1 critical design review ashley brawner neelam datta xing huang jesse jones team 2: balsa to the...
Post on 15-Jan-2016
259 views
TRANSCRIPT
![Page 1: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/1.jpg)
1
Critical Design ReviewCritical Design Review
Ashley Brawner
Neelam Datta
Xing Huang
Jesse Jones
Team 2: Balsa to the Wall
and the TFM-2
Matt Negilski
Mike Palumbo
Chris Selby
Tara Trafton
![Page 2: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/2.jpg)
2 of 48
Presentation OverviewPresentation Overview
Aerodynamics Propulsion Structures D&C Specifications
Summary
![Page 3: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/3.jpg)
3 of 48
Aerodynamics OverviewAerodynamics Overview
Airfoil Selection Taper Ratio Aspect Ratio Drag Model
Parasite, Induced, Viscous Max CL & Flaps Aero Design Summary
![Page 4: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/4.jpg)
4 of 48
Airfoil Selection: Airfoil Selection: Main WingMain Wing
Wing Section Design Requirements
Gives approximate 2D Cl needed for dash Relatively thin for minimizing drag Thick enough for structural considerations
Other Considerations Availability of empirical data
Conclusion: NACA 1408
![Page 5: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/5.jpg)
5 of 48
Airfoil Selection: Airfoil Selection: TailTail
Tail Sections Horizontal Stabilizer
Symmetric with low Cd over a wider range of α (0 - 5 degrees)
Conclusion : Jones airfoil (8% t/c)
Vertical Stabilizer Symmetric with low Cd at low α (0 degrees)
Conclusion : NACA 0006
![Page 6: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/6.jpg)
6 of 48
Taper RatioTaper Ratio Ideal lift distribution is
elliptical (minimizes induced drag)
λ=0.45 gives closest elliptical lift distribution
Less than 1% higher induced drag than ideal (Raymer)
Figure from Raymer textbook
![Page 7: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/7.jpg)
7 of 48
AR Trade StudyAR Trade StudyLines of constant C
D (An AR trade study)
AR
CL
0.02550.026 0.0265
0.027 0.0275 0.0280.029
0.03
0.035
0.04
0.05
0.06
0.08
0.10.12
3 4 5 6 7 8 9 10 11 120
0.2
0.4
0.6
0.8
1
1.2
High CL
Drag-due-to-lift dominates High AR
Low CL
Parasite drag dominates Low AR
CL design ≈ 0.083 AR needs to be
small
![Page 8: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/8.jpg)
8 of 48
Drag Build-up MethodDrag Build-up Method Cfc = Component skin
friction coefficient FFc = Component form
factor Qc = Component
interference effects Swet,c = Component
wetted area Sref = Wing planform
ref
c cwetccfD S
SQFFCC c ,
0
Method from Raymer textbook
![Page 9: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/9.jpg)
9 of 48
Component Friction CoefficientComponent Friction Coefficient
Figure from Nicolai paper
![Page 10: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/10.jpg)
10 of 48
Aircraft Drag PolarAircraft Drag Polar
2
min0 LLDD CCKKCC
Takes into account having a cambered wing. Minimum drag occurs at some non-zero CL
Models inviscid and viscous drag-due-to-lift. K′ is the inviscid drag-due-to-lift factor
Due to trailing edge vortices (induced drag) K′′ is the viscous drag-due-to-lift factor
Due to transition and increased skin friction
Method from Nicolai paper
![Page 11: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/11.jpg)
11 of 48
Aircraft Drag Polar (cont.)Aircraft Drag Polar (cont.)
2
min0 LLDD CCKKCC
eARK
1
minmin lL CC More involved
(next slide)
Method from Nicolai paper
Assumes that the zero lift angle of attack is the same for 2D and 3D
![Page 12: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/12.jpg)
12 of 48
Aircraft Drag Polar (cont.)Aircraft Drag Polar (cont.)
2
min0 LLDD CCKKCC
Method from Nicolai paper
Viscous Drag Coefficient K′′ for NACA 1408
Overall:y = 0.0243x + 0.0045
High Speed Region:y = 0.0167x + 0.0051
0
0.005
0.01
0.015
0.02
0.025
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7
(Cl-Clmin)2
Cd Overall
High Speed
K′′ = 0.0167
![Page 13: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/13.jpg)
13 of 48
Effect of Flaps Effect of Flaps
maxmaxmax LLL CCCclean
KS
SCC
W
WFlL maxmax
92.0coscos08.01 4/4/3
4/2 ccK
cleanclean lL CCmaxmax
9.0
S
SCCC WFllL
clean maxmaxmax92.09.0
Figure from Nicolai textbook
![Page 14: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/14.jpg)
14 of 48
Aerodynamics SummaryAerodynamics Summary
Main Airfoil NACA 1408 CL,o 0.152
Horz. Tail Jones (8%) CL,α (1/rad) 4.3719
Vert. Tail NACA 0006 CL,max (clean) 0.85
S (ft2) 4.95 CL,max (flapped) 1.06
AR 5 CD,min 0.018
Taper 0.45 Cf ,e 0.00587
MGC (ft) 1
% Chord 20Max δf (deg) 35
∆CL 0.21
SWF (ft2) 1.75
Flaps Design
Wing Design Aircraft
![Page 15: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/15.jpg)
15 of 48
Propulsion OverviewPropulsion Overview
Ducted Fan Basics Propulsion System Thrust Model Duct Design
![Page 16: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/16.jpg)
16 of 48
Ducted Fan ApplicationsDucted Fan Applications
Wind Tunnels
Hovercraft
Tail Rotor
Similar to:High Bypass Turbofan
![Page 17: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/17.jpg)
17 of 48
Ducted Fan BasicsDucted Fan Basics
Pros No Propeller Tip Downwash Direct Drive High Static Thrust No Landing Gear
Hand Launch / Belly Landing
No Landing Gear Drag
Cons Duct Profile Drag High RPM Duct Weight High Amperage Dangerous Belly Landing
System Propeller Ducted Fan
Method Retractable Landing Gear Hand Launch
Weight 0.91 lbf 0.65 lbf
Cost $70.00 $60.00
Weight & Cost Comparison
![Page 18: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/18.jpg)
18 of 48
Propulsion SystemPropulsion System
WeMoTec Midi Fan Fan Dia: 3.5 in Max RPM: 35,000 Weight: 0.25 lbf
![Page 19: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/19.jpg)
19 of 48
Propulsion System Cont’dPropulsion System Cont’d Electrifly Ammo 36-50-2300
Kv: 2300 RPM/Volt Max Cont. Current: 60 Amps Max Surge* Current: 100 Amps Max Cont. Power: 1.5 hp
A123 Systems M1 Li-Ion Cells 5 cells in Series Capacity: 2300 mAh Voltage: 18 Volts Max Cont. Current: 70 Amps Max Surge* Current: 120 Amps
* - Surge is 10 sec
![Page 20: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/20.jpg)
20 of 48
Thrust Model Cont’dThrust Model Cont’d
Thrust atMax RPM(35,000 RPM)
Thrust atOperating RPM(30,000 RPM)
Stall Speed = 30 ft/sThrust Required Max Speed
107 ft/s( 72 mph )
![Page 21: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/21.jpg)
21 of 48
Duct DesignDuct Design
44
22HubFan DD
FSA
FSA highlighted in blueDFan = Diameter of FanDHub = Diameter of Hub
Duct Inlet 129 % of Fan Swept Area (FSA)
Converging Nozzle Ensure Sufficient Mass Flow Ingest Boundary Layer
Duct Exit 85 % of FSA
Converging Nozzle Raise Exhaust Velocity Optimized for High Speed
![Page 22: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/22.jpg)
22 of 48
Duct Design Cont’dDuct Design Cont’d Duct Intake Area
9.81 in2
Duct Intake Diameter 3.53 in
Duct Intake Length 3.57 in
Duct Exit Area 6.85 in2
Duct Exit Diameter 2.95 in
Duct Exit Length 3 in
![Page 23: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/23.jpg)
23 of 48
Duct IntegrationDuct Integration
![Page 24: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/24.jpg)
24 of 48
Propulsion SummaryPropulsion Summary
High Speed Max Endurance
RPM 30,000 RPM 15,000 RPMVoltage 16.1 Volts 7.4 VoltsAmps 73.7 Amps 19.9 VoltsPower 1.59 hp 0.21 hp
107 ft/ s 47 ft/ s( 65 mph ) ( 32 mph )
Speed
Propulsion Performance
Unit Manufacturer Model CostDucted Fan Wemotec Midi Fan $56.50
Motor Great Planes Ammo 36-50-2300 $79.99Batteries A123 5 X HS-DK-4 $55.00
Total $191.49
Propulsion Costs & Weights
![Page 25: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/25.jpg)
25 of 48
Structures OverviewStructures Overview
V-n Diagram Analysis of Wing Loads Wing/Boom Structure Fuselage and Tail CATIA Model
![Page 26: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/26.jpg)
26 of 48
Preliminary Weight EstimatePreliminary Weight Estimate
![Page 27: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/27.jpg)
27 of 48
V-n DiagramV-n Diagram
2
2V
W
SCn L
dashdive VV 25.1
2
2V
W
SCn L
Maximum Design Load Factor = 7.5
![Page 28: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/28.jpg)
28 of 48
Structural Properties of WingStructural Properties of Wing
Discretized wing into ten sections Initially, elliptic airfoil approximation Bending and polar moments of inertia
found at each station using XFOIL Foam core, fiberglass skin construction Foam neglected in analysis
![Page 29: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/29.jpg)
29 of 48
Bending AnalysisBending Analysis
0 0.5 1 1.5 2 2.50
5
10
15
20
25Bending Moment vs. Span
Distance from Root [ft]
Ben
ding
Mom
ent
[ft-
lb]
tIyM
bending
M = bending moment
y = vertical distance from neutral axis
I(t) = moment of inertia, a function of skin thickness, t
![Page 30: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/30.jpg)
30 of 48
Twisting AnalysisTwisting Analysis
cSCVT m2
2
1 GJ
TL
T = Torque
Cm = Moment coefficient
c = Chord length
phi = Twist angle/unit length0 0.5 1 1.5 2 2.5
-6
-5
-4
-3
-2
-1
0Torque vs. Distance from Root
Distance from Root [ft]
Tor
que
[ft-
lbf]
![Page 31: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/31.jpg)
31 of 48
Wing StructureWing Structure
[0/90] Woven Cloth
E_1 [Msi] 3.5
E_2 [Msi] 3.5
G_12 [Msi] 0.68
2 Ply Laminate [0/45]
E_x [Msi] 2.87
E_y [Msi] 2.87
G_xy [Msi] 1.13
Skin: 2 oz E-glass ClothEZ-Lam Epoxy
Core: Expanded Polystyrene Foam
3 Ply Laminate [-45/0/45]
E_x [Msi] 2.62
E_y [Msi] 2.62
G_xy [Msi] 1.28
![Page 32: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/32.jpg)
32 of 48
Wing StructureWing Structure
Shaped balsa blocks integrated into wing foam at boom, fuselage, and motor/duct mount interfaces
Carbon fiber composite arrow shafts for booms
Fiberglass over wing/boom structure
![Page 33: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/33.jpg)
33 of 48
Fuselage and TailFuselage and Tail
Fuselage Foam core on CNC due to advanced
geometry 3 oz satin weave fiberglass and epoxy
Horizontal and vertical tails Hot wire cut foam cores 2 oz plain weave fiberglass and epoxy
![Page 34: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/34.jpg)
34 of 48
Component IntegrationComponent Integration
![Page 35: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/35.jpg)
35 of 48
CATIA Model ContributionCATIA Model Contribution
Visualization of design Wetted areas Aircraft weight Accurate CG calculation/placement Moments and products of inertia Manufacturing necessity
![Page 36: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/36.jpg)
36 of 48
Structures SummaryStructures Summary
Dual boom design contributes significantly to structural design of wing
Twist is dominant constraint Foam core/fiberglass skin construction Value of CATIA model
![Page 37: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/37.jpg)
37 of 48
D&C OverviewD&C Overview
Tail Sizing Control surface sizing Trim diagram Yaw rate feedback control system
![Page 38: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/38.jpg)
38 of 48
Horizontal TailHorizontal Tail
Longitudinal X-plot Tail area = 90 in2
Chord = 5 in Span = 18 in AR = 3.6
Static margin 18 %
![Page 39: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/39.jpg)
39 of 48
Vertical Tail – Twin Tail Config.Vertical Tail – Twin Tail Config.
Directional X-plot Tail area = 30 in2
Chord = 5 in Span = 6 in AR = 1.2
Weathercock stability = 0.102 rad-1
Total vertical tail area 60 in2
![Page 40: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/40.jpg)
40 of 48
Control Surface SizingControl Surface Sizing
Elevator 25% of chord = 1.25 inches Elevator effectiveness (Cmδe) = -1.28 rad-1
Rudder – Only one rudder on twin-tail 50% of chord = 2 inches Rudder effectiveness (Cnδr) = -0.031 rad-1
![Page 41: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/41.jpg)
41 of 48
Trim DiagramTrim Diagram
Limitations Tail Stall at
α = 7.2º
CL,max = 1.06 Trim Velocity
92 ft/sec From Trim
Diagram δe range -1º-8º
-0.4-0.3-0.2-0.100.10.20.3-0.2
0
0.2
0.4
0.6
0.8
1
1.2
CLmax
CL
Cm0.25c
α = 3o
α = 7o
α = -1o
Cm = 0
Xcg forward
Cm = 0
Xcg nominal
Cm = 0
Xcg aft
![Page 42: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/42.jpg)
42 of 48
Feedback Control SystemFeedback Control System
Dutch roll mode damping ratio required to be at least 0.8
Without feedback control system damping ratio is 0.212
Integration of feedback controller with control law gain of -0.45 increases dutch roll mode damping ratio to 0.81
![Page 43: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/43.jpg)
43 of 48
Feedback Control SystemFeedback Control System
+
-
-0.45 1
95040
9502 ss
Futaba Servo
Control Law and Rate Gyro Gains
)587.8244.1)(2114.0)(461.5(
)4492.0)(7033.0)(821.5(7924.92
ssss
sssr
Yaw Rate Aircraft Transfer Function
δr [rad]Yaw rate
[r/s]
![Page 44: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/44.jpg)
44 of 48
D&C SummaryD&C Summary
Horizontal tail area 90 in2 for static margin of 18%
Vertical tail area 60 in2 for weathercock stability
Feedback control system with control law gain of -0.45 needed to meet dutch roll mode damping of 0.8
![Page 45: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/45.jpg)
45 of 48
CATIA Model 3-ViewCATIA Model 3-View
![Page 46: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/46.jpg)
46 of 48
SummarySummary
Total length (in) 53.24Wing span (ft) 60Wing root chord (in) 16.47Wing tip chord (in) 7.42Tail span (in) 18Tail height (in) 6Weight (lbf) 5.5Stall speed (ft/sec) 30Top speed (ft/sec) 107
Design Specifications
![Page 47: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/47.jpg)
47 of 48
Questions?Questions?
![Page 48: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/48.jpg)
48 of 48
Appendix
![Page 49: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/49.jpg)
49 of 48
Aerodynamics Appendix
![Page 50: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/50.jpg)
50 of 48
Airfoil Selection: Airfoil Selection: Main Wing (cont.)Main Wing (cont.)
XFOIL: Drag Polar
0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1
1.1
1.2
0 0.005 0.01 0.015 0.02 0.025 0.03
Cd
Cl Jones Airfoil
NACA 1408MH 30
MH 64
Design Cl = 0.15
![Page 51: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/51.jpg)
51 of 48
Airfoil Selection: Airfoil Selection: Tail (cont.)Tail (cont.)Various Airfoil Cd-α curves
0.004
0.005
0.006
0.007
0.008
0.009
0.01
0.011
0.012
0.013
0 0.5 1 1.5 2 2.5 3 3.5 4 4.5 5
α [deg]
Cd
NACA 0006
NACA 0007
NACA 0008
Jones (6.8% t/c)
Jones (7.2% t/c)
Jones (8% t/c)
![Page 52: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/52.jpg)
52 of 48
XFOIL XFOIL ααstall stall vs. actual vs. actual ααstall stall NACA 1408 Cl-α curve
Re = 3,000,000
-1
-0.5
0
0.5
1
1.5
2
-10 -8 -6 -4 -2 0 2 4 6 8 10 12 14 16 18 20
α [deg]
Cl
Experimental
Numerical
XFOILClCl maxmax 8.0
![Page 53: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/53.jpg)
53 of 48
XFOIL XFOIL ααstall stall vs. actual vs. actual ααstall stall (cont.)(cont.) NACA 1408 Cl-α curve
Re = 6,000,000
-1
-0.5
0
0.5
1
1.5
2
-10 -5 0 5 10 15 20 25
α [deg]
Cl
Experimental
Numerical
XFOILClCl maxmax 8.0
![Page 54: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/54.jpg)
54 of 48
XFOIL XFOIL ααstall stall vs. actual vs. actual ααstall stall (cont.)(cont.)NACA 1408 Cl-α curve
Re = 9,000,000
-1
-0.5
0
0.5
1
1.5
2
-10 -5 0 5 10 15 20 25
α [deg]
Cl
Experimental
Numerical
XFOILClCl maxmax 8.0
![Page 55: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/55.jpg)
55 of 48
maxlCFinding Finding
NACA 1408 section with flaps (XFOIL @ Re=5.0e5)
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
-4 -2 0 2 4 6 8 10
α (deg)
Cl
Clean NACA 1408
Flap: x/c=0.8, 30 degrees
maxlC
![Page 56: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/56.jpg)
56 of 48
Propulsion Appendix
![Page 57: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/57.jpg)
57 of 48
Thrust CalculationsThrust Calculations
VVmVmT eA D2SCV
2
1 RT
DragofCoeffC
AreaWingS
AreaSweptFanA
DensityStreamFree
VelocityStreamFreeV
FanofVelocityExitV
FlowMassAVm
AvailableThrustT
D
e
e
A
.
![Page 58: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/58.jpg)
58 of 48
Structures Appendix
![Page 59: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/59.jpg)
59 of 48
Wing Skin MaterialWing Skin Material
With 4 oz E-glass/EpoxyWing Area [in^2] 1465.078
Wing Area [yd^2] 1.130
Fiberglass Weight [lbf] 0.283
Epoxy Weight [lbf] 0.283
Wing Volume [in^3] 478.516
Wing Volume [ft^3] 0.277
Foam Weight [lbf] 0.485
Wing Weight [lbf] 1.050
Φ = - 0.82 deg
Deflection = 2e-6 in
![Page 60: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/60.jpg)
60 of 48
Wing Skin MaterialWing Skin Material
http://www.airfieldmodels.com/information_source/how_to_articles_for_model_
builders/finishing_techniques/apply_fiberglass_finish/index.htm
![Page 61: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/61.jpg)
61 of 48
Material PropertiesMaterial Properties
Material Properties Table
E-Glass
FiberS-Glass
FiberE-glass (Fabric)
Balsa Wood
Carbon Fiber
Polyurethane Foam
Density (lbs/in^3) 0.071 0.072 0.068 0.054 0.065 0.0046
Tensile Strength (ksi) 165 250 62.8 0.16 325 0.16
Shear Strength (ksi) 12.9 10 12.2 0.54 10.6 0.2
Longitudinal Young's Modulus (10^6 psi) 6 6.5 3.55 0.0094 21.3 0.0051
Transverse Young's Modulus (10^6 psi) 1.5 1.6 3.45 0.0094 1.5 0.0051
Shear Modulus (10^6 psi) 0.62 0.66 0.68 0.0085 1 0.00145
Poisson's Ratio 0.28 0.29 0.11 0.4 0.27 0.25
![Page 62: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/62.jpg)
62 of 48
V-n DiagramV-n Diagram
Load Factor vs. Turn Radius for Different Velocities
0
5
10
15
20
25
30
35
0 10 20 30 40 50 60
Vertical Turn Radius [ft]
Lo
ad F
acto
r (n
)
30 [ft/s]
35 [ft/s]
40 [ft/s]
45 [ft/s]
50 [ft/s]
55 [ft/s]
60 [ft/s]
65 [ft/s]
70 [ft/s]
75 [ft/s]
80 [ft/s]
85 [ft/s]
90 [ft/s]
95 [ft/s]
100 [ft/s]
Design Point:
Vertical turn radius = 28 ft
Velocity = 60 ft/s
Load factor = 5
12
gr
Vn
![Page 63: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/63.jpg)
63 of 48
Load Factor – Max LiftLoad Factor – Max Lift
2
2V
W
SCn L
10 20 30 40 50 60 70 80 90 1000
2
4
6
8
10
12
14Load Factor vs. Velocity
Velocity [ft/sec]
n max
![Page 64: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/64.jpg)
64 of 48
Load Factor – Level TurnLoad Factor – Level Turn
0 10 20 30 40 50 60 70 80 900
2
4
6
8
10
12Load Factor vs. Bank Angle
Bank Angle [deg]
n turncos1n
![Page 65: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/65.jpg)
65 of 48
Load Factor – Vertical TurnLoad Factor – Vertical Turn
0
50
100
150
0
50
100
1500
2
4
6
8
10n pu
ll up
Load Factor vs. Velocity and Vertical Turn Radius
Velocity [ft/sec]Vertical Turn Radius [ft]
12
gr
Vn
![Page 66: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/66.jpg)
66 of 48
Wing CentroidWing Centroid
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
0.4NACA 1408 Normalized Airfoil and Centroid Location
x/c
y/c
![Page 67: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/67.jpg)
67 of 48
ComparisonComparison
I_xx_area_avg_error 22.70%
I_xx_skin_avg_error 6.79%
J_area_avg_error 23.81%
J_skin_avg_error 27.30%
Airfoil Tip Deflection
[ft] 1.386E-04
Ellipse Tip Deflection
[ft] 1.298E-04
Airfoil Tip Twist [deg] -1.045
Ellipse Tip Twist [deg] -0.820
![Page 68: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/68.jpg)
68 of 48
D&C Appendix
![Page 69: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/69.jpg)
69 of 48
D&C AppendixD&C Appendix Horizontal tail sizing method LongitudinalX-plot Set center of gravity location at the quarter-chord Plot aerodynamic center of aircraft as a function of
the horizontal tail area
wfh
wfhhwfA
Lhh
L
Lachh
Lacac
CSS
ddCF
FCXSS
ddCXX
11
1
![Page 70: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/70.jpg)
70 of 48
D&C AppendixD&C Appendix
Vertical tail sizing method directional X-plot Use of twin-tail configuration to determine
weathercock stability as a function of vertical tail area
S
SC
C
CC
b
zlCC
b
l
S
SKKC
C
CCCC
VVeffy
Veffy
WBFVyVy
VVVyVn
BBsRlNBn
wn
nnnnVBw
)(2
sincos
3.57
0All equations result in rad-1
![Page 71: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/71.jpg)
71 of 48
D&C AppendixD&C Appendix
Open loop poles of aircraft yaw rate transfer function
Eigenvalue Damping Freq. (rad/s)
0.00e+000 -1.00e+000 0.00e+000
2.11e-001 -1.00e+000 2.11e-001
-6.22e-001 + 2.86e+000i 2.12e-001 2.93e+000
-6.22e-001 - 2.86e+000i 2.12e-001 2.93e+000
-5.46e+000 1.00e+000 5.46e+000
![Page 72: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/72.jpg)
72 of 48
Appendix:Appendix:Control System Root LocusControl System Root Locus
Use of SISOTool to help determine the correct gain to use
![Page 73: 1 Critical Design Review Ashley Brawner Neelam Datta Xing Huang Jesse Jones Team 2: Balsa to the Wall and the TFM-2 Matt Negilski Mike Palumbo Chris Selby](https://reader033.vdocuments.us/reader033/viewer/2022061501/56649d595503460f94a38a5e/html5/thumbnails/73.jpg)
73 of 48
AppendixAppendix
Control system closed loop poles: Eigenvalue Damping Freq. (rad/s)
0.00e+000 -1.00e+000 0.00e+000
2.81e-001 -1.00e+000 2.81e-001
-3.36e+000 + 2.16e+000i 8.40e-001 3.99e+000
-3.36e+000 - 2.16e+000i 8.40e-001 3.99e+000
-4.41e+000 1.00e+000 4.41e+000
-1.78e+001 + 2.18e+001i 6.32e-001 2.82e+001
-1.78e+001 - 2.18e+001i 6.32e-001 2.82e+001