Heavy Lift Cargo Plane Progress PresentationMatthew Chin, Aaron Dickerson Brett J. Ulrich, Tzvee Wood

November 4th, 2004Group #1 Project #3

Presentation OutlineReview of Project Objectives & DeliverablesEarly Design ConceptsComputer Software ImplementationData DigitalizationWINFOIL EvaluationsEngineering Equation Solver CalculationsDesign ConceptsWingLanding GearTailPropSchedule Update

Project ObjectivesCompete in SAE Aero East CompetitionApply areas of Mechanical Engineering education to a real life problem:DynamicsFluid MechanicsModeling & SimulationAnalysis of Stresses

Project ObjectivesDynamics/Analysis of stressesForce of drag, weight, and gravity on the wing/fuselage

Fluid MechanicsUsed in analysis of airfoil

Modeling & SimulationFor CAD models of wing, fuselage, landing gear

Anticipated DeliverablesFinished calculationsFinal wing selectionSketches of the final designCAD drawings - wing, fuselage, landing gearProjected construction budgetParts order

Problems To Watch Out ForIdeal design needs to be able to be actually constructedStability of construction so that the plane does not fall apart on landingTime management for constructionPrevious team only used one design did not iterateMore practice on shrink wrap coating procedure for wing

Early Design ConceptsBiplanes originally popular for increased lifting capacityAt this scale the effect of the additional wing is not worth the additional weight and construction cost

Early Design ConceptsDual wing plane also consideredInitially thought to be able to produce significantly more lift than standard monoplaneAlignment of wings can produce major parasitic losses if done improperly

Early Design ConceptsFlying wing early popular conceptOne large wing has significantly larger area than standard monoplanePossibly difficult to build and transportStill under consideration

Early Design Concepts

Data DigitalizationSAE Documentation Provides Data for LMN-1 Airfoil (similar to Selig 1223, Liebeck LD-X17A and other RC aircraft)Data includes:The dependence of CL on Aspect Ratio and Angle of AttackViscous drag due to liftRatio of Thrust to Static Thrust vs. Speed

Data DigitalizationThe following graphs are provided in the aforementioned white paper

Data DigitalizationLarge samples of data points were recorded and entered into MATLAB

manuallyIn the event you missed it, theyre computerized now!

Wing AnalysisWith WINFOILMonoplane first examinedFirst sought to examine the effects of different designs on L/D Ratio:Constant ChordTaperedSwept Back TaperedFor each design L/D ratio is the sameCan be easily seen from CL CDCL=L/(0.5*AP*V2*)CD=D/(0.5*AP*V2*)

Wing AnalysisWith WINFOILSelected Eppler 193 Mod WingPrevious designsSuggestion of Senior Design CoordinatorHigher CL than other airfoils such as NACA 6409Relatively easy to buildNo fine trailing edgeReasonable ThicknessDecided against use of Swept Back Tapered Too many variablesRequires too much precisionTapered Wing is still under consideration

Wing AnalysisWith WINFOIL

Wing AnalysisWith WINFOIL

Wing AnalysisWith WINFOILEffect of wing taper ratio on various performance characteristics examinedAssumptions:Wing holds entire plane weight assumed to be 7lbsMax 2hpNo fuselage accounted for

Wing AnalysisWith WINFOILFlying Wing AnalysisLike the Monoplane L/D ratio is independent of wing design for wings of same area

Wing AnalysisWith WINFOIL

Wing AnalysisWith WINFOILWINFOIL 3D RenderingStill experiencing problems exporting from WINFOIL to CAD programs for tapered wings

Wing Features Being ConsideredHoerner Plates reduce tip lossesDihedral Angle reduces chance of stall under banked conditionsMay not be necessary for a 60 wingspan

Addl Computer AnalysisPreviously generated MATLAB curve fits utilized in EES for calculationsEntire current EES model included in presentation handouts

Addl Computer AnalysisBased upon white paper and aerodynamic principlesInput Design ParametersTakeoff distance (e.g.,

Addl Computer AnalysisOutput ValuesTakeoff velocity48 ft/s = 33 mphStall velocity49 ft/s = 34 mphMaximum weight (plane + payload)Next generation of EES developmentCurrently Weight is an inputBenefitsRapid designReduced chance for calculation errorsContinuous refinement - design called for and time permittedReusable in future years

Addl Computer AnalysisMathematical analysis entered into to EES

Addl Computer AnalysisMathematical analysis entered into to EES

Landing GearTricycleConventional Tail DraggerTandem

Landing GearTail draggerOnly uses two forward main wheelsReduces weightReduces dragMay be unstable when aircraft turnsTricycleThree wheel configurationIncreases control on ground if equipped with steerable front wheelTandem usually used on large aircraft

Landing GearLanding gear week point in past designsCAD Model for Conventional Landing Gear Primary AssemblyAluminum supportNylon wheels

Landing GearSimulate impact of a 30lbs plane dropping from a stallApplied 80lbs to the surface simulating attachment to the plane

Other Plane FeaturesBoom length too long can create increased drag and instabilityVertical stabilizer height if too large, the control surface induces a large moment leading to instabilityLed to a crash in 2002

Tail DesignVertical StabilizerSingleDual Configuration

Tail DesignStabilizer/ElevatorFixed Stabilizer PortionMoveable ElevatorRequires complex mechanism to move elevatorIncreases drag if not trimmed for the specific cruising speed of the aircraftStabilatorServes double duty as a stabilizer and elevatorRotates on aerodynamic centerMechanism to rotate stabilator will be less complex than required for stabilizer/elevatorTheoretically reduces dragGenerally used in very fast aircraft

StabilatorStabilizer/Elevator

DemonstrationClick Here!

Stabilator

Stabilizer/Elevator

Prop SelectionPropeller selection depends upon the size of the enginePropeller will be purchased from outside sourcePrecise dimensions difficult to manufacture by handHigher grade materials with higher strength to weight ratio available commercially

Prop SelectionCompetition rules mandate use of a O.S. .61 FX engine0.607 cu in displacementManufacturer recommends the following props:11x8-1012x7-1112.5x6-7

Prop SelectionDynathrust Props (www.dynathrustprops.com) sells injection molded fiberglass and nylon propellersHigher strength to weight ratio than wood propsProp manufacturer reccomends the following props:11x7-812x6A 12x8 prop costs only $3.00Manufacturing labor time cost will also be saved

MaterialsBalsa woodInjection molded fiberglass and nylonLight metal, such as aluminumHeat shrink monocoat for wingRip-stop NylonCarbon fiber tubing

Schedule Update

ConclusionsDigitalized data enables swift calculations in EESDesign team has evaluated past difficultiesWing design is on scheduleSelect final wing profileSelect monoplane or flying wingLanding gear will be selected when plane design is finalizedMonoplane = Conventional Tail DraggerFlying Wing = TricycleTail will consist of a single vertical stabilizer, exact shape to be determined when wing design is completeProp will be outsourced to save time and money

We Welcome Your Questions and FeedbackThank You

Referenceshttp://students.sae.org/competitions/aerodesign/easthttp://adg.stanford.edu/aa241/performance/landing.htmlhttp://adg.stanford.edu/aa241/wingdesign/wingparams.htmlhttp://www.profili2.com/eng/default.htmhttp://www.uoguelph.ca/~antoon/websites/air.htmhttp://www.angelfire.com/ar2/planes2/links.htmlhttp://www.geocities.com/CapeCanaveral/Hall/2716/index.htmlhttp://www.winfoil.com/