4. Mission Requirements
Requirement Outcome
Wing Placement Low Wing
Engine Placement Tractor- Mounted on Wings
Landing Gear Tricycle-retractable
IFR Design yes
FAR 23 - C normal category
standards
yes
6 passengers total + 120 lbs
baggage
yes
2 gallons unusable fuel per engine yes
45 minutes excess fuel yes
T-Hanger with 6” clearance yes
4 hours mission time Yes-- 3 hours 50 minutes
5. Cost Analysis: Production
Eastlake Method (General Aviation Aircraft Design:Applied
Methods and Procedures)
Total Hours and employees required (5 years)
Description Value Units
Engineering hours 183,719.6 hours
Tooling hours 141,641.7 hours
Manufacturing hours 1,398,511.4 hours
Description Value Units
Engineering Employees 19 employees
Tooling Employees 15 employees
Manufacturing Employees 140 employees
6. Cost Analysis: Total
Total Cost Breakdown with Quantitative Discount Factor (600 Units)
Description Value Units
Engineering cost $35,442,227.91 dollars
Development support cost $11,102,832.47 dollars
Flight test cost $7,896,836.95 dollars
Tooling cost $18,117,521.81 dollars
Manufacturing labor cost $72,559,419.14 dollars
Quality Control cost $20,205,190.53 dollars
Materials and Equipment cost $20,951,909.82 dollars
Engines, Props, and Avionics cost $125,081,520.00 dollars
Insurance cost $58,090,020.00 dollars
Total Production Cost $449,335,824.00 dollars
$748,893.04 per unit
7. Cost Analysis: Break Even
Break-Even Point analysis
Determined Selling Price: $1,000,000.00
Time to Break even: 2.33 years
0 200 400 600 800 1000 1200 1400 1600
0
200
400
600
800
1000
1200
1400
1600
$ 700k
$ 800k
$ 900k
$ 1000k
production cost
Units Sold
TotalRevenueandProductionCost($millions)
289 aircraft to
break even
480 aircraft to
break even
1420 aircraft
to break even
13. Design
Initial design revised to
reduce drag
Twin Vertical tail to ensure
dynamic stability in EO
takeoff
Blended wings and HT
Fully retractable landing
gear
Main landing gear on aft
spar
Wing is made transparent to
show landing gear storage
15. Design: Fuel Tanks
Fuel Tanks are located between the
forward and aft spars in the wings
Fuel Tanks
Tanks are located immediately outboard of the landing gear wheelhouse
16. Weight and Balance
Fuel remaining after Mission : 280 lb
Description Symbol Value Units
Design Gross Weight W0
6404.0 lb
Projected Empty Weight We
4044.0 lb
Design Fuel Weight Wf
1200.0 lb
Crew Weight Wc
190.0 lb
Payload Wp
970.0 lb
Projected Useful Load Wu
2360.0 lb
Wing Loading W/S 28.1
21. Performance: General
Category Value Units
Endurance 6:48 Hours:minutes
Range 1550 Nautical miles
Stall Speed 72 KTAS
Take-off Speed 73.2 KTAS
Take-off Distance 1712 ft
Cruise Speed 198 KTAS
Max Speed 218 KTAS
ROD 634 Fpm
Landing Distance 2,265 ft
Mission Flight Time 3:50 Hours:minutes
22. Performance: Mission
Engine: Lycoming L/TIO-540-W2A
Mission Completion Time: 3:50
Cruise Altitude: 7000'
Mission Breakdown
− 9 minute climb to 7000' altitude
− 3 hours 6 minutes at cruise
− 10 minutes to descend to 1000'
− 2 minute to climb back to 3000'
− 4 minutes from DCA to BWI
− 5 minute descent into BWI (+5 minutes loiter)
31.
Important Stability Derivatives:
Very Stable aircraft to account for engine
out case at takeoff
Stability and Control
Derivative Value
CMCL -0.1352
CyB -0.83897
ClB -0.002004
CnB 0.003895
32. Stability and Control
Short Period Oscillation
STABLE
Damping Ratio: 0.58
Period: 1.19 sec/cycle
Phugoid
STABLE
Damping Ratio: 0.178
Period: 56.97 sec/cycle
33. Stability and Control
Dutch Roll
STABLE
Damping Ratio: 0.170
Period: 1.29 sec/cycle
Roll
STABLE
Time to Half: 0.08 seconds
35. Ongoing Issue and
Future Work
Work on control surfaces to decrease
stall speed
Detailed structural design and wind
tunnel testing
36. Conclusion
Viable cross-country option as a private
passenger plane
Competitive with Beechcraft Baron 58
Exceeds Mission Requirements
4 months of hard work