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18-1 Sarah page Edwin Kumar peter Schneider rick prasad. 154A Aircraft Design. Changing the Specs. 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.

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18 1 sarah page edwin kumar peter schneider rick prasad

18-1Sarah page Edwin Kumarpeter Schneider rick prasad

154A Aircraft Design



Other stol planes
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/



Airfoil selection
Airfoil Selection

WING

NACA 1412 Airfoil at 5° angle of attack

Lift Curve Slope

Drag Polar


Airfoil selection1
Airfoil Selection

CANARD

NACA 23018

Lift Curve Slope

Drag Polar


Airfoil selection2
Airfoil Selection

TAIL

NACA 0009

Lift Curve Slope

Drag Polar


Drag calculations
Drag Calculations

Induced Drag

Parasite Drag




Lift to drag ratios
Lift to Drag Ratios

104 fps

142 fps

182 fps


Designing a propeller
Designing a Propeller

250HP @ 2600 RPM

285HP @ 2700 RPM

210HP @ 2700 RPM


Propeller design for takeoff
Propeller Design for Takeoff

Variable Pitch Propeller Required

Thrust versus Velocity for a 285 HP engine with a 15 degree blade angle



Range
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 @ 160 mph


Range1
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 @ 101 mph


Endurance
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 @ 69 mph



Weight calculations
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


Weight calculations1
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 plane’s weight


Final weigh estimates
Final Weigh Estimates

Gross Takeoff Weight: 2631.81 lbs


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