11

AAE 451 Senior Aircraft Design Spring 2006AAE 451 Senior Aircraft Design Spring 2006Preliminary Design ReviewPreliminary Design Review

Group VIGroup VI

Team Members:Team Members:

John CollinsJohn CollinsChad DavisChad DavisChris FlesChris Fles

Danny Sze Ling LimDanny Sze Ling LimJustin RohdeJustin RohdeRyan SchulzRyan SchulzRonald WongRonald Wong

Yusaku YamashitaYusaku Yamashita

22

Market ReviewMarket Review Target: Business Market Target: Business Market

• Corporate Flight DepartmentsCorporate Flight Departments• Air Taxi and Air CharterAir Taxi and Air Charter• Fractional SharesFractional Shares

Profit OpportunitiesProfit Opportunities• Air taxi, fractional ownership expected to more than Air taxi, fractional ownership expected to more than

double in coming decadedouble in coming decade• Increasing incentive for use by small businessIncreasing incentive for use by small business• Strong business aviation growth expected in European Strong business aviation growth expected in European

and Asian markets over next 20 yearsand Asian markets over next 20 years

33

Design RequirementsDesign Requirements Cabin Capacity - 2 Crew + 6 PassengersCabin Capacity - 2 Crew + 6 Passengers Cruise Range - 600 nmCruise Range - 600 nm Cruise Speed - 250 ktsCruise Speed - 250 kts T.O./Landing Distance - 2,100 ftT.O./Landing Distance - 2,100 ft Acquisition Cost - $1.8 MillionAcquisition Cost - $1.8 Million D.O.C./Hour - $550D.O.C./Hour - $550

Taxi

Take-off 2100 ft. Runway

Climb

Cruise

Descend for Landing

600 nm range Reserve

Execute Missed Landing Land 2100 ft. Runway

Begin Landing

Pilots (150 lbs. each)Pilots (150 lbs. each) Passengers (200 lbs. each)Passengers (200 lbs. each) 1500 lbs. Total Payload1500 lbs. Total Payload

200 nmcruise

+45 minloiter

V-cruise = 250 kts@ 20,500 ft

44

Present ConceptPresent Concept

55

SizingSizing Major parametersMajor parameters

• P/W = 0.1716 hp/lbP/W = 0.1716 hp/lb• W/S = 32 lb/ftW/S = 32 lb/ft• AR = 7.6AR = 7.6• TOGW = 6500 lbTOGW = 6500 lb• λλ = 0.4 = 0.4

CostsCosts• Acquisition = $1.725 MillionAcquisition = $1.725 Million• Direct Operating = $450/HourDirect Operating = $450/Hour

Carpet Plot ApproachCarpet Plot Approach• We/Wo – Regression:We/Wo – Regression:• P/W, W/S, AR, V-max, TOGWP/W, W/S, AR, V-max, TOGW• We/Wo – Verified:We/Wo – Verified:• Component Weight AnalysisComponent Weight Analysis

20 22 24 26 28 30 32 34 36 38 404500

5000

5500

6000

6500

7000

7500

8000

8500

0.1400 P/W

0.1463 P/W

0.1547 P/W

0.1632 P/W

0.1716 P/W

0.1800 P/W

Aspect Ratio = 7.6

Wing Loading (lbs/ft2)

Airc

raft

Gro

ss W

eigh

t (lb

s)

Design Point:P/W = 0.1716 hp/lbW/S = 32 lb/ft2

V-max = 250 kts

Takeoff Distance = 2100 ft

66

Concept ComparisonConcept Comparison

  Concept 15Socata TBM

700[i]

Pilatus PC 12[ii]

TOGW 6500 lb 6578 lb 9920 lb

W/S 32 lb/ft² 33.9 lb/ft² 35.7 lb/ft²

Wing Area 212 ft2 193.8 ft2 277.8 ft2

AR 7.6 8.97 9.85

Wing Span 40 ft 41ft 7 in 52 ft 3 in

P/W 0.1716 0.106 0.121

STO 2100 ft 2133 ft 2300 ft

VCruise 250 kts 243 kts 232 kts

Acquisition Cost $1.725 M $ 2 M $ 2.8 M

D.O.C. $450/hr $425/hr $400/hr

Requirements Concept 15

Capacity2 Crew

6 Passengers2 Crew

6 Passengers

Range 600 nm600 nm

w/ 200 nm divert 45 min loiter

Cruise Speed

250 kts250 kts

Vbest = 225 ktsVmax = 265 kts

Acquisition Cost

$1.8 M $1.725

D.O.C. $550/Hour $450/Hour

77

AerodynamicsAerodynamics Wing Airfoil Selection CriteriaWing Airfoil Selection Criteria

• High CHigh Clmaxlmax (Required C(Required Clmaxlmax=1.5)=1.5)• High L/DHigh L/D (Required L/D = 11.66)(Required L/D = 11.66)• Low CLow Cdd

• Low CLow Cm.25 m.25 at cruiseat cruise

• NACA 22012 was selected as it can meet the requirements at a lower drag penalty NACA 22012 was selected as it can meet the requirements at a lower drag penalty than NACA 4412than NACA 4412

• 20 degree deflection of plain flaps located at ¾-chord were used during takeoff to 20 degree deflection of plain flaps located at ¾-chord were used during takeoff to augment the Caugment the Cll required required

Wing - NACA 22012Wing - NACA 22012 Take off with Take off with 20deg flaps20deg flaps

CruiseCruise

CCLL 1.6221.622 0.220.22

CCm.25m.25 -0.207-0.207 -0.007-0.007

88

Drag Polar

0

0.05

0.1

0.15

0.2

0.25

0.3

0.35

0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8

Cl

Cd

Cruise Take Off with 20deg flap

-0.5

0

0.5

1

1.5

2

-10 -5 0 5 10 15 20 25

AoA

Cl

No Flaps With Flaps

Drag Polar

Cl – alpha curve with and without flaps

99

Canard AirfoilCanard Airfoil• NACA 2212 was selected as it NACA 2212 was selected as it

provides adequate Cprovides adequate CLL at cruise to at cruise to meet the L/D requirement.meet the L/D requirement.

Winglet AirfoilWinglet Airfoil• NACA 4412 was selected based on NACA 4412 was selected based on

Raymer’s textbook, “the camber Raymer’s textbook, “the camber of the winglet must be greater of the winglet must be greater than that of the wing to ensure than that of the wing to ensure sufficient side force.”sufficient side force.”

Canard - Canard - NACA 2212NACA 2212

Take offTake off CruiseCruise

CCll 0.4370.437 0.1850.185

CCm.25m.25 -0.039-0.039 -0.034-0.034

Aerodynamics – Wing SelectionAerodynamics – Wing Selection

Winglet - Winglet - NACA 4412NACA 4412

CCll 0.2760.276

CCm.25m.25 -0.098-0.098

1010

Drag EstimationDrag EstimationCCd0d0 WingsWings CanardCanard WingletsWinglets FuselageFuselage

Take-offTake-off 0.01770.0177 0.00240.0024 0.000720.00072 0.001020.00102

CruiseCruise 0.01540.0154 0.00210.0021 0.000620.00062 0.00090.0009

Fuselage UpsweepFuselage Upsweep Landing GearsLanding Gears

Misc. DragMisc. Drag0.002580.00258 0.00260.0026

Total Parasite Total Parasite DragDrag Total DragTotal Drag

Take-offTake-off 0.0360.036 0.1480.148

CruiseCruise0.0220.022 0.0260.026

Note: Figures might not add up due to rounding error

1111

Summary of Aerodynamic Summary of Aerodynamic PerformancePerformance

CCLmaxLmax = 1.622 = 1.622 CCLcruiseLcruise = 0.320 = 0.320 L/D = 12.26L/D = 12.26 CCdd cruise = 0.026 cruise = 0.026 CCdd takeoff = 0.148 takeoff = 0.148

1212

V-n DiagramV-n DiagramV-n Diagram

-1.5

-1

-0.5

0

0.5

1

1.5

2

2.5

3

V (kts)

n (

Lo

ad

Fa

cto

r)

Vstall = 68 kts

Vcruise = 250 kts

Vdive = 280 kts

VAOA = 115.65 kts

1313

StructuresStructures

Box Beam Analysis ProgramBox Beam Analysis Program• Compares Different MaterialsCompares Different Materials• Includes TolerancesIncludes Tolerances

DeflectionDeflection BucklingBuckling ShearShear

• Program Minimizes Material UsedProgram Minimizes Material Used

Loading ConditionsLoading Conditions• Trapezoidal Lift DistributionTrapezoidal Lift Distribution• Large Bending Moment at Wing RootLarge Bending Moment at Wing Root• Lateral Forces Applied on WingletLateral Forces Applied on Winglet

1414

StructuresStructures

ResultsResults• Aluminum CompositeAluminum Composite

140 lb Supporting Structure / Wing140 lb Supporting Structure / Wing

• AluminumAluminum 170 lb Supporting Structure / Wing170 lb Supporting Structure / Wing

• Loading Factor – 2.0 Before FailureLoading Factor – 2.0 Before Failure• Further Optimization RequiredFurther Optimization Required

1515

Component Weight Breakdown Component Weight Breakdown (Numbers)(Numbers)

ComponentsComponents Weight (lb)Weight (lb)

Wing 400.00

Canard 150.15

Winglets 70.00

Fuselage 168.87

Landing gear Nose 31.27

Main 184.67

Installed Engine 800.00

All else 1536.70

Total Empty Weight 3321.66

ComponentsComponents Weight (lb)Weight (lb)

Total Empty Weight 3321.66

Fuel 1665

Crew (pilot + copilot) 300

Passengers (6 PAX) 1200

Gross Takeoff Weight (GTOW)

6486.66

1616

Component Weight Breakdown Component Weight Breakdown (empty)(empty)

Total Empty Total Empty WeightWeight

= 3321.6 lb= 3321.6 lb

1717

Component Weight Breakdown Component Weight Breakdown (Gross takeoff Configuration)(Gross takeoff Configuration)

Gross Gross Takeoff Takeoff WeightWeight

= 6500 lb= 6500 lb

1818

Component Weight DistributionComponent Weight Distribution

1919

CG Travel and Static MarginCG Travel and Static Margin

2020

PropulsionPropulsion Cruise SFC – 0.553Cruise SFC – 0.553 Installed Power – 1000 hpInstalled Power – 1000 hp Similar Engine - PT6A-60ASimilar Engine - PT6A-60A

PropellerPropeller• Diameter - 8 ftDiameter - 8 ft• 4 Blades4 Blades

• ηηpp Max Speed – 0.91 Max Speed – 0.91

• Variable PitchVariable Pitch Feathering and ReversibleFeathering and Reversible

PT6A – Large – www.unitedtubrine.com

2121

Propulsion ConsiderationsPropulsion ConsiderationsHorsepower vs. Engine Weight

-from 'Total' Tab -note: outliers are removed

y = 1.8211x0.7915

R2 = 0.8024

0

200

400

600

800

1000

1200

0 500 1000 1500 2000 2500 3000

Horsepower [shp]

Wei

ght

[lbs

]

Turboprops

Power (Turboprops)

Horsepower vs. Engine Sizes-from 'Total' Tab

y = 6.1832x0.3184

y = 4.8598x0.2375

0

20

40

60

80

100

120

0 500 1000 1500 2000 2500 3000

Horsepower [shp]

Leng

th, D

iam

ete

r [in

]

Length

Diameter

Power (Length)

Power (Diameter)

Horsepower vs. SFC-from 'Total' Tab -note: outliers are removed

y = 0.8214x-0.0573

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

0 500 1000 1500 2000 2500 3000

Horsepower [shp]S

FC

[lb

/sh

p-h

r]

Turboprops

Power (Turboprops)

2222

Fuel ConsiderationsFuel Considerations

BioJet FuelBioJet Fuel• First Created by University of North DakotaFirst Created by University of North Dakota• Heating Value – 16,000 (btu/lb)Heating Value – 16,000 (btu/lb)• Specific Gravity – 0.87-0.89Specific Gravity – 0.87-0.89• TSFC – 0.553 TSFC – 0.553 *Approximate*Approximate

• Compatible with Current TurbinesCompatible with Current Turbines• Engine Heat Used to Prevent GellingEngine Heat Used to Prevent Gelling

2323

CostCost

AcquisitionAcquisition• $1.725 Million$1.725 Million• Regression of Similar Regression of Similar

AircraftAircraft• Based on:Based on:

Gross WeightGross Weight Aircraft PerformanceAircraft Performance

DOCDOC• $450 / Hour$450 / Hour• Component AnalysisComponent Analysis

Parts - $19 4%

Fuel - $12227%

Crew - $24154% Labor - $70

15%

2424

Competing AircraftCompeting Aircraft

Acquisition CostAcquisition Cost• Baron G58 - $1.22 MBaron G58 - $1.22 M• Adam A500 - $1.25 MAdam A500 - $1.25 M• Pilatus PC-12 - $2.80 MPilatus PC-12 - $2.80 M• Concept 15 - $1.725Concept 15 - $1.725

D.O.C./HourD.O.C./Hour• Baron G58 - $288Baron G58 - $288• Adam A500 - $450Adam A500 - $450• Pilatus PC-12 - $400Pilatus PC-12 - $400• Concept 15 - $450Concept 15 - $450

2525

Production CostsProduction CostsRecurring Costs• Manufacturing• Materials• Quality Control• Development Support• Engines• Avionics• Inventory

Non-Recurring Costs • Engineering/Design• Tooling• Flight Testing

• DAPCA model (Raymer) used to estimate costs- Adjusted to current dollar value- Weighting used for composite components- Learning curve applied to various recurring man-hours as production progresses

2626

Production CostsProduction Costs

• Significant decrease in unit cost as production increases• Acquisition cost of $1.725M; includes 30% profit• Break even point ~ 210 aircraft

2727

Production Cost BreakdownProduction Cost Breakdown

• Engineering, development, and testing decrease substantially in percentage as production increases

• Manufacturing, materials costs begin to level off

2828

Production Cost BreakdownProduction Cost Breakdown

2929

SummarySummary

Concept 15Concept 15• Design Requirements AchievedDesign Requirements Achieved

Mission Requirements MetMission Requirements Met Stable Aircraft (Positive Static Margin)Stable Aircraft (Positive Static Margin) Aerodynamic Properties PossibleAerodynamic Properties Possible

• Need Wind Tunnel Verification (Better Need Wind Tunnel Verification (Better Approximations)Approximations)

Competitive Cost AchievedCompetitive Cost Achieved

3030

QuestionsQuestions