Flight Theory And Aerodynamics 4th Edition Joseph R. Badick; Brian A. Johnson - Solutions

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Convert 65 kts. to fps.
Convert 200 fps to kts.
Convert 35 kts. to fpm.
Convert 52 nm to sm.
An airplane weighs 16 000 lb. The local gravitational acceleration g is 32.2 fps2. What is the mass of the airplane?
The airplane in Problem 5 accelerates down the runway with a net forward force (thrust less drag) of 6000 lb. Find the acceleration of the airplane.Data from problem 5An airplane weighs 16 000 lb. The local gravitational acceleration g is 32.2 fps2. What is the mass of the airplane?
The airplane in Problem 6 starts from a brakes‐locked position on the runway. The airplane takes off at an airspeed of 200 fps. Find the time for the aircraft to reach takeoff speed.
Under no‐wind conditions, what takeoff roll is required for the aircraft in Problem 7?
Upon reaching a velocity of 100 fps, the pilot of the airplane in Problem 7 decides to abort the takeoff and applies brakes and stops the airplane in 1000 ft. Find the airplane’s deceleration.
An airplane is towing a glider to altitude. The tow rope is 20°below the horizontal and has a tension force of 300 lb exerted on it by the airplane. Find the horizontal drag of the glider and the amount of lift that the rope is providing to the glider. Sin 20° = 0.342; cos 20° = 0.940.
A jet airplane is climbing at a constant airspeed in no‐wind conditions. The plane is directly over a point on the ground that is 4 statute miles from the takeoff point and the altimeter reads 15 840 ft. Find the plane’s climb angle and the distance that it has flown through the air.
Find the distance s and the force F on the seesaw fulcrum shown in the figure. Assume that the system is in equilibrium. 20 lb ks- F -24 ft- 10 lb
A helicopter has a rotor diameter of 30 ft and it is being operated in a hover at 286.5 rpm. Find the tip speed Vt of the rotor.
An airplane weighs 16 000 lb and is flying at 5 000 ft altitude and at an airspeed of 200 fps. Find (a) the potential energy, (b) the kinetic energy, and (c) the total energy. Assuming no extra drag on the airplane, if the pilot drove until the airspeed was 400 fps, what would the altitude be?
An aircraft’s turbojet engine produces 10 000 lb of thrust at 162.5 kts. true airspeed. What is the equivalent power that it is producing?
An aircraft weighs 24 000 lb and has 75% of its weight on the main (braking) wheels. If the coefficient of friction is 0.7, find the braking force Fb on the airplane.
Newton’s third law of motion states:a. A body at rest will remain at rest and a body in motion will remain in motion, in a straight line, unless acted upon by an unbalanced force.b. For every action force there is an equal and opposite reaction force.c. If a body is acted on by an unbalanced
An aircraft parked on an airport ramp would be an example of Newton’s _______ law of motion.a. first.b. second.c. fourth.d. third.
An airplane in level flight increases thrust, resulting in an acceleration until once again thrust equals:a. aerodynamic force.b. lift.c. weight.d. drag.
An airplane in straight‐and‐level, unaccelerated flight weighs 2300 lb, what total lift must the aircraft produce to maintain a constant altitude assuming no additional forces are involved:a. 2000 lbb. 2300 lbc. 1150 lbd. >2300 lb
An increase in static air pressurea. affects air density by decreasing the density.b. does not affect air density.c. affects air density by increasing the density.
A decrease in temperaturea. affects air density by decreasing the density.b. does not affect air density.c. affects air density by increasing the density.
Pressure ratio isa. ambient pressure divided by sea level standard pressure measured in the same units.b. ambient pressure in millibars divided by 29.92.c. ambient pressure in pounds per square inch divided by 2116.d. sea level standard pressure in inches of mercury divided by 29.92.
Density ratio, σ (sigma) isa. equal to pressure ratio divided by temperature ratio.b. measured in slugs per cubic foot.c. equal to the ambient density divided by sea level standard pressure.d. None of the above.
According to Table 2.1, the value for the density ratio on a standard day at sea level is:a. 0.861 7b. 1.0c. 1.5d. 0.002 377
Bernoulli’s equation for subsonic flow states thata. if the velocity of an airstream within a tube is increased, the static pressure of the air increases.b. if the area of a tube decreases, the static pressure of the air increases.c. if the velocity of an airstream within a tube increases, the
Dynamic pressure of an airstream isa. directly proportional to the square of the velocity.b. directly proportional to the air density.c. Neither (a) nor (b).d. Both (a) and (b).
In this book, we use the formula for dynamic pressure, q = σV2K/295, rather than the more conventional formula, q = 1/2ρV2, becausea. V in our formula is measured in kts.b. density ratio is easier to handle (mathematically) than the actual density (slugs per cubic foot).c. Both (a) and (b).d.
True altitude equals indicated altitude:a. below flight level 180.b. during standard conditions.c. when the altimeter is set to 29.92”.d. only when the temperature is standard regardless of pressure.
Which of the following determines the vertical altitude above the ground:a. pressure altitude.b. indicated altitude.c. true altitude.d. absolute altitude.
The corrections that must be made to indicated airspeed (IAS) to obtain calibrated airspeed (CAS) area. position error and compressibility error.b. instrument error and position error.c. instrument error and density error.d. position error and density error.
The correction that must be made to CAS to obtain equivalent airspeed (EAS) is called compressibility error, whicha. is always a negative value.b. can be ignored at high altitude.c. can be ignored at high airspeed.d. can be either a positive or a negative value.
The correction from EAS to true airspeed (TAS) is dependent ona. temperature ratio alone.b. density ratio alone.c. pressure ratio alone.d. None of the above.
Groundspeed equals ______ when zero wind at altitude.a. equivalent airspeed.b. indicated airspeed.c. true airspeed.d. calibrated airspeed.
An airplane is operating from an airfield that has a barometric pressure of 27.82″ Hg and a runway temperature of 100 °F. Calculate (or find in Table 2.1)the following:a. Pressure ratio.b. Pressure altitude.c. Temperature ratio.d. Density ratio.e. Density altitude.
Fill in the values below for the stations in the drawing. 1 2 At station 1 At station 2 At station 3 A 10 ft 4, 5 ft V3 = 80 kts. V = 100 kts. V = ? A3 = ? = P 2030 psf P2 = ? P3 = ? = 0.968 H = ? 92 = ? 93 = ? 3
Using Table 2.1, calculate the dynamic pressure, q at 5000 ft density altitude and 200 kts. TAS.
The airspeed indicator of an airplane reads 355 kts. There are no instrument or position errors. If the airplane is flying at a pressure altitude of 25 000 ft, find the equivalent airspeed (EAS).
Find the true airspeed (TAS) of the airplane in Problem 18 if the outside air temperature is −40 °C.
Using the TAS from the previous example, when a = 594.5 kts., calculate the Mach number for the aircraft.
Flight control systems are of two types:a. first and second.b. primary and secondary.c. trim systems and tabs.d. balanced and imbalanced.
During a turn to the right, the aileron on the right wing is deflected:a. up.b. down.c. in the same direction as the aileron on the left wing.d. neither up or down as it remains stationary.
During the transition from level flight to a climb attitude in a light aircraft, as the control stick is moved aft, the elevator or stabilator is positioned to produce a _______ by deflecting the elevator/stabilator _______.a. a tail‐up force/upward.b. a tail‐down force/upward.c. a tail‐down
The rudder controls movement around the:a. longitudinal axis.b. lateral axis.c. vertical axis.
Deploying trailing edge flaps increases lift and drag.a. Trueb. False
Number 3 on the drawing showsa. the chord line.b. the maximum camber.c. the thickness.d. the mean camber line.
Number 4 on the drawing showsa. the chord line.b. the thickness.c. the maximum camber.d. the mean camber line.
Number 5 on the drawing showsa. the maximum camber.b. the mean camber line.c. the upper‐surface curvature.d. the maximum thickness.
Which of the following is not considered a primary variable in the geometry of an airfoil?a. airfoil composition.b. shape of the mean camber line.c. leading edge radius.d. location of the maximum thickness.
The Magnus effect explains whya. a bowling ball curves.b. a pitched baseball curves.c. a golf ball slices.d. Both (b) and (c).
Which of the following will develop positive lift?a. A symmetrical airfoil at zero AOA.b. A nonrotating cylinder in a wind tunnel.c. A cambered airfoil at zero AOA.
Which of the following will not produce a pitching moment?a. A symmetrical airfoil at a positive AOA.b. A cambered airfoil that is developing zero lift.c. A cambered airfoil that is at a positive AOA.d. A symmetrical airfoil at zero AOA.e. Both (a) and (d).
The aerodynamic center (AC) is located ata. 50% C subsonically and 25% C supersonically.b. 25% C at all speeds.c. 50% C at all speeds.d. 25% C subsonically and 50% C supersonically.
For a cambered airfoil, the center of pressure (CP)a. moves to the rear of the wing at low AOA.b. moves backward as AOA increases.c. moves forward as AOA increases.d. Both (a) and (c).
Which of these statements is false? For a cambered airfoil,a. the AC is where all changes in lift effectively take place.b. there is no pitching moment at the AC.c. the AC is located near 25% C subsonically.d. the pitching moment at the AC is constant with change of AOA (at constant airspeed).
For a symmetrical airfoil,a. the center of pressure moves forward as AOA increases.b. the center of pressure stays at the same place as AOA increases.c. there is no pitching moment about the CP.d. Both (b) and (c).
As thickness of an airfoil is increased, the critical AOAa. is greater.b. is less.c. remains the same.
As camber of an airfoil is increased, its CL at any AOAa. is less.b. remains the same.c. is greater.
The Coanda effect is an example of:a. Newton’s second law.b. Newton’s third law.c. Newton’s first law.d. Bernoulli’s equation.
Air in the boundary layera. has zero velocity at the wing surface.b. is turbulent near the leading edge.c. is more apt to stall if it is turbulent.d. None of the above
Air in the boundary layera. changes from laminar to turbulent at low Reynolds numbers.b. separates from the wing when its velocity is maximum.c. reverses flow direction when stall occurs.d. None of the above.
Two things an airfoil designer can change to increase CL(max) area. thickness and wing area.b. chord length and aspect ratio.c. camber and wing span.d. thickness and camber.
High values of the Reynolds number will more likelya. occur near the leading edge of an airfoil.b. indicate laminar flow.c. occur at lower airspeeds.d. show turbulent airflow.
Adverse pressure gradient on an airfoil is founda. from the point of maximum thickness to the trailing edge.b. near the stagnation point at the leading edge.c. from the point of minimum pressure to the trailing edge.d. Both (a) and (c).
At low‐velocity stall, the airflowa. stops.b. reverses direction.c. speeds up.d. moves toward the wingtips.
Airflow separation can be delayed bya. making the wing surface rough.b. using vortex generators.c. directing high‐pressure air to the top of the wing or flap through slots.d. All of the above.
Show which type of high‐CL device (camber changer, energy adder, or combination) each of the below is:a. Blowing air (BLC) over a flap_____b. Fixed slot_____c. Slotted leading‐edge flap_____d. Plain flap_____
An airplane in flight encounters wing icing. The greatest danger is thata. weight is increased.b. CD is increased.c. CL is decreased.d. All of the above.
According to Figure 4.12, what is the corresponding AOA if the CL is 0.8?a. 4°b. 6°c. 8°d. 10° Level stall airspeed at gross weight is 38 kts. Stall speed: 41 kts. 30 Stall speed: 45 kts. Stall speed: 53 kts. 45 60 TAS 40 mph Turn radius 185 ft Turn radius 107 ft Turn radius 062 ft TAS 60 mph
Find the CL on an airfoil given the following information:Weight = 14 000 lb Wing area, S = 134 ft2 TAS = 140 kts.Sea level, standard day
Find the lift on an airfoil using Figure 4.12 and Table 2.1 given the following information:AOA = 12°Wing area, S = 110 ft2 TAS = 130 kts.Pressure altitude = 8000 ft Temperature – Standard Day Level stall airspeed at gross weight is 38 kts. Stall speed: 41 kts. 30 Stall speed: 45 kts. Stall
An aircraft has the CL–α curve shown in Figure 4.12. The following data applies:Weight = 20 000 lb Wing area, S = 340 ft2Density altitude = 10 000 ft TAS = 242.4 kts.Find the aircraft’s AOA for steady flight:_____ Level stall airspeed at gross weight is 38 kts. Stall speed: 41 kts. 30 Stall
Calculate the stall speed for the aircraft in Problem 16:_____
If the airplane in Problem 16 burns 5000 lb of fuel during its flight, calculate its new stall speed:_____
An airplane has a rectangular wing with a chord length of 8 ft. If the airplane is flying at 200 kts. TAS and at 20 000 ft density altitude, find the Reynolds number at the trailing edge of the wing.
Find the stall speed (VS) for an aircraft at sea level, standard day with the following information:CL = Use Figure 4.12 Wing area, S = 110 ft2Weight = 11 000 lb 1G Flight Level stall airspeed at gross weight is 38 kts. Stall speed: 41 kts. 30 Stall speed: 45 kts. Stall speed: 53 kts. 45 60 TAS 40
The coefficient of drag can be defined asa. the ratio of lift forces to drag forces.b. a measure of the efficiency of the airplane.c. the ratio of drag forces to lift forces.d. the ratio of drag pressure to dynamic pressure.
Laminar flow airfoils have less drag than conventional airfoilsa. in the high‐CL region.b. in the high‐AOA region.c. in the high‐speed region.d. in the landing phase of flight.
Laminar flow airfoils have less drag than conventional airfoils becausea. the adverse pressure gradient starts farther back on the airfoil.b. the airfoil is thinner.c. more of the airflow is laminar.d. Both (a) and (c).
Lift/drag ratio isa. a measure of the aircraft’s efficiency.b. a maximum when the drag is a minimum.c. numerically equal to the glide ratio.d. All of the above.
Two aircraft with the same wing area have different wing spans, with all other airfoil characteristics being equal, the aircraft with the longer wing span will:a. experience a lower induced drag.b. experience a higher induced drag.c. wing span does not impact the amount of induced drag if wing area
An airplane flying at CL(max) will havea. more parasite drag than induced drag.b. more induced drag than parasite drag.c. equal amounts of parasite and induced drag.d. Not enough information is given to evaluate the drag.
Induced drag isa. more important to low aspect ratio airplanes than to high aspect ratio airplanes.b. reduced when the airplane enters ground effect.c. reduced if the airplane has winglets.d. All of the above.
Induced drag results from the lift vector being tilted to the rear, becausea. the tip vortices cause downwash behind the wing.b. the relative wind behind the wing is pushed downward.c. the local relative wind at the AC is depressed.d. All of the above.
An airplane with a heavy load _____ it can lightly loaded.a. can glide farther thanb. cannot glide as far asc. can glide the same distance as
If an airplane has a symmetrical wing that has an angle of incidence of 0° during takeoff, all the drag isa. profile drag.b. parasite drag.c. wave drag.d. induced drag.
Which of the following is not a characteristic of ground effect on an aircraft while crossing the runway threshold during landing:a. increase in induced drag.b. nose‐down pitching moment.c. airspeed indicator reads lower than normal.d. decrease in AOA to maintain same CL.
A low‐tailed airplane with static ports beneath the wing leaves ground effect after takeoff. It will have:a. increased drag, nose‐up pitch, lowered IAS.b. increased drag, nose‐up pitch, higher IAS.c. decreased drag, nose‐down pitch, lowered IAS.d. decreased drag, nose‐up pitch, higher IAS.
In Figure 5.24, what is the value of CLmax?a. 1.5b. 12.5c. 0.1500d. 1.3
In Figure 5.24, what is the value of (L/D)max?a. 1.3b. 0.1250c. 12.5d. 1.0
Calculate the aspect ratio given the following:Wing span = 36 ft Wing area = 174 ft2
An aircraft has a Di of 750 lb when at (L/D)max, what is the value of Dp?
A 10 000 lb aircraft has a (L/D)max value of 9.8; find its minimum drag.
If the aircraft in Problem 17 has a wing area S = 200 ft2 and the value of CL = 0.5 at (L/D)max, find the sea level airspeed where Dmin occurs.
For the aircraft in Problem 17, find Di and Dp at (L/D)max.
For the aircraft in Problem 17, complete the following table and plot Di, Dp, and DT on a sheet of graph paper. V2 (V2/V1) D = Dmin (V2/V) (V1/V2) D = Dmin(V1/V2) DT = Dp + Di 125 150 172 200 300 400
The equation Ta = Q(V2 − V1) shows thata. you can get more thrust from a jet engine by using water injection.b. you can get more thrust from a jet engine by decreasing the exhaust pipe area.c. Neither (a) nor (b).d. Both (a) and (b).
Q in Ta = Q(V2 − V1) is the mass flow (slugs/s). The mass flow depends ona. the cross‐sectional area of the turbojet engine inlet.b. the engine inlet velocity.c. the density of the air at the same point.d. All of the above.
The equation ηp = 2V1/(V2 + V1) shows that decreasing the exhaust pipe area willa. decrease the propulsive efficiency of a jet engine.b. increase the propulsive efficiency.c. increase the thrust of the engine.d. decrease the thrust of the engine.
Specific fuel consumption of a turbine engine at 35 000 ft altitude compared to that at sea level isa. less.b. more.c. the same.

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Flight Theory And Aerodynamics 4th Edition Joseph R. Badick; Brian A. Johnson - Solutions

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