
• Fuel Consumption 39.7 mpg
• Engine 250 HP
• V_stall 51 knots
• Take off distance 2,227 ft
• Landing distance 2,817 ft

FINAL FLOPS SIZING AND PERFORMANCE RESULTS
OPERATING WEIGHT EMPTY 1506.7 LB
PAYLOAD 800.0 LB
MAXIMUM FUEL 136.6
LB GROSS WEIGHT
2443.4 LB REFERENCE WING AREA
138.00 SQ FT WING LOADING
17.71 LB/SQ FT THRUST PER ENGINE
419.8 LB ENGINE SCALE
FACTOR 1.0000 THRUST-WEIGHT
RATIO 0.1718
Geometry Span 38 ft. Wing Area 138 sq.ft. AR
10.4 Taper Ratio 0.446 Sweep 7.0 Dihedral
20 Thickness to chord of wing (weighted ave.)
0.12
5
Conceptual Sizing and Synthesis
6
Conceptual Sizing and Synthesis - Summary

• Using project 1 sizing and synthesis Fixed Wing
  Conceptual Design Tool
• Mission analysis (summary, table)
• Constraint analysis (plot)
• Final design point and estimated TOGW
• Briefly Summarize sizing exercise and document
  key assumptions
• Design point (from conceptual design tool)
• T/W 0.14
• W/S 17.0
• W_0 2,348 lbs
• W_E 1,408 lbs
• W_CP 2,209 lbs
• Wing Area 138 sq.ft.
• Required Thrust 328.7 lbs.

7
Conceptual Sizing and Synthesis 3-View

• Graphical Model (3-view)

38
Wing Area 138 ft.sq.
24
8 4 bladed
8
Conceptual Sizing and Synthesis Mission Analysis

• Mission Analysis
• 800 lbs of payload
• Take-Off Gross Weight 2,348 lbs
• Weight Empty 1,408 lbs

Note Source
9
Conceptual Sizing and Synthesis Mission Summary

• Mission Summary
• 700 miles range (608.3 nautical miles)
• 139 lbs of Fuel (23.2 gal)
• 30 mpg (Design requirement)

Note Source
10
Conceptual Sizing and Synthesis Constraint
Analysis
Design Space
Landing distance 3,000 ft, V_TD gt1.15 V_stall
Thrust Loading, T/W
Design Point
Take off 3,000 ft, 50 ft obstacle, V_stall lt 61
kts
T/W 0.14 W/S 17.0
Climb 300 fpm, V_CL gt 1.2V_stall
V_stall lt 61 kts
Service Ceiling 15,000 ft
Cruise Speed gt 200 mph
Wing Loading, W/S
11
Preliminary Sizing and Synthesis - Input
12
Preliminary Sizing and Synthesis - Input

• Construct Working FLOPS File
• Convey information and assumptions form
  conceptual phase have carried over to FLOPS
  started preliminary sizing with output from
  conceptual design phase
• T/W 0.14 and W/S 17.0
• What information (assumed or inferred) from the
  vehicle concept description
• Sizing Mission
• Payload 22 Pax baggage (400 240 160 lbs
  800 lbs total)
• Block Fuel Burn gt 30 miles per gallon
• Range 700 miles (608.3 nm)
• Loiter 45 minutes, end of mission
• Design Constraints
• Cruise Speed gt 200 mph (174 knots)
• TOFL 3000 ft, over 50 ft obstacle
• V_stall lt 61 kts Stall
• V_TO gt 1.1 V_stall Takeoff
• V_CL gt 1.2 V_stall Climb
• V_A gt 1.3 V_stall Approach
• V_TD gt 1.15 V_stall Touchdown
• Climb 300 fpm _at_SLS

Source (2)
13
Preliminary Sizing and Synthesis - Input

• Design Point
• Started preliminary sizing with T/W 0.14, W/S
  17.0
• Attempt to match the 329 lbs of thrust
  requirement
• 30 mpg
• Max Cruise Altitude 12,000 ft.
• 3,000 ft. runway
• Geometry parameters (from output of conceptual
  design)
• Wing
• Span 38 ft.
• Wing Area 138 sq.ft.
• AR 10.4
• Taper Ratio 0.446
• Sweep 7.0
• Dihedral 20
• Thickness to chord of wing (weighted ave.) 0.12
• Fuselage
• Length 24 ft.
• Width 3.44 ft.
• Depth 4.59 ft.

Source (2)
14
Preliminary Sizing and Synthesis - Input

• Propulsion and power plant parameters
• TELEDYNE CONTINENTAL MOTORS - IO-360-ES (X
  Modified for 2,027 tech.)
• 250 HP (Modified for 2,027 tech.)
• Min SFC 0.35 (modified for 2,027 tech.)
• Six cylinders horizontally opposed
• Four strokes, Fuel injected, Spark ignition,
  Direct drive
• Air-cooled
• Wet sump engine, Incorporating a top induction
  system, bottom exhaust.
• Height 22.43 in.
• Width 31.46 in.
• Length 34.03 in.

Source (4)
15
Preliminary Sizing and Synthesis - Input

• Aircraft type Single engine, tail sitter, low
  wing
• Aircraft class Family four passenger
• Percent of Materials used Airframe 85
  composites
• Technology year - 2027
• Intermediary and Final Calculations
• To obtain the required efficiency the RPM was
  varied to achieve 30 mpg
• To obtain the required rate of climb the engine
  power was increased from 210 hp to 250 hp
• To obtain the required take off distance wing CL
  max was increased to CL 2.0

16
Preliminary Sizing and Synthesis - Output
17
Conceptual Sizing and Synthesis 3-View

• Graphical Model (3-view) FINAL DESIGN

38
Wing Area 138 ft.sq.
24
6.5 6 bladed
18
High Efficiency Wing Design
High Aspect Ratio
Advanced Feather Tip
Combination of advance tips and high aspect ratio
balance Aerodynamics with Manufacturability
19
Preliminary Sizing and Synthesis - Weight

• Weight Breakdown
• Table user defined percentage of usage of
  composites and non-traditional materials

• Emergency parachute system, and air-bag system
  (Cirrus SR20/22 safety features)

Source (3)
20
Preliminary Sizing and Synthesis - Weight

• Weight Breakdown

• Structure 85 Composites
• Wing
• Tail
• Fuselage

• Emergency parachute system, and air-bag system
  (Cirrus SR20/22 safety features)

Final WE 1,497 Final TOGW 2,443
Source (3, 4)
21
Preliminary Sizing and Synthesis - Propulsion

• Propulsion and Powerplant
• Description of powerplant
• 250 HP
• Six cylinders horizontally opposed
• Low RPM (1,600 RPM)
• High Efficiency (0.35 SFC)
• Number of Engines 1
• Placement Front Mounted

Source (4)
22
Preliminary Sizing and Synthesis - Propulsion

• Propulsion and Powerplant
• Thrust vs. Altitude curves for varying Mach
  number

Mach
0.28 0.24 0.20 0.16 0.12 0.08 0.04
0.00
Altitude (ft)
Standard Day
Thrust (lbs)
23
Preliminary Sizing and Synthesis - Propulsion

• Propulsion and Powerplant
• Fuel consumption curves

Mach
0.00 0.04 0.08 0.12 0.16 0.20 0.24
0.28
Altitude (ft)
Standard Day
SFC (lbsm/lbs hour )
24
Preliminary Sizing and Synthesis - Aerodynamics

• Aerodynamics
• Basic aerodynamic description of aircraft
• Span 28 ft.
• Wing Area 138 sq.ft.
• AR 10.4
• Taper Ratio 0.446
• Sweep 7.0
• Dihedral 20
• Thickness to chord of wing (weighted ave.) 0.12

25
Preliminary Sizing and Synthesis - Aerodynamics

• Aerodynamics
• Drag polar for varying Mach number (graph)

Mach 0.2 Mach 0.3 Mach 0.4 Mach 0.5
CD
CL
26
Preliminary Sizing and Synthesis - Mission
10,000 ft Altitude Cruise _at_ 200mph
45 min Loiter

• Mission Performance
• Mission profile (schematic)

700 Miles
TO _at_ SL, Standard
Land _at_ SL, Standard
17.6 Gallons
39.7 mpg
700 miles (608.3 nm)
27
Preliminary Sizing and Synthesis - Mission

• Mission Performance
• Instantaneous cruise data

28
Preliminary Sizing and Synthesis Constraint
Analysis

• Constraint Analysis
• After completing the FLOPS preliminary design
  analysis, the required thrust went from 329 lbs
  to 419 lbs
• Keeping the wing area the same the wing loading
  went up to W/S 17 to 17.74 psf

Conceptual Design Point Preliminary Design Point
T/W 0.14 TOGW 2,348 lbs WE 1,408 lbs Thrust 329 lbs T/W 0.178 TOGW 2,443 lbs WE 1,507 lbs Thrust 419
W/S 17 S 138 sq.ft. W/S 17.71 S 138 sq.ft.
29
Preliminary Sizing and Synthesis Constraint
Analysis

• Landing Requirements
• Take off, DFAROFF 2,227 ft lt 3,000 ft
• Landing, DFARLDG 2,817 ft lt 3,000 ft.
• Stall Requirements
• STALL SPEED (VS) 51.14 kts lt 61 kts
• 1.05 VS 53.69 kts
• 1.20 VS 61.36 kts
• Miles per Gallon 39.7 gt 30.0
• Cost/AC 58 Million gt 150,000 Maybe I made a
  mistake?

Exceeded
Exceeded
Exceeded
Exceeded
Not Met
30
Conclusions
31
Conclusions

• Using the FLOPS program an aircraft with the
  range of 700 miles _at_ 200 mph was designed The
  table below summarizes the key parameters for the
  Mensa XE
• Further detail into engine design would be the
  next step, specifically
• Efficiency
• Fuel type
• Engine size

FINAL FLOPS SIZING AND PERFORMANCE RESULTS
OPERATING WEIGHT EMPTY 1506.7 LB
PAYLOAD 800.0 LB
MAXIMUM FUEL 136.6
LB GROSS WEIGHT
2443.4 LB REFERENCE WING AREA
138.00 SQ FT WING LOADING
17.71 LB/SQ FT THRUST PER ENGINE
419.8 LB ENGINE SCALE
FACTOR 1.0000 THRUST-WEIGHT
RATIO 0.1718
32
References

• (1) AE 6343 Aircraft Design Project 2, -2007,
  Sizing and Synthesis with a Legacy Tool for
  Distance Learning Students, Hernando Jimenez
• (2) Flight Optimization System, Release 6.12,
  User's Guide, Revised 14, October 2004, L.A.
  (Arnie) McCullers
• (3) http//www.cirrusdesign.com/sr20/features.aspx
  
• (4) http//www.tcmlink.com/EngSpecSheetDocs/IO360G
  .pdf