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Charlie RushCharlie RushZheng WangZheng Wang
Brandon WeddeBrandon WeddeGreg WilsonGreg Wilson
Stephen BeirneStephen BeirneMiles HatemMiles HatemChris KesterChris Kester
Jim RadtkeJim Radtke
Preliminary Design ReviewPreliminary Design Review
AAE 451 Team VAAE 451 Team V
The Flying V Barn OwlThe Flying V Barn Owl
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 22
OutlineOutline1.1. MarketMarket2.2. Design RequirementsDesign Requirements3.3. Present ConceptPresent Concept4.4. SizingSizing5.5. AerodynamicsAerodynamics6.6. PerformancePerformance7.7. StructuresStructures8.8. Weight and BalanceWeight and Balance9.9. StabilityStability10.10.PropulsionPropulsion11.11.CostCost12.12.SummarySummary
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 33
GA Market ReviewGA Market Review
• Product Product – 4 Seat Single Engine Piston Aircraft for 4 Seat Single Engine Piston Aircraft for
Hobbyists, Training Fleets, and Fixed Base Hobbyists, Training Fleets, and Fixed Base OperatorsOperators• Powered by an Alternative FuelPowered by an Alternative Fuel
• Customer NeedsCustomer Needs– 100LL Replacement 100LL Replacement
• Current staple fuel for GA piston enginesCurrent staple fuel for GA piston engines• Production uncertain after 2015Production uncertain after 2015• Provides opportunity to be first to marketProvides opportunity to be first to market
– Petroleum fuel alternative for post peak oilPetroleum fuel alternative for post peak oil
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 44
Design RequirementsDesign Requirements
Design Design RequirementsRequirements
Team V Team V PlanePlane
T/O Distance <1500 1499
600 lb Payload 600
150 kts cruise speed 153
600 nm range 600
48”x46” cabin dim. 50”x50”
<2800 lb GTOW 2705
Acq. Cost <$300k $298,400
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 55
Current Design Current Design The “Barn Owl”The “Barn Owl”
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 66
15 16 17 18 19 20 21 222400
2500
2600
2700
2800
2900
3000Wing loading vs. GTOW
W/S [lbs/ft2]
GT
OW
[lb
s]
Design pointDesign point
Carpet Plot Carpet Plot Stall (57 kts)
Cruise (150 kts)
Climb (1300 fpm)
Takeoff (1500 ft)
Aspect Ratio (increments of 0.5)
Turn (n=2)
AR=6
AR=10
Note: Sizing was done with a predetermined 200 hp engine
Design SpaceDesign Space
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 77
I/O for Carpet PlotI/O for Carpet PlotNotable InputsNotable Inputs
Cd0Cd0 == 0.0260.026
Payload WeightPayload Weight == 600 [lbs]600 [lbs]
CL_maxCL_max == 1.61.6
Cruise AltitudeCruise Altitude == 8000 [ft]8000 [ft]
L/DL/D == 1010
BBhphpSFCSFC ==.439.439
[[lblb//hp*hrhp*hr]]
Stall SpeedStall Speed == 57 [kts]57 [kts]
Oswald efficiency Oswald efficiency factorfactor == 0.650.65
Prop DiameterProp Diameter == 74 [in]74 [in]
Prop efficency Prop efficency (cruise)(cruise) == 0.860.86
Prop efficency (climb)Prop efficency (climb) == 0.760.76
Notable OutputsNotable Outputs
GTOWGTOW == 2705 [lbs]2705 [lbs]
W/SW/S == 17.717.7
ARAR == 7.57.5
Takeoff (50 ft obs.)Takeoff (50 ft obs.) == 1499 [ft]1499 [ft]
Power / WeightPower / Weight == 0.0740.074
Sea Level Climb RateSea Level Climb Rate ==1351 1351
[fpm][fpm]
Wing AreaWing Area == 153 [ft153 [ft22]]
Turn Load FactorTurn Load Factor == 2.062.06
Cruise SpeedCruise Speed == 153 [kts]153 [kts]
Fuel WeightFuel Weight == 463 [lbs]463 [lbs]
Fuel VolumeFuel Volume == 63 [gal]63 [gal]
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 88
Drag Polar
0
0.001
0.002
0.003
0.004
0.005
0.006
0.007
0.008
0.009
0.01
0.011
0.012
0.013
0.014
0.015
-1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2 1.4
Cl
Cd
2412 Laminar
2412 Tripped
FVGA 5121 Laminar
FVGA 5121 Tripped
•FVGA 5121-12.1% thick•Designed using Genetic Algorithm •Laminar flow•Large Laminar bucket•Performance comparable to 2412 when tripped•30% less drag at cruise commpared to 2412•Low penalty at high Cl
New Airfoil DesignNew Airfoil Design
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 99
Wing Planform DesignWing Planform Design
-20 -15 -10 -5 0 5 10 15 200
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8Polynomial Twist for wing CL = 0.3
Distance along wing
Sec
tion
lift
* S
ectio
n co
rd
Wing twist distributionEliptical distribution
-20
2
-15
-10 -5 0 5 10 15
x
y
•Span = 33.87Span = 33.87•Taper ratio = 0.7Taper ratio = 0.7•Polynomial twistPolynomial twist•Close to elliptical lift distributionClose to elliptical lift distribution•1.51 degrees total twist1.51 degrees total twist
-1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8 1
2.6
2.8
3
3.2
3.4
3.6
3.8
4
4.2Twist Distribution for CL = 0.3
Distance along span (ratio)
Tw
ist
angl
e (d
eg)
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 1010
Cmarc AnalysisCmarc Analysis
• Used to acquire an accurate Used to acquire an accurate prediction of induced drag prediction of induced drag and parasite drag.and parasite drag.
• Detailed fuselage shaping to Detailed fuselage shaping to minimize interference dragminimize interference drag
• Bathtub style wing joint Bathtub style wing joint utilized, with smooth LE/TE utilized, with smooth LE/TE junctions, possible with junctions, possible with composite skin layovercomposite skin layover
• 8 deg tail upsweep to 8 deg tail upsweep to minimize wake interferenceminimize wake interference
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 1111
CCD0D0 Determination Determination
CCD0D0 = 0.022 = 0.022 (Sref = (Sref = 153)153)
• Lower than Cessna Lower than Cessna 172 @ 0.027172 @ 0.027
• The FVGA5121 airfoil The FVGA5121 airfoil is laminar at low CLis laminar at low CL
• Incompressible flight Incompressible flight envelopeenvelope
• No wing strutsNo wing struts• Aerodynamic fuselageAerodynamic fuselage• Close to elliptical Close to elliptical
loadingloading
3D Drag Polar
0
0.05
0.1
0.15
0.2
0.25
0.3
0.35
0.4
-2.5 -2 -1.5 -1 -0.5 0 0.5 1 1.5 2 2.5
CL
CD
Barn Ow l
AR = 9.6
Poly. (Barn Ow l)
Poly. (AR = 9.6)
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 1212
L/DL/DMAXMAX Determination DeterminationCmarc 3D L/D vs CL
-15
-10
-5
0
5
10
15
-0.75 -0.5 -0.25 0 0.25 0.5 0.75 1
CL
L/D
L/DL/DMAXMAX = 10.4 = 10.4
• This is because the This is because the FVGA5121 airfoil is FVGA5121 airfoil is laminar at low CLlaminar at low CL
• Most efficient cruise at Most efficient cruise at 185 ft/s (109 kts)185 ft/s (109 kts)
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 1313
3D Lift Curve3D Lift CurveLift Curve
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
-5 -3 -1 1 3 5 7 9 11 13 15
Alpha
CL
Wings oriented to have a level fuselage at max cruise speed.Wings oriented to have a level fuselage at max cruise speed.
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 1414
PerformancePerformance
0 20 40 60 80 100 120 140 160-3
-2
-1
0
1
2
3
4
V-n Diagram
Ve [Knots]
n
Design Limit Design Limit LoadLoad
3.8 g 3.8 g
per FAR 23.337per FAR 23.337
FAR Gust FAR Gust Velocities Under Velocities Under
20,000 ft20,000 ft
50 ft/s @ V50 ft/s @ VCruise Cruise
25 ft/s @ V25 ft/s @ VDive Dive
Design Loading
Gust Loading
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 1616
StructureStructure• Material SelectionMaterial Selection
– Aluminum frame with fiberglass skin selectedAluminum frame with fiberglass skin selected– Cost savings expectedCost savings expected– Slight weight savings achievedSlight weight savings achieved
• FrameFrame– ““Big bones” approachBig bones” approach– Manufacturing cost reduced due to fewer Manufacturing cost reduced due to fewer
components and advanced joiningcomponents and advanced joining
• SkinSkin– Fiberglass cured in large segmentsFiberglass cured in large segments– Segments bonded to frameSegments bonded to frame
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 1717
Structural LayoutStructural Layout
C-ChannelsI-Beam Spar
Ribs
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 1818
Spar CarrythroughSpar Carrythrough• Spar located Spar located
at front of rear at front of rear seatsseats
• Spar does not Spar does not hinder cabin hinder cabin comfortcomfort
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 1919
Component WeightsComponent Weights
• Began with Began with Raymer’s Statistical Raymer’s Statistical Group Weights Group Weights methodmethod
• Replaced with Replaced with known or calculated known or calculated weightsweights– EngineEngine– PropellerPropeller– WingsWings– FuselageFuselage
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 2020
Component WeightsComponent Weights• EngineEngine
– Total installed weight from DeltaHawkTotal installed weight from DeltaHawk– Includes all pumps, turbocharger, lines, Includes all pumps, turbocharger, lines,
exhaust, and mountexhaust, and mount– 390 lbs390 lbs
• PropellerPropeller– Off the ShelfOff the Shelf– 51 lbs51 lbs
20
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 2121
Wing SizingWing Sizing• Cross-sectional optimization along spanCross-sectional optimization along span• Design Variables:Design Variables:
• Constrained by:Constrained by:Allowable StressesAllowable Stresses Upper Skin Upper Skin
BucklingBuckling
Spar Web BucklingSpar Web Buckling Damage ToleranceDamage Tolerance
Skin ThicknessSkin Thickness Spar Web Spar Web ThicknessThickness
Spar Cap SizeSpar Cap Size
Stringer AreaStringer Area Spar Cap Spar Cap ThicknessThickness
Rib SpacingRib Spacing
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 2222
Wing SizingWing Sizing
• Validation of sizing algorithmValidation of sizing algorithm– Raymer statistical weight:Raymer statistical weight: 302 lbs302 lbs– All-aluminum wing optimization:All-aluminum wing optimization: 300 lbs300 lbs
• Our designOur design– S2-glass/epoxy skinS2-glass/epoxy skin– New weight:New weight: 286 lbs286 lbs– Difference due to minimum gauge skin over Difference due to minimum gauge skin over
outer 1/3 spanouter 1/3 span
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 2323
FuselageFuselage
• Preliminary model created and Preliminary model created and analyzed with I-DEASanalyzed with I-DEAS
• Ability to sustain limit load verifiedAbility to sustain limit load verified
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 2424
Weight and BalanceWeight and Balance
• Design Design gross weight gross weight from sizingfrom sizing– 2705 lbs2705 lbs
• Detailed Detailed gross weight gross weight predictionprediction– 2694 lbs2694 lbs
Component Dist. from nose [in.] Weight [lbs]Engine 30 390Prop/ Spinner 6 51Avionics 81 51Fuel System 123 47Electrical System 60 130Wing 129 286Flight Controls 160 41Hydraulics 138 3fuel 123 463Front Seat PAX 106 300Rear Seat PAX 143 300Furnishings 125 92Fuselage 160 241Horiz Tail 321 98Vert Tail 321 21Main Gear 138 151Nose Gear 44 29
Total Weight 2694 lbsCenter of mass 117 in. from nose
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 2525
CG Travel
0
500
1000
1500
2000
2500
3000
109 111 113 115 117 119
CG position (in)
Wei
gh
t
C.G. and Static StabilityC.G. and Static Stability• Static Margin with full loadStatic Margin with full load 10.6%10.6%• Static Margin with no fuel, 1 pilotStatic Margin with no fuel, 1 pilot 19.6%19.6%
A Empty Fuel, Rear PAXB Full Fuel, Rear PAXC Full Fuel, all PAXD Full FuelE Full Fuel, Front PAXF Empty Fuel, 2 Front PAXG Empty Fuel, 1 Front PAXH Empty
GF
ED
A
C
B
H
20% S.M. 10% S.M.
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 2626
Fuel SelectionFuel Selection
• Bio-diesel chosen as alternative fuelBio-diesel chosen as alternative fuel• Reasons chosen:Reasons chosen:
– BSFC of 0.439 lbs/(hp*hr) is bested only BSFC of 0.439 lbs/(hp*hr) is bested only by hydrogenby hydrogen
– Most developed technology of all of the Most developed technology of all of the proposed alternative fuelsproposed alternative fuels
– Requires only minor modifications to Requires only minor modifications to available piston enginesavailable piston engines
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 2727
Engine DesignEngine Design
• Engine Requirements:Engine Requirements:– No more than 200 hp to remain “low No more than 200 hp to remain “low
performance”performance”– Meet dimension constraints for the nose Meet dimension constraints for the nose
of the aircraftof the aircraft– Powerful enough to meet cruise speed Powerful enough to meet cruise speed
target target • An existing diesel aircraft engine An existing diesel aircraft engine
meets our requirements meets our requirements – Development cost savingsDevelopment cost savings
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 2828
Engine DesignEngine Design
• Deltahawk V4 DH200V4 Deltahawk V4 DH200V4 • Rated PowerRated Power
– 200 hp200 hp
• Total installed Weight Total installed Weight – 390 lbs390 lbs
• Dimensions:Dimensions:– 30x23x32 (inches)30x23x32 (inches)
• CostCost– $32,450$32,450
• Meets all desired Meets all desired requirementsrequirements
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 2929
PropellerPropeller
• Existing PropellerExisting Propeller– 2 Blade, constant Speed2 Blade, constant Speed– Hartzell HC-C2YK-1 ( )/7666A-2Hartzell HC-C2YK-1 ( )/7666A-2
• Same Propeller as Piper ArrowSame Propeller as Piper Arrow– HP 200HP 200– RPM 2700RPM 2700– Cruise 145 ktsCruise 145 kts
• Specs.Specs.– Max constant HP = 250Max constant HP = 250– Max constant RPM = 2700Max constant RPM = 2700– Diameter = 74”Diameter = 74”
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 3030
• Three cost estimating relationships:Three cost estimating relationships:– GA Plane LibraryGA Plane Library– Modified RAND DAPCAModified RAND DAPCA– Airframe Weight RelationshipAirframe Weight Relationship
• Weighted average yields purchase price of Weighted average yields purchase price of ~$298,400.00~$298,400.00
• RTD&E Break-Even set by DAPCA model at RTD&E Break-Even set by DAPCA model at ~5 years (~2000 planes)~5 years (~2000 planes)– Reasonable with market that breakeven would Reasonable with market that breakeven would
be met.be met.
Acquisition CostAcquisition Cost
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 3131
Acquisition CostAcquisition CostPurchase Price v DAPCA CER v AMPR CER
$-
$100,000.00
$200,000.00
$300,000.00
$400,000.00
$500,000.00
$600,000.00
$700,000.00
1500 2000 2500 3000 3500 4000
GTOW (lbs)
Acq
uis
itio
n C
ost
Purchase Price
AMPR ($277.05/lb)
DAPCA*60%
Expon. (AMPR)
Expon. (DAPCA)
Expon. (Purchase Price)
Barn Owl
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 3232
• Compiled data from web resources Compiled data from web resources (Company websites; Plane Quest)(Company websites; Plane Quest)
• Allows for current fuel pricesAllows for current fuel prices– 100LL ~ $4.27/gal100LL ~ $4.27/gal– B100 ~ $3.00 - $3.25/galB100 ~ $3.00 - $3.25/gal
• Gives Total Operating Cost of Gives Total Operating Cost of ~$81/hr (2006 USD) ~$81/hr (2006 USD)
Operating CostsOperating Costs
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 3333
Operating CostsOperating CostsOperating Costs v. GTOW
R2 = 0.8677
R2 = 0.9155
R2 = 0.6407
$-
$20.00
$40.00
$60.00
$80.00
$100.00
$120.00
$140.00
$160.00
$180.00
1500 2000 2500 3000 3500 4000
GTOW (lbs)
Op
erat
ing
Cos
ts
Variable DOC/hrFixed DOC/hrTotal Operating Costs/hrBarn Owl (GTOW)Expon. (Total Operating Costs/hr)Expon. (Variable DOC/hr)Expon. (Fixed DOC/hr)
Barn Owl
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 3434
Operating CostsOperating Costs
• How does ~$81/hr compare?How does ~$81/hr compare?
*Determined using DOC v. GTOW Relationship*Determined using DOC v. GTOW Relationship
Plane Type DOC/hr variable DOC/hr fixed Total Cost/Hr
Diamond DA 40 $ 55.00 $ 15.00 $ 70.00
Flying V Barn Owl $ 55.00 $ 26.00 $ 81.00
Cessna 172S $ 64.00 $ 26.00 $ 90.00
Cessna 182s $ 87.00 $ 44.00 $ 131.00
Cirrus SR 22* $ 99.00 $ 41.00 $ 141.00
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 3535
Life Cycle Cost EstimateLife Cycle Cost Estimate• Est. Cost for Owner over 12 year span of Est. Cost for Owner over 12 year span of
time?time?Purchase Price $ 298,400.00 Notes:
RTD&E/unit $ 53,712.00 ~20% purch./1.1
Production/unit $ 217,832.00 ~80% purch./1.1
O&M (total over yrs.) $ 767,426.67 ~500 FH/yr.
Fuel $ 234,000.00 B100=$3/gal; 13 gal/FH
Maintenance $ 240,000.00 MMH/FH=0.5; $/MMH=80.00
Insurance $ 24,866.67 ~0.7% purch price/year
Depreciation {f(age)} $ 268,560.00 (purch/12 *age), for age <12
Disposal $ (29,840.00)
Life Cycle Cost $ 1,035,986.67
• Saves Owner over $100,000 than if same plane were Saves Owner over $100,000 than if same plane were powered by 100LL at current prices! (LCC $1,136k)powered by 100LL at current prices! (LCC $1,136k)
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 3636
Design RequirementsDesign Requirements
Design Design RequirementsRequirements
Team V Team V PlanePlane
T/O Distance <1500 1499
600 lb Payload 600
150 kts cruise speed 153
600 nm range 600
48”x46” cabin dim. 50”x50”
<2800 lb GTOW 2705
Acq. Cost <$300k $298,400
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 3737
Comparison to Current Comparison to Current CompetitionCompetition
Range @ 45% power (nm) - 638 - 971 - - -Range @ 55% power (nm) - - 930 - - - -Range @ 60% power (nm) 687 - - - - - -Range @ 75% power (nm) - 518 - - 600 700 600Range @ 80% power (nm) 580 - 773 615 - - -Range @ 88% power (nm) - - - - - - -
Power (bhp) 160 180 230 235 180 310 200Power loading (lbs/hp) 15.3 14.2 13.5 13.2 14.1 10.9 13.5
Climb at sea level (fpm) 720 730 924 1040 1070 1304 1351Cruise speed (kts) 122 124 145 159 147 185 153
Stall speed, flap up (kts) 47 48 49 49 49 61 57Balanced field length (ft) 1685 1630 1514 1385 1027 1574 1499
GTOW (lbs) 2457 2558 3100 3112 2535 3400 2705Usefull load (lbs) 818 895 1140 1037 906 1150 1063
Wing area (sf) 174 174 174 174 145 145 153Wing loading (lbs/sf) 14.1 14.7 17.8 17.8 14.5 23.4 17.7
Purchase Price ($) $172k $180k $326k $355k $259k $350k $298k
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 3838
SummarySummary
• The Barn Owl will be a successful The Barn Owl will be a successful alternative fuel aircraftalternative fuel aircraft
• The current design is feasible and meets The current design is feasible and meets all requirementsall requirements
• Next steps:Next steps:– Controls sizing & dynamic stabilityControls sizing & dynamic stability
– Refine and consolidate structure, aerodynamic, Refine and consolidate structure, aerodynamic, and layout modelsand layout models
– Detailed production cost estimationDetailed production cost estimation
Charlie RushCharlie RushZheng WangZheng WangBrandon WeddeBrandon WeddeGreg WilsonGreg Wilson
Stephen BeirneStephen BeirneMiles HatemMiles HatemChris KesterChris Kester
Jim RadtkeJim Radtke
Preliminary Design ReviewPreliminary Design Review
AAE 451 Team VAAE 451 Team V
The Flying V Barn OwlThe Flying V Barn Owl
This Concludes the…This Concludes the…
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 4040
Slide left intentionally blank… except for this.Slide left intentionally blank… except for this.
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 4141
ReferencesReferences• Hartzell Propeller Data. “Hartzell Propeller Data. “TYPE CERTIFICATE DATA SHEET NO. P-TYPE CERTIFICATE DATA SHEET NO. P-
920 920 Available Available <http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rg<http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMM akeModel.nsf/0/akeModel.nsf/0/aac7773a13ad299186257114005a5cd0/$FILE/P-aac7773a13ad299186257114005a5cd0/$FILE/P- 920.pdf>. 920.pdf>.
• Plane QuestPlane Quest. Plane Quest Website. Cited 4/1/06. Available . Plane Quest Website. Cited 4/1/06. Available <http://www.planequest.com/operationcosts/default.asp>.<http://www.planequest.com/operationcosts/default.asp>.
• Raymer, Daniel. Raymer, Daniel. Aircraft Design a Conceptual Approach. 3Aircraft Design a Conceptual Approach. 3rdrd Ed. Ed. 1999. 1999. AIAA. Reston, VA. AIAA. Reston, VA.
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 4444
Wing Structure Sizing Wing Structure Sizing ResultsResults
0 50 100 150 2000.04
0.05
0.06
0.07
0.08
0.09
0.1
0.11
0.12
0.13
0.14Spar Web Thickness
Span location [in]
Th
ickn
ess
[in
]
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 4545
Wing Structure Sizing Wing Structure Sizing ResultsResults
0 50 100 150 2000
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1
1.1Spar Cap Thickness
Span location [in]
Th
ickn
ess
[in
]
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 4646
Wing Structure Sizing Wing Structure Sizing ResultsResults
0 50 100 150 2001
1.1
1.2
1.3
1.4
1.5
1.6
1.7Spar Cap Width
Span location [in]
Wid
th [i
n]
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 4747
Wing Structure Sizing Wing Structure Sizing ResultsResults
0 50 100 150 2000.03
0.04
0.05
0.06
0.07
0.08
0.09Skin Thickness
Span location [in]
Th
ickn
ess
[in
]
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 4848
Wing Structure Sizing Wing Structure Sizing ResultsResults
0 50 100 150 2000
0.02
0.04
0.06
0.08
0.1
0.12
0.14
0.16Stringer Area (of each stringer)
Span location [in]
Are
a [i
n2 ]
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 4949
PropellerPropellerParameter Value Units Notes Parameter Value Units Notes
density 2.38E-03 slug/ft^3 h=0 V_tip 872.26 fps must be less than (a*.85)speed of sound (a) 1116.40 ft/s h=0 V_tip_helix 908.26 fps must be less than (a*.85)a * .85 948.94 ft/s h=0
Advance Ratio 0.91 --Two Bladed Propeller? yes -- yes or no (no->b= 3)
Power Coefficient 0.06 --V= Forward Velocity 150.00 kts Thrust Coefficient 0.13 -- Raymer 13.13
172.62 smi/h Speed-Power Coefficient 3.39 -- Raymer 13.14253.17 ft/s
Activity Factor per blade 106.4 -- Raymer 13.15SBHP= 200.00 lb-f^2/s^3
Two Blade Diameter 6.17 ft Raymer 10.23D=Drag 630.67 lb-ft/s^2 74.04 inT=Thrust 630.67 lb-ft/s^2 Three Blade Diameter 5.64 ft Raymer 10.24
67.69 inN=RPM 2700.00 1/min Delta Hawk website
45.00 1/s Tip Ground Clearance 1.12 ftMinimum Tip Clearance 0.00 ft random parameter?
Cruise Efficiency 0.86 -- ~.85TO/Land Efficiency 0.70 -- ~.7 for fixed Forward Flight Thrust 630.67 lb-ft/s^2 Raymer 13.17
Static Thrust 987.38 lb-ft/s^2Shaft Ground Clearance 4.20 ft
Propeller lambda 0.80 -- Crossley says ~.8
root chord of prop. 0.50 ft guess
4/18/20064/18/2006 AAE 451 Team VAAE 451 Team V 5050
PropellerPropeller
Two and Three Blades
60
65
70
75
80
85
90
100 120 140 160 180 200 220 240 260 280 300 320 340
HP
Dia
met
er (
in)
Two Blades
R: Two Blade
Three Blades
R: Three Blades
Barn Owl
Two and Three Blades
70
71
72
73
74
75
76
77
78
79
80
2350 2400 2450 2500 2550 2600 2650 2700 2750
RPM
Dia
met
er (
in)
Two Blades
Three Blades
Barn Owl