This document provides a preliminary design summary for the SPARROW aircraft. It includes sections on mission requirements, cost analysis, design details, weight and balance, performance analysis, stability and control, and conclusions. The design meets FAR 23 standards for a normal category aircraft that can carry 6 passengers up to a 4 hour mission time. Total production cost is estimated at $449 million for 600 units. The aircraft is predicted to have a stall speed of 72 knots and a maximum speed of 218 knots. Stability derivatives and dynamic modes were calculated and indicate the design is stable in all flight conditions.

1. Preliminary Design:
SPARROW
AE 420-02
Professor J Martin
Dordick, Jacob ○ Hassan, Mahnoor ○ Kowolchuk, Robert ○
Lutz, Kurtis ○ Orren, Charlotte ○ White, Zack
3 December 2014

2. SPARROW

3. Introduction

Mission Requirements

Cost Analysis

Design

Weight and Balance

Drag Analysis

Performance Analysis

Stability and Control

Ongoing Issues and Future work

Conclusion

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

8. Cost Analysis:Ownership

Annual Cost of ownership (300 flight hours/year)

15 Year Loan @ 8.5% APR
Cost Category Value Units
Maintenance $1,260.00 Dollars
Storage $3,000.00 Dollars
Fuel (annual) $54,240.00 Dollars
Insurance (annual) $1,965.23 Dollars
Inspection (annual) $500.00 Dollars
Engine Overhaul $3000.00 Dollars
Loan Amount $1,000,000.00 Dollars
Interest Rate APR 8.50% Percent
Annual Loan Payment $118,168.75 Dollars
Total Annual Cost $182,133.97 Dollars
Hourly Cost $607.11 Dollars
Hourly Cost without loan $213.22 Dollars

9. Marketing Strategy

Air-International magazine
− Allows for greater market visibility than
only US market

5 year full-page adverts

$40,000 contract

10. Beech Baron 58

Retail Cost: $1.35
million

Operation Cost:$68,172.00

Cost/hour: $227.34
SPARROW

Retail Cost: $1.00
million

Operation Cost:$63,966.00

Cost/hour: $213.22
Comparison

11. Design (3-VIEW)

12. Design (3-VIEW)

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

14. Design: Club Seating

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

17. Weight and Balance

18. Weight and Balance

19. Weight and Balance

Aerodynamic Center located at 38.4% MGC at Cruise

CG limits are 30.8% MGC and 39.2% MGC

20. Drag Analysis: Drag Polar

CD :

Takeoff = 0.09648

Cruise = 0.03142

Landing = 0.10898

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)

23. Performance: Climb

Max ROC:
1749 fpm

ROC speed:
116 KTAS

24. Performance: Cruise

Cruise Speed:
198 KTAS

Cruise Speed
with padding:
194 KTAS

25. Performance: Max Speed

Max Speed:
218 KTAS

Max Speed
with padding:
214 KTAS

26. Performance: Descent

Min ROD:
634 fpm

ROD speed:
96 KTAS

27. Performance: Endurance
% Throttle Airspeed (KTAS) Range* (N. Mi.) Endurance
(hours:minutes)
100 % 218 1459 5:49
75 % 198 1550 6:48
40 % 156 1672 9:18
*Assuming Constant Altitude and Airspeed

28. Range: Global
Displaying maximum range at 75% throttle

29. Range: US and Europe
Displaying maximum range at 75% throttle
Departures from LAX, DAB Departure from London, Heathrow (LHR)

30. Stability and Control
Calculations for Stability and Control computed with SURFACES
model and verified with hand-calculation

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

34. Stability and Control

STABLE

Time to Half: 85.1 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

37. Questions?