AE-705: Introduction to Flight Range and Endurance Subham Panda - - PowerPoint PPT Presentation

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AE-705: Introduction to Flight Range and Endurance Subham Panda - - PowerPoint PPT Presentation

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AE-705: Introduction to Flight Range and Endurance Subham Panda PEC University of Technology Chandigarh AE-705 Introduction to Flight Chapter-09 Lecture No. 17 Range & Endurance RANGE Total distance on a tank of fuel

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

AE-705: Introduction to Flight Range and Endurance

Subham Panda

PEC University of Technology Chandigarh

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

RANGE

Range Total distance on a tank of fuel

http://www.airbus.com/aircraftfamilies/passengeraircraft/a320family/a319neo/ http://www.airbus.com/aircraftfamilies/passengeraircraft/a320family/a319neo/

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

AIRBUS A318

http://www.airbus.com/aircraftfamilies/passengeraircraft/a320family/a318neo/

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

AIRBUS A319

http://www.airbus.com/aircraftfamilies/passengeraircraft/a320family/a319neo/

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

266 Pax– 7500km

AIRBUS A320

http://www.airbus.com/aircraftfamilies/passengeraircraft/a320family/a319neo/

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

AIRBUS A321

http://www.airbus.com/aircraftfamilies/passengeraircraft/a321family/a319neo/

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

A380 RANGE EX MUMBAI

BOM

Range with 555 passengers : up to 8150 nm/ 15100 km

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

BOEING B777 RANGE CAPABILITY FROM SINGAPORE

14700 km 9700 km 11400 km 14320 km 17600 km

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

BOEING V/S AIRBUS

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

 Launched in 2004  > 16,600 km  > 18.5 hours  > 56,000 gallons fuel  Airbus A340-500  Discontinued in 2013  Previous Record

  • SIN-LAX
  • 14,762 km
  • >16 hours

World’s longest nonstop flight

SQ21 SIN-EWR 29/06/04

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

DELHI SAN FRANCISCO FLIGHT

  • Flying Westward

28 kmph headwind Headwind Groundspeed = 776 kmph

  • Flying Eastward

138 kmph Jetstream Tailwind Groundspeed = 936 kmph 2 hours ↓ in Flight Time 13 tons ↓ in Fuel Weight Departure Oct 16 4-00 AM Arrival Oct 16 6-30 AM Time Difference of 12 hours ! THIS RECORD MAY BE BROKEN SOON Singapore Airlines Singapore-New York 16,500 km 19 hours

B 777-200ER

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

RANGE PAYLOAD DIAGRAM

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

B777 PAYLOAD- RANGE CAPABILITY

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

World Records in Aircraft Range

https://en.wikipedia.org/wiki/Flight_distance_record

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

http://www.aviastar.org/pictures/usa/scaled_globalflyer.jpg

GlobalFlyer

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

PAY LOAD VS RANGE FOR ULTRA LONG HAUL AIRCRAFT

https://static.seekingalpha.com/uploads/2014/5/9932311_14013166954015_rId5.png

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

Specific Fuel Consumption

Brake Specific Fuel Consumption Thrust Specific Fuel Consumption comparing the efficiency with a shaft output (Mainly for internal combustion engines) Comparing fuel efficiency with a thrust output (Mainly for air breathing jet engines)

http://static.newworldencyclopedia.org/a/a6/4-Stroke-Engine.gif

https://upload.wikimedia.org/wikipedia/commons/4/4c/Jet_engine.svg

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

V/S

Jet Aircraft Propeller Aircraft SPECIFIC FUEL CONSUMPTION

https://cirrusaircraft.com/wpcontent/themes/cirrus_aircraft_v1.5/images/colorpicker_images/Upgrade/Carb

  • n/2017_Carbon_Mantis_White.png

http://www.floridaairplanehangarforsale.com/wp-content/uploads/2016/04/Airplane_PNG_Clipart-421.png

𝑑 = 𝑋𝑔 𝑄 𝑑𝑢 = 𝑋𝑔 𝑈 SFC TSFC 𝑑𝑢 = cV∞ ηpr

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

RANGE

Distance travelled on a given amount of fuel

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

GENERALIZED RANGE EQUATION

Gross Weight (W) = W1+ Wf change in aircraft weight fuel consumption 𝑑𝑢 = w𝑔 T = − dWf /d𝑢 T 𝑒𝑋 𝑒𝑢 = 𝑒𝑋𝑔 𝑒𝑢 𝑒𝑢 = − 𝑒𝑋𝑔 ctT For steady level flight at stationary atmosphere W1 +

http://www.fuel-togo.com/images/515_IMG_5783.JPG http://www.fuel-togo.com/images/515_IMG_5783.JPG

Wf

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

GENERALIZED RANGE EQUATION

Since 𝑒𝑋𝑔 = 𝑒𝑋 𝑒𝑡 = − 𝑊∞ ctT 𝑒𝑋 = − 𝑊∞ ct 𝑋 T 𝑒𝑋 W

  • In steady straight level flight L = W , T = D

𝑒𝑡 = − 𝑊∞ ct 𝑀 D 𝑒𝑋 W

  • Integrating it from full fuel condition until empty, Range:

𝑆 =

𝑋1 𝑋0 𝑊∞

ct 𝑀 D 𝑒𝑋 W 𝑒𝑡 = 𝑊∞𝑒𝑢 𝑒𝑢 = − 𝑒𝑋𝑔 ctT = − 𝑊∞ ctT 𝑒𝑋𝑔

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

BREGUET RANGE EQUATION

Assume flight at constant 𝑊∞ , ct , and L/D The generalized range equation can be simplified 𝑆 = 𝑊∞ ct 𝑀 D

𝑋1 𝑋0 𝑒𝑋

W 𝑆 =

𝑋1 𝑋0 𝑊∞

ct 𝑀 D 𝑒𝑋 W

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

RANGE FOR PROPELLER-DRIVEN AIRCARFT

  • For propeller SFC
  • To maximize Range:
  • Maximize propeller efficiency (ηpr )
  • Minimize SFC (c)
  • Fly at maximum L/D
  • Maximize fuel capacity (maximize W0/W1)

𝑑𝑢 = 𝑑𝑊∞ ηpr 𝑆 = ηpr 𝑑 L D In W0 W1

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

  • MAX. RANGE : PROPELLER-DRIVEN AIRCRAFT
  • For a given aircraft, 𝑜𝑞𝑠, c, and 𝑋

0/𝑋 1 are fixed

  • Maximum range is achieved by flying at maximum L/D
  • For parabolic drag polar 𝐷𝐸 = 𝐷𝐸0 + 𝐿𝐷𝑀

2, this condition yields :

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

RANGE FOR JET-PROPELLED AIRCRAFT

  • For jet-propelled aircraft in steady straight level flight,

range is not only influenced by L/D, but by 𝑊

∞(L/D):

  • Substitute this into the generalized range equation:
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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

ENDURANCE

Time in air on a given amount of fuel

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

ENDURANCE

Total Time taken for a Cruise Flight

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

First aircraft to fly around the world nonstop without refuelling

Rutan Model 76 Voyager

Voyager Takeoff

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

ENDURANCE RECORD

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

Endurance Record for an autonomous aircraft < 50 kg (81 hours)

Atlantik Solar Research UAV ETH Zurich

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

GENERALIZED ENDURANCE EQUATION

Definition of TSFC : In steady straight level flight: L = W, T = D Integrating from Full Fuel to Empty,

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

ENDURANCE FOR PROPELLER-DRIVEN AIRCRAFT

Using SFC and steady straight level flight condition:

If 𝑜𝑞𝑠 , c ,𝜍∞, and 𝐷𝑀

3/2/𝐷𝐸are constant:

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

ENDURANCE FOR PROPELLER-DRIVEN AIRCRAFT

To maximize endurance:

  • Fly at maximum 𝐷𝑀

3/2/𝐷𝐸

  • Fly at sea level (maximum 𝜍∞)
  • Maximize propeller efficiency (η𝑞𝑠)
  • Minimize SFC (c)
  • Maximize fuel capacity (maximize (𝑋

1 −1/2 − 𝑋 −1/2

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

  • MAX. ENDURANCE:PROPELLER-DRIVEN AIRCRAFT

For a specific aircraft, η𝑞𝑠, c , and (𝑋

1 −1/2 − 𝑋 −1/2) are fixed

At a given altitude (𝜍∞ is constant), Endurance is maximized by Flying at maximum 𝐷𝑀

3/2/𝐷𝐸 —> 3𝐷𝐸0 = 𝐿CL

2

For parabolic drag polar, this condition yields: 3CD0 = KCL

2

CL= √{3CD0 /K} CD = CD0+ KCL

2 =4CD0

CL

3/2/CD = {3CD0/K}3/4/{(4CD0}

3CD0 = KCL

2

→

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

ENDURANCE FOR JET-PROPELLED AIRCRAFT

  • lf 𝑑𝑢 and 𝑀/𝐸 are constant:

To maximize Endurance:

  • Fly at maximum L/D
  • Minimize TSFC(𝑑𝑢)
  • Maximize fuel capacity, Reduce W0 (maximize 𝑋

0/𝑋 1)

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

  • MAX. ENDURANCE: JET-PROPELLED AIRCRAFT
  • For a specific aircraft, 𝑑𝑢 and 𝑋

0/𝑋 1 are fixed

  • Maximum endurance is achieved by flying at maximum 𝑀/𝐸
  • For parabolic drag polar, this condition yields:
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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

  • 1. Pmin : (CL

3/2/CD)max

: 3CD0=KCL

2

Endurance Max Prop

  • 2. Dmin = (P/V) min : (CL/CD)max

: CD0=KCL

2

Range Max Prop & Endurance Max Jet

  • 3. (P/V) min : (CL/CD)max

: CD0=KCL

2

Same as 2 above

  • 4. (D/V) min : (CL

1/2/CD)max

: CD0 =3KCL

2

Range Max Jet

POWER REQUIRED AND THRUST REQUIRED (DRAG) CURVES

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

EFFECT OF WIND

Headwind & Tailwind

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

EFFECT OF WIND

Headwind Tailwind

Range is dependent on speed w.r.t. the ground (ground speed) For jet aircraft: For propeller-driven aircraft: Because ground speed is affected by wind, so the range is

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

Ground Speed (VG) = True Air Speed (V) + Tail Wind (VT)

EFFECT OF TAIL WIND & HEAD WIND ON GROUND SPEED

Ground speed (VG ) = True Air Speed (V) – Head Wind (VH)

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

(Increase in Range in Tail Wind)

(Decrease in Range in Head Wind)

Note: (L/D) value as applicable for constant altitude cruise or constant speed cruise

EFFECT OF TAIL & HEAD WIND ON RANGE JET AIRCRAFT

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

(increase in Range in Tail Wind) (decrease in Range in Head Wind)

Note: (L/D) value as applicable for constant altitude cruise or constant speed cruise

EFFECT OF TAIL & HEAD WIND ON RANGE PROPELLER A/C

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

RANGE AND ENDURANCE – SUMMARY

* * * ** #

Range for Jet Aircraft Constant speed (h increases- Cruise climb) * CD0 = KCL

2

Constant h (V decreases) ** CD0 = 3KCL

2

Endurance for Jet Aircraft * CD0 = KCL

2

Range for Propeller Aircraft * CD0 = KCL

2

Endurance for Propeller Aircraft # 3CD0 = KCL

2

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AE-705 Introduction to Flight Lecture No. 17 Range & Endurance Chapter-09

1. Pmin : (CL

3/2/CD)max

: 3CD0=KCL

2

Endurance Max Prop

  • 2. Dmin = (P/V) min : (CL/CD)max

: CD0=KCL

2

Range Max Prop & Endurance Max Jet

  • 3. (P/V) min : (CL/CD)max

: CD0=KCL

2

Same as 2 above

  • 4. (D/V) min : (CL

1/2/CD)max

: CD0 =3KCL

2

Range Max Jet

RANGE AND ENDURANCE – SUMMARY