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									MAE 3241: AERODYNAMICS AND
    FLIGHT MECHANICS
          Thrust and Power Requirements



                  April 28, 2010

  Mechanical and Aerospace Engineering Department
          Florida Institute of Technology

                    D. R. Kirk
             EXAMPLE: BEECHCRAFT QUEEN AIR
•   The results we have developed so far for lift and drag for a finite wing may also be applied to a
    complete airplane. In such relations:
     – CD is drag coefficient for complete airplane
     – CD,0 is parasitic drag coefficient, which contains not only profile drag of wing (c d) but also
        friction and pressure drag of tail surfaces, fuselage, engine nacelles, landing gear and any
        other components of airplane exposed to air flow
     – CL is total lift coefficient, including small contributions from horizontal tail and fuselage
     – Span efficiency for finite wing replaced with Oswald efficiency factor for entire airplane
•   Example: To see how this works, assume the aerodynamicists have provided all the information
    needed about the complete airplane shown below

                                                     Beechcraft Queen Air Aircraft Data

                                                     W = 38,220 N
                                                     S = 27.3 m2
                                                     AR = 7.5
                                                     e (complete airplane) = 0.9
                                                     CD,0 (complete airplane) = 0.03

                                                     What thrust and power levels are required of
                                                     engines to cruise at 220 MPH at sea-level?
                                                     How would these results change at 15,000 ft
                                                                                                         2
                 OVERALL AIRPLANE DRAG
• No longer concerned with aerodynamic details
• Drag for complete airplane, not just wing




        Wing or airfoil                               Entire Airplane



                                    Engine Nacelles          Tail Surfaces



  Landing Gear




                                                                             3
                                DRAG POLAR
•   CD,0 is parasite drag coefficient at zero lift (aL=0)
•   CD,i drag coefficient due to lift (induced drag)
•   Oswald efficiency factor, e, includes all effects from airplane
•   CD,0 and e are known aerodynamics quantities of airplane




                     Example of Drag Polar for complete airplane      4
              4 FORCES ACTING ON AIRPLANE
• Model airplane as rigid body with four natural forces acting on it
  1. Lift, L
      • Acts perpendicular to flight path (always perpendicular to relative wind)
  2. Drag, D
      • Acts parallel to flight path direction (parallel to incoming relative wind)
  3. Propulsive Thrust, T
      • For most airplanes propulsive thrust acts in flight path direction
      • May be inclined with respect to flight path angle, aT, usually small angle
  4. Weight, W
      • Always acts vertically toward center of earth
      • Inclined at angle, q, with respect to lift direction

• Apply Newton’s Second Law (F=ma) to curvilinear flight path
   – Force balance in direction parallel to flight path
   – Force balance in direction perpendicular to flight path

                                                                                      5
       GENERAL EQUATIONS OF MOTION (6.2)




                                                   Free Body Diagram



Apply Newton’s 2nd Parallel to flight path:


Apply Newton’s 2nd Perpendicular to flight path:


                                                                       6
               LEVEL, UNACCELERATED FLIGHT
                                                  L



    T                                                                                   D



                                                  W
•   JSF is flying at constant speed (no accelerations)
•   Sum of forces = 0 in two perpendicular directions
•   Entire weight of airplane is perfectly balanced by lift (L = W)
•   Engines produce just enough thrust to balance total drag at this airspeed (T = D)
• For most conventional airplanes aT is small enough such that cos(aT) ~ 1
                                                                                            7
LEVEL, UNACCELERATED FLIGHT




        • TR is thrust required to fly at a given velocity in
          level, unaccelerated flight



        • Notice that minimum TR is when airplane is at
          maximum L/D
           – L/D is an important aero-performance quantity




                                                            8
                  THRUST REQUIREMENT (6.3)
• TR for airplane at given altitude varies with velocity
• Thrust required curve: T R vs. V∞




                                                           9
         PROCEDURE: THRUST REQUIREMENT
                                                  1. Select a flight speed, V ∞
                                                  2. Calculate CL


          Minimum TR when airplane
          flying at (L/D)max

                                                  3. Calculate CD




                                                  4. Calculate CL/CD
                                                  5. Calculate TR

This is how much thrust engine
must produce to fly at selected V∞

Recall Homework Problem #5.6, find (L/D)max for NACA 2412 airfoil                 10
                  THRUST REQUIREMENT (6.3)
• Different points on T R curve correspond to different angles of attack




 At b:
 Small q∞                                                             At a:
 Large CL (or CL2) and a to support W                                 Large q∞
 D large                                                              Small CL and a
                                                                      D large




                                                                                   11
THRUST REQUIRED VS. FLIGHT VELOCITY




    Zero-Lift TR     Lift-Induced TR
    (Parasitic Drag) (Induced Drag)



                                                  Zero-Lift TR ~ V2
                                                  (Parasitic Drag)

                                       Lift-Induced TR ~ 1/V2
                                       (Induced Drag)



                                                                      12
    THRUST REQUIRED VS. FLIGHT VELOCITY


                           At point of minimum TR, dTR/dV∞=0
                                      (or dTR/dq∞=0)




          CD,0 = CD,i at minimum TR and maximum L/D
Zero-Lift Drag = Induced Drag at minimum TR and maximum L/D
                                                               13
                   HOW FAST CAN YOU FLY?
• Maximum flight speed occurs when thrust available, T A=TR
  – Reduced throttle settings, T R < TA
  – Cannot physically achieve more thrust than T A which engine can provide




                                                     Intersection of TR
                                                     curve and maximum
                                                     TA defined maximum
                                                     flight speed of airplane




                                                                              14
    FURTHER IMPLICATIONS FOR DESIGN: V MAX
• Maximum velocity at a given altitude is important specification for new airplane
• To design airplane for given V max, what are most important design parameters?

                                                Steady, level flight: T = D

                                                Steady, level flight: L = W


                                                Substitute into drag equation

                                                Turn this equation into a quadratic
                                                equation (by multiplying by q ∞)
                                                and rearranging


                                                Solve quadratic equation and set
                                                thrust, T, to maximum available
                                                thrust, TA,max

                                                                                      15
    FURTHER IMPLICATIONS FOR DESIGN: V MAX




• TA,max does not appear alone, but only in ratio (T A/W)max
• S does not appear alone, but only in ratio (W/S)
• Vmax does not depend on thrust alone or weight alone, but rather on ratios
   – (TA/W)max: maximum thrust-to-weight ratio
   – W/S: wing loading
• Vmax also depends on density (altitude), C D,0, peAR
• Increase Vmax by
   – Increase maximum thrust-to-weight ratio, (TA/W)max
   – Increasing wing loading, (W/S)
   – Decreasing zero-lift drag coefficient, CD,0
                                                                               16
                  AIRPLANE POWER PLANTS

Two types of engines common in
  aviation today



1. Reciprocating piston engine with
   propeller
    – Average light-weight, general
       aviation aircraft
    – Rated in terms of POWER

2. Jet (Turbojet, turbofan) engine
    – Large commercial transports
        and military aircraft
    – Rated in terms of THRUST


                                          17
                          THRUST VS. POWER
• Jets Engines (turbojets, turbofans for military and commercial applications) are
  usually rate in Thrust
   – Thrust is a Force with units (N = kg m/s2)
   – For example, the PW4000-112 is rated at 98,000 lb of thrust

• Piston-Driven Engines are usually rated in terms of Power
   – Power is a precise term and can be expressed as:
       • Energy / time with units (kg m2/s2) / s = kg m2/s3 = Watts
           – Note that Energy is expressed in Joules = kg m 2/s2
       • Force * Velocity with units (kg m/s 2) * (m/s) = kg m2/s3 = Watts
   – Usually rated in terms of horsepower (1 hp = 550 ft lb/s = 746 W)

• Example:
   – Airplane is level, unaccelerated flight at a given altitude with speed V ∞
   – Power Required, PR=TR*V∞
   – [W] = [N] * [m/s]
                                                                                     18
           POWER AVAILABLE (6.6)

Propeller Drive Engine      Jet Engine




                                         19
           POWER AVAILABLE (6.6)

Propeller Drive Engine      Jet Engine




                                         20
POWER REQUIRED (6.5)




 PR vs. V∞ qualitatively

 (Resembles TR vs. V∞)




                           21
POWER REQUIRED (6.5)




         PR varies inversely as CL3/2/CD

         Recall: TR varies inversely as CL/CD
                                            22
     POWER REQUIRED (6.5)




Zero-Lift PR   Lift-Induced PR




                                     Zero-Lift PR ~ V3


                                 Lift-Induced PR ~ 1/V




                                                         23
POWER REQUIRED




  At point of minimum PR, dPR/dV∞=0




                                      24
                        POWER REQUIRED
• V∞ for minimum PR is less than V ∞ for minimum TR




                                                      25
              WHY DO WE CARE ABOUT THIS?
• We will show that for a piston-engine propeller combination
  – To fly longest distance (maximum range) we fly airplane at speed
     corresponding to maximum L/D
  – To stay aloft longest (maximum endurance) we fly the airplane at minimum
     PR or fly at a velocity where CL3/2/CD is a maximum

• Power will also provide information on maximum rate of climb and altitude




                                                                              26
POWER AVAILABLE AND MAXIMUM VELOCITY (6.6)




                 Propeller Drive
                    Engine



                                          PA

                      PR




             1 hp = 550 ft lb/s = 746 W
                                               27
POWER AVAILABLE AND MAXIMUM VELOCITY (6.6)




              Jet Engine




                       PR




                                         28
ALTITUDE EFFECTS ON POWER REQUIRED AND AVAILABLE (6.7)

      Recall PR = f(r∞)
      Subscript ‘0’ denotes seal-level conditions




                                                         29
ALTITUDE EFFECTS ON POWER REQUIRED AND AVAILABLE (6.7)
                 Propeller-Driven Airplane




                 Vmax,ALT < Vmax,sea-level
                                                         30
                     RATE OF CLIMB (6.8)

• Boeing 777: Lift-Off Speed ~ 180 MPH
• How fast can it climb to a cruising altitude of 30,000 ft?




                                                               31
             RATE OF CLIMB (6.8)




Governing Equations:

                                   32
             RATE OF CLIMB (6.8)




                                         Vertical velocity

   Rate of Climb:


TV∞ is power available
DV∞ is level-flight power required (for small q neglect W)
TV∞- DV∞ is excess power

                                                             33
               RATE OF CLIMB (6.8)

Propeller Drive Engine               Jet Engine




  Maximum R/C Occurs when Maximum Excess Power



                                                  34
                         EXAMPLE: F-15 K
• Weapon launched from an F-15 fighter by a small two stage rocket, carries a heat-
  seeking Miniature Homing Vehicle (MHV) which destroys target by direct impact
  at high speed (kinetic energy weapon)
• F-15 can bring ALMV under the ground track of its target, as opposed to a ground-
  based system, which must wait for a target satellite to overfly its launch site.




                                                                                 35
GLIDING FLIGHT (6.9)




            To maximize range, smallest
            q occurs at (L/D)max

                                      36
EXAMPLE: HIGH ASPECT RATIO GLIDER




                                                      q




    To maximize range, smallest q occurs at (L/D)max
 A modern sailplane may have a glide ratio as high as 60:1
                  So q = tan-1(1/60) ~ 1°
                                                             37
   RANGE AND ENDURANCE

                 How far can we fly?
              How long can we stay aloft?

How do answers vary for propeller-driven vs. jet-engine?
                     RANGE AND ENDURANCE
•   Range: Total distance (measured with respect to the ground) traversed by airplane
    on a single tank of fuel
•   Endurance: Total time that airplane stays in air on a single tank of fuel

1. Parameters to maximize range are different from those that maximize endurance
2. Parameters are different for propeller-powered and jet-powered aircraft



•   Fuel Consumption Definitions
     – Propeller-Powered:
         • Specific Fuel Consumption (SFC)
         • Definition: Weight of fuel consumed per unit power per unit time

    – Jet-Powered:
       • Thrust Specific Fuel Consumption (TSFC)
       • Definition: Weight of fuel consumed per unit thrust per unit time
                                                                                   39
 PROPELLER-DRIVEN: RANGE AND ENDURANCE
• SFC: Weight of fuel consumed per unit power per unit time




• ENDURANCE: To stay in air for longest amount of time, use minimum
  number of pounds of fuel per hour




• Minimum lb of fuel per hour obtained with minimum HP
• Maximum endurance for a propeller-driven airplane occurs when
  airplane is flying at minimum power required
• Maximum endurance for a propeller-driven airplane occurs when
  airplane is flying at a velocity such that C L3/2/CD is a maximized
                                                                        40
 PROPELLER-DRIVEN: RANGE AND ENDURANCE
• SFC: Weight of fuel consumed per unit power per unit time




• RANGE: To cover longest distance use minimum pounds of fuel per mile




• Minimum lb of fuel per hour obtained with minimum HP/V ∞
• Maximum range for a propeller-driven airplane occurs when airplane
  is flying at a velocity such that C L/CD is a maximum


                                                                     41
  PROPELLER-DRIVEN: RANGE BREGUET FORMULA




• To maximize range:
   – Largest propeller efficiency, h
   – Lowest possible SFC
   – Highest ratio of W initial to Wfinal, which is obtained with the largest fuel weight
   – Fly at maximum L/D




                                                                                        42
PROPELLER-DRIVEN: RANGE BREGUET FORMULA




  Propulsion                  Structures and Materials
               Aerodynamics




                                                         43
  PROPELLER-DRIVEN: ENDURACE BREGUET FORMULA




• To maximize endurance:
   – Largest propeller efficiency, h
   – Lowest possible SFC
   – Largest fuel weight
   – Fly at maximum CL3/2/CD
   – Flight at sea level


                                               44
     JET-POWERED: RANGE AND ENDURANCE
• TSFC: Weight of fuel consumed per thrust per unit time




• ENDURANCE: To stay in air for longest amount of time, use minimum
  number of pounds of fuel per hour




• Minimum lb of fuel per hour obtained with minimum thrust
• Maximum endurance for a jet-powered airplane occurs when
  airplane is flying at minimum thrust required
• Maximum endurance for a jet-powered airplane occurs when
  airplane is flying at a velocity such that C L/CD is a maximum
                                                                      45
     JET-POWERED: RANGE AND ENDURANCE
• TSFC: Weight of fuel consumed per unit power per unit time




• RANGE: To cover longest distance use minimum pounds of fuel per mile




• Minimum lb of fuel per hour obtained with minimum Thrust/V ∞




• Maximum range for a jet-powered airplane occurs when airplane is
  flying at a velocity such that C L1/2/CD is a maximum
                                                                     46
    JET-POWERED: RANGE BREGUET FORMULA




• To maximize range:
   – Minimum TSFC
   – Maximum fuel weight
   – Flight at maximum CL1/2/CD
   – Fly at high altitudes




                                         47
JET-POWERED: ENDURACE BREGUET FORMULA




• To maximize endurance:
   – Minimum TSFC
   – Maximum fuel weight
   – Flight at maximum L/D




                                    48
           SUMMARY: ENDURANCE AND RANGE
•   Maximum Endurance
     – Propeller-Driven
         • Maximum endurance for a propeller-driven airplane occurs when airplane is
           flying at minimum power required
         • Maximum endurance for a propeller-driven airplane occurs when airplane is
           flying at a velocity such that CL3/2/CD is a maximized
     – Jet Engine-Driven
         • Maximum endurance for a jet-powered airplane occurs when airplane is
           flying at minimum thrust required
         • Maximum endurance for a jet-powered airplane occurs when airplane is
           flying at a velocity such that CL/CD is a maximum

•   Maximum Range
     – Propeller-Driven
         • Maximum range for a propeller-driven airplane occurs when airplane is flying
           at a velocity such that CL/CD is a maximum
     – Jet Engine-Driven
         • Maximum range for a jet-powered airplane occurs when airplane is flying at a
           velocity such that CL1/2/CD is a maximum
                                                                                     49
EXAMPLES OF DYNAMIC
   PERFORMANCE

     Take-Off Distance
      Turning Flight
TAKE-OFF AND LANDING ANALYSES (6.15)




                            Rolling resistance
                            mr = 0.02




     s: lift-off distance
                                                 51
NUMERICAL SOLUTION FOR TAKE-OFF




                                  52
         USEFUL APPROXIMATION (T >> D, R)
sL.O.: lift-off distance




• Lift-off distance very sensitive to weight, varies as W 2
• Depends on ambient density
• Lift-off distance may be decreased:
   – Increasing wing area, S
   – Increasing CL,max
   – Increasing thrust, T




                                                              53
EXAMPLES OF GROUND EFFECT




                            54
TURNING FLIGHT




                 Load Factor




R: Turn Radius



 w: Turn Rate
                               55
EXAMPLE: PULL-UP MANEUVER




                      R: Turn Radius


                      w: Turn Rate




                                       56
V-n DIAGRAMS




               57
STRUCTURAL LIMITS




                    58

								
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