18-1 Sarah pageEdwin Kumar peter Schneiderrick prasad - PowerPoint PPT Presentation

Title: 18-1 Sarah pageEdwin Kumar peter Schneiderrick prasad


1
18-1Sarah page Edwin Kumarpeter
Schneider rick prasad

• 154A Aircraft Design

2
Changing the Specs
Specification Given in Design Project Final Specification
Payload (lbs) 100 100
Passengers 4 2
Range (mi) 1200 1000
Top Speed (mph) 180 180
Cruising Speed (mph) 160 160
Stall Speed (mph) 65 50
Ceiling (ft) 17,000 17,000
Rate of Climb (fpm) 1000 1000
Takeoff Distance (ft) 1500 lt 1000
3
Other STOL Planes
Picture of Mountain Goat STOL
Mountain Goal STOL
Max Gross Weight 2500 lbs Wing Span 35.5
ft Wing Area 188 sq ft
Katmai STOL Plane with Canard
Max Gross Weight 2950 lbs Stall Speed 40
mph Takeoff Distance 383 ft R/C 1380 rpm

• http//www.katmai-260se.com/

4
Wings
Wing Canard
Clmax 2.5 3
Aspect Ratio 7 10
f 0.9 0.1
Area (ft2) Span (ft) Width (ft)
Wing 190.82 36.56 5.22
Canard 17.67 13.29 1.33
5
Airfoil Selection
WING
NACA 1412 Airfoil at 5 angle of attack
Lift Curve Slope
Drag Polar
6
Airfoil Selection
CANARD NACA 23018
Lift Curve Slope
Drag Polar
7
Airfoil Selection
TAIL NACA 0009
Lift Curve Slope
Drag Polar
8
Drag Calculations
Induced Drag
Parasite Drag
Equivalent Skin Friction Method Component Buildup Method
0.0246 0.02887
9
Thrust Required / Available
147 fps
10
Drag Polar
11
Lift to Drag Ratios
104 fps
142 fps
182 fps
12
Designing a Propeller
250HP _at_ 2600 RPM
285HP _at_ 2700 RPM
210HP _at_ 2700 RPM
65 IO-470-C 65 IO-520-A J 65 IO-520-A J 65 IO-520-A J 75 IO-520-A J 75 IO-520-A J 75 IO-520-A J 65 TSIO-360-LB 65 TSIO-360-LB 75 TSIO-360-LB 75 TSIO-360-LB 75 TSIO-360-LB
Cs 1.62 1.552 1.552 1.552 1.479 1.479 1.479 1.65 1.65 1.60 1.60 1.60
Power (ft-lb/sec) 89375 101887.5 101887.5 101887.5 117562.5 117562.5 117562.5 75075 75075 86625 86625 86625
? (degrees) 20 20 25 25 20 25 25 20 25 20 25 25
? (at cruise) 0.85 0.85 0.82 0.82 0.87 0.84 0.84 0.85 0.85 0.85 0.85 0.85
J 0.88 0.8 0.8 0.9 0.77 0.77 0.89 0.84 0.94 0.86 0.86 0.92
D (ft) 7.10 7.53 7.53 6.69 7.45 7.45 6.45 7.17 6.40 7.00 7.00 6.54
Vtip (fps) 837.76 921.5 921.5 819.14 957.44 957.44 828.35 877.65 784.28 857.24 857.24 801.33
T1 (lbs) 323.74 369.05 369.05 356.02 435.85 435.85 420.82 271.93 271.93 313.77 313.77 313.77
CT 0.37 0.038 0.038 0.06 0.044 0.044 0.06 0.03 0.052 0.029 0.029 0.058
T2 (lbs) 260.26 362.9 362.9 357.71 445.06 445.06 340.03 235.70 260.53 207.38 207.38 316.69
13
Propeller Design for Takeoff
Variable Pitch Propeller Required
Thrust versus Velocity for a 285 HP engine with a
15 degree blade angle
14
Final Results
Specification Given to Design Project Final Specification
Payload (lbs) 100 100
Passengers 2 2
Range (mi) 1200 1037
Top Speed (mph) 180 180
Cruising Speed (mph) 160 160
Stall Speed (mph) 50 50
Ceiling (ft) 17,000 21300
Rate of Climb (fpm) 1000 1144
Takeoff Distance (ft) lt 1000 718.837
15
Range

• Bruguet Range Equation
• Our L/D ratio is less than comparable aircrafts
• This is due to trade-offs between STOL and other
  performance aspects
• Cruise Range
• 1037 statute miles _at_ 160 mph

16
Range

• Maximizing Range
• This happens at the maximum L/D ratio possible
• L/D)max occurs at the minimum thrust setting
• Historical trends show that our L/D)max should
  occur at around 12.
• This is a good check for our calculations
• L/D)max turns out to be 12.7
• Maximum Range
• 1581 statute miles _at_ 101 mph

17
Endurance

• Found using a different form of Berguet Range
  equation
• Density is a factor in this equation
• The aircraft we based ours upon, the Peterson
  Katmai has an endurance of 13.6 hour _at_ 69 mph

18
Performance
Setting Velocity (mph) Range (mi) Endurance (hr)
Cruise 160 1037 6.5
Minimum Thrust L/D)max 101 1581 15.7
Minimum Power L3/2/D)max 77 1283 16.7
19
Weight Calculations

• Initial estimates done with mission segment
  method
• Our mission profile is that of a contraband
  runner
• No significant loiter time
• Estimates done using Berquet range equation
• Concerns arose about our fuel fraction
• Topped out at 17 early in design process
• Estimating using this method depends on expected
  range
• We failed to account for reduced range

20
Weight Calculations

• Due to the similarities between our aircraft and
  Cessna 172, we used the Cessna weight estimations
• The engine, wing, and fuel/fuel system accounted
  for most of the planes weight

Component Weight (lbs) Weight ()
Wing 583.97 22.12
Engine 450.00 17.10
Fuel/Fuel System 421.74 16.02
21
Final Weigh Estimates
Component Weight (lbs)
Wing 584.97
Tail 47.07
Canard 34.53
Fuselage 289.50
Engine 450
Fuel/System 421.74
Landing gear 175.00
Component Weight (lbs)
Avionics 105.00
Firewall 5.00
Furnishing 20.00
Pilot 200.00
Passenger 200.00
Payload 100.00
Total 2631.81

• Gross Takeoff Weight 2631.81 lbs