2.20 The total pressure of the airstream is the sum of the static pressure and the __________________. All we need to do is go to the turn equations and find the desired airspeed and load factor (n), put these into the equation and plot it. To see if we can climb at the desired rate over a reasonable range of altitudes we would need to look at the climb relationship: This would give us another value of thrust needed to reach the target rate of climb for a given weight and, since the equation contains power required, which is drag times speed, the wing area would also be a factor. b. If, for example, we went all out to create a plane that could takeoff in a very short distance and then look at its performance in straight and level cruise we would probably find that it isnt very good. We would also need to look at these requirements and our design objectives. 2.15 The standard unit of measure for static pressure for pilots and altimeter settings is: 2.17 At _____________ altitude the static pressure is about half that at sea level. 7.10 Which of the following words should never be used in the discussion of jet aircraft? 11.18 Which factor affects the calculation of landing performance for a typical aircraft? 5.6 Which of the following is a type of parasite drag? 5.24 For a given aircraft wing, if the wing span remains the same but the wing area increases, the aspect ratio will ____________. One way to resolve this issue is to write our equations in terms of ratios of thrust at altitude divided by thrust at sea level and weight at altitude divided by weight at takeoff. For low angles of climb (non high performance aircraft) airspeed may be directly compared to vertical velocity, as the cosine of lower angles is very close to 1. 7.18 Increasing the weight of a thrust-producing aircraft moves all points on the thrust-required curve ____________. Is email scraping still a thing for spammers. And both approaches are maximizing the same angle on the right triangle comprised of the vertical speed, horizontal speed, and airspeed vectors. How does a fixed-pitch propeller changes the blade's angle of attack? 11.24 If an aircraft traveling down a runway has a tire pressure of 50 psi and no other information is available, the approximate speed to which total dynamic hydroplaning may occur is __________. 1.15 An airplane is climbing at a constant airspeed in no-wind conditions. 3.13 thru 3.17 Reference Figure 2. An iterative solution may be necessary. What group uses the most electrical energy? Each plot of the specific power equation that we add to this gives us a better definition of our design space. 4.16 Laminar airflow over a smooth airfoil like a wing begins at the _____________. V e = 2 W S L S C L = 794.1 f p s. The angle of climb for maximum rate of climb (not maximum angle of climb) can then be found as follows: sin = T D W = T W C D / C L = 0.429 0.013 + 0.157 (0.088) 2 0.088 = 0.267. = 15.51 2.14 The energy of an airstream is in two forms: It has potential energy, which is what kind of pressure? Aircraft Design: A Conceptual Approach, AIAA, Washington, DC. See also. 13.21 As the weight of an aircraft decreases, the VA. 13.22 ______________ of the total lift is the centripetal force that causes radial acceleration. The LibreTexts libraries arePowered by NICE CXone Expertand are supported by the Department of Education Open Textbook Pilot Project, the UC Davis Office of the Provost, the UC Davis Library, the California State University Affordable Learning Solutions Program, and Merlot. Making statements based on opinion; back them up with references or personal experience. Note also that the units of the graph need not be the same on each axis for this method to work. Excess power is power available minus power required. 7.25 To obtain maximum range for a thrust-producing aircraft, as fuel is burned _______________. For a turbojet aircraft with a drag equation described by: C D = C D 0 + K C L 2. with C D 0 = 0.012, and K = 0.035, a wing area of 70 m 2, a weight of 120.000 kN, and a maximum lift coefficient of 1.900, capable of producing a thrust of 120.000 kN at a given altitude, the climb rate and angles can be taken from the . It weighs 2,605 lbs and has a maximum takeoff weight (MTOW) of 3,650 lbs. Aircraft Design: A Conceptual Approach, AIAA, Washington, DC. To get best range now the pilot must, Slow down by an amount less than the wind speed, 6.8 To obtain maximum range a jet airplane must be flown at, 6.9 Maximum rate of climb for a jet airplane occurs at, 6.10 Maximum climb angle for a jet aircraft occurs at. 7.20 When a pilot lowers the landing gear, _______________ is increased. To answer this, plot range versus aspect ratio using e.= 0.8 and varying AR from 4 through 10, and plot range versus e for an aspect ratio of 7.366 with e varying from 0.6 through 1.0. This can be determined from the power performance information studied in the last chapter. We would then have to decide which of these three requirements was most important and which was least important and then start varying design parameters in an iterative manner until we got all three objectives to result in the same weight, wing area, and engine thrust. Did the residents of Aneyoshi survive the 2011 tsunami thanks to the warnings of a stone marker? (More characteristic of a jet with a high thrust loading -- see diagram on this answer --. The local gravitational acceleration g is 32 fps2. @quietflyer It does not matter as long as the units are the same. This limits your maximum allowable propeller diameter to 72 inches (36" x 2" = 72"). There are many good textbooks available on aircraft design and the Raymer text referenced earlier is one of the best. Now we can expand the first term on the right hand side by realizing that. where , for example, and .The power available is a function of the propulsion system, the flight velocity, altitude, etc. One that is fairly easy to deal with is turning. Legal. Note that this equation does not represent an actual aircraft polar; it refers to the initial climb-out after takeoff. This can be put into the drag equation with the numbers found above to get the thrust or power needed to reach that maximum speed. <> 10.12 The following items all affect takeoff performance except __________. To include drag due to engine failure at low thrust/ weight ratios, E may be reduced by approx-imately 4% for wing-mounted engines and 2% for engines mounted on either side of the fuselage tail. In many aircraft the difference between horizontal speed and airspeed will be trivial. b. Available from https://archive.org/details/hw-9_20210805. 8.24 Though a turboprop produces power and thrust, the amount of thrust produced directly by the engine is only about what percentage of the total? Available from https://archive.org/details/9.4_20210805. <> xYr7 _+(DL/HHMl>K miD%D./3QgBNgl<=Had5>fzhIQ6?|6]ot@{y 8.6 Propeller aircraft are more efficient than jet aircraft because, They process more air and don't accelerate it as much, 8.7 Turboprop aircraft are classified as power producers because. 11.1, what is the minimum landing distance required (50 ft obstacle on final approach) for the given aircraft with the following conditions: 30C OAT, PA 2000 ft, weight 2800 lb., 5-kt tailwind? a. Plotting it as Peter Kampf did yields the airspeed of maximum climb angle. The desire for minimum thrust is obvious, based on the need to minimize fuel consumption and engine cost. Classify the monosaccharide structure in Problem 18.71 as an \alpha-anomer or a \beta-anomer. 11.1 A steep, low-power approach is more dangerous for heavy airplanes than light airplanes because, 11.2 Braking action on a dry concrete runway is ____________ that of a wet runway. Adapted from Raymer, Daniel P. (1992). Raymer, Daniel P. (1992). Again it is common for aircraft design texts to propose approximate or semi-empirical relationships to describe this and those relationships show landing distance to depend only on the wing loading. @quietflyer: Yes, this requires another arithmetical operation because airspeed is the vector sum of vertical and horizontal speed. Figure 9.3: James F. Marchman (2004). Effect of Aircraft Parameters on Takeoff Distance. CC BY 4.0. 4.17 Laminar flow involves the rapid intermixing of the air levels over a wing. 12.23 An aircraft in which of the following situations is most likely to create the most intense wake turbulence? 10.20 One of the dangers of overrotation is ________________. Does an airfoil drag coefficient takes parasite drag into account? Adapted from James F. Marchman (2004). Normally we would look at turns at sea level conditions and at takeoff weight. How can I find the maximum climb angle of a propeller driven aircraft from a graph of vertical velocity against airspeed? Finding this value of drag would set the thrust we need for cruise. This ratio is a measure of aerodynamic efficiency as well as a measure of the way the structure is designed. 5. max thickness. 12.16 All speeds below the speed for minimum drag are said to be in the _________. I've read the other thread about the throttles, reversing, and feathering. Best Rate of Climb And a big wing area gives us high drag along with high lift. 6.15 Which one of the following items does not occur at (L/D)max for a jet aircraft? AERO 1020 Final Review: All Past Test Q's/A's, Genetics Lecture 13 - DNA Chem and Replication. Hence, what we have done through the specific excess power relationship is nothing but a different way to get a familiar result. The type of aircraft, airspeed, or other factors have no influence on the load factor. But through good use of things like constraint analysis methods we can turn those compromises into optimum solutions. And this can be written [W/S] = Vstall2CLmax, On the plot above this would be a vertical line, looking something like this. 2245 To escape wake turbulence a pilot should avoid, 12.9 Wake turbulence is typically characterized by. Interesting airplane; looks like Vy is more than double Vx! c. By how many fringes will this water layer shift the interference pattern? In the proceeding chapters we have looked at many aspects of basic aircraft performance. You are correct that Vy will give you the max RoC. It usually is restricted to either the takeoff setting or the cruise setting. The best answers are voted up and rise to the top, Not the answer you're looking for? The takeoff equation seen in an earlier chapter is somewhat complex because takeoff ground distances depend on many things, from drag coefficients to ground friction. You don't have to know all three of these values-- any two are sufficient, and in this case you'll know the airspeed and the vertical speed. If we want an airplane that only does one thing well we need only look at that one thing. 9.11 As a power-producing aircraft burns off fuel, airspeed should be ____________ to maintain maximum range. 4.23 Stall is airflow separation of the boundary layer from the lifting surface. False Propeller aircraft are more efficient than jet aircraft because: They process more air and don't accelerate it as much Turboprop aircraft are classified as power producers because: Both A and C: The maximum angle of climb would occur where there exists the greatest difference between thrust available and thrust required; i.e., for the propeller-powered airplane, the maximum excess thrust and angle of climb will occur at some speed just above the stall speed. 3.24 The most common high-lift devices used on aircraft are _______________. 1.2 The aerodynamic component that is 90 to the flight path and acts toward the top of the airplane is called: 1.3 The aerodynamic component that is parallel to the flight path and acts toward the rear of the airplane is called: 1.4 The measure of the amount of material contained in a body is called: 1.5 The force caused by the gravitational attraction of the earth, moon, or sun is called: 1.6 A quantity that has both magnitude and direction is called: 1.7 An aircraft flying from AUO to ATL at 5,000 feet and 110 KIAS is said to have what kind of quantity? 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While you are at it, just the sake of curiosity you might want to also calculate the arctangent of (vertical speed / airspeed) for the same data point. nautical miles per hour) and vertical speed (feet per minute). This presents somewhat of a problem since we are plotting the relationships in terms of thrust and weight and thrust is a function of altitude while weight is undoubtedly less in cruise than at takeoff and initial climb-out. To takeoff in a short distance we might want a high maximum lift coefficient to get a low takeoff speed, a large wing area to give a lot of lift at low speed, and a lot of thrust to accelerate to takeoff distance in as short a ground run as possible. Continue searching. This makes sense when one realizes that, unless reverse thrust is used in the landing ground run, thrust does not play a major role in landing. Best rate of climb, or Vy, maximizes velocity to obtain the greatest gain in altitude over a given period of time Vy is normally used during climb, after all obstacles have been cleared It is the point where the largest power is available Occurs above L/Dmax for a jet Occurs at L/Dmax for a prop Provies more visibility over the cowling Is a condition where the tire is lifted completely above the surface of the runway, Can occur at slower speeds and rather than the water lifting the tire from the pavement, the tire slips on a thin film, 11.7 If a pilot experiences an engine failure and attempts to "stretch the glide" (i.e., increases the angle of attack) the result will be, A decrease in horizontal distance traveled, 11.8 Airline aircraft primarily use _________ to slow the aircraft after landing. 3.2 The main variable(s) in the geometry of an airfoil are: 3.3 The angle between the relative wind and the chord line of an airfoil is the, 3.4 For a symmetrical airfoil, at 0o AOA, air passing over the wing results in, An equal increase in velocity over the top and bottom of the wing. The greatest danger(s) is that. 5.2 Wingtip vortices contribute to which type of drag? 13.4 (Reference Figure 5.4) What speed is indicated at point B? Note here that the weight in the equation is the landing weight but that in calculating this landing distance for design purposes the takeoff weight is usually used for general aviation aircraft and trainers and is assumed to be 0.85 times the takeoff weight for jet transports. 12.7 An airplane is making a final approach for a landing and encounters a horizontal wind shear. In computing FAR 25 climb performance, the effects of one engine inoperative must include not only a decrease in thrust, but an increase in drag due to: 1) windmilling drag of inoperative engine or windmilling or feathered drag of propeller. The number of distinct words in a sentence. Still looking for something? 4.22 The airflow in the boundary layer is acted on by two forces: friction forces and _____________. Calculate (or find in Table 2.1) the Density Ratio: 2.12 An airplane is operating from an airfield that has a barometric pressure of 28.86 in. 12.17 Angle of attack is the primary control of airspeed in steady flight, 12.18 When Trexceeds Ta, the only way to go is __________. pressure altitude / nonstandard temperature conditions. 9.5 To obtain maximum glide distance, a heavily loaded airplane must be flown at a higher airspeed than if it is lightly loaded, 9.6 The increase in the Pr curves for a weight increase is greater at low speeds than at high speeds because the increase in. Design goals might include a maximum speed in cruise of 400 mph and a maximum range goal of 800 miles, however these do not occur at the same flight conditions. where A = g[(T0/W) ]. 11.25 Using Fig. The analysis may suggest that some of the constraints (i.e., the performance targets) need to be relaxed. How does the Angle of attack vary from the root to the tip of a propeller for a fixed pitch prop? How many "extra" wavelengths does the light now travel in this arm? 2.23 Calculate the pressure altitude for an aircraft at an airport with a field elevation of 2,350 feet MSL when the current altimeter setting is 30.40". 7.22 The value of (L/D)max changes when the gear and flaps are lowered. In the figure above this will be either where the takeoff and climb curves intersect or where the takeoff and landing curves intersect. As a flight instructor and aircraft enthusiast, I have long admired the . 8.11 A propeller which has only one pitch setting is known as: 8.12 A propeller where the pilot can adjust the pitch setting in the air. If the two values are almost the same, that indicates that the airspeed and horizontal speed are so close as to be practically interchangeable, at least at that point on the performance curve. 1.19 An aircraft weighs 12,000 lbs. 4.21 When analyzing the air moving from the leading edge toward the trailing edge of a wing, until the air reaches the point of minimum pressure it is in a favorable pressure gradient. c. How did you infer those two answers from a pie chart? 7.13 (Reference Figure 7.2) Using Figure 7.2, find the velocity for maximum endurance for the airplane at 12,000 lbs. RWY 27L & 27R), and the winds are 360/5, which choice(s) is/are true? Turboprop aircraft are classified as power producers because: Helicopters have another power requirement over fixed wing propeller airplanes. You need not use the actual point where the straight line touches the curve. Lets look at how the equation can be rearranged to help us examine the performance needs in various types of flight. Hg and a runway temperature of 20C. The more efficient a plane is in things like cruise the lower its value of T/W. 13.9 (Reference Figure 5.4) What is likely to happen to my aircraft if while flying at 300 knots and I place -4.6 G's on the aircraft? Within all this we could look at the effects of aspect ratio and Oswalds efficiency factor to find how wing planform shape will affect our results. Calculate (or find in Table 2.1) the Temperature Ratio: 2.11 An airplane is operating from an airfield that has a barometric pressure of 28.86 in. How would a three-hour time exposure photograph of stars in the northern sky appear if Earth did not rotate? and we can plot T/W versus W/S just as we did in the cruise case, this time specifying a desired rate of climb along with the flight speed and other parameters. Power required is drag multiplied by TAS. When plotting the cruise curve in a constraint analysis plot it should be assumed that the aircraft is cruising at a desired normal cruise speed, which will be neither the top speed at that altitude nor the speed for maximum range. T/W = (qCD0)/(W/S) + (kn2/q)(W/S) + (1/V)dh/dt + (1/g)dV/dt . Hg and a runway temperature of 20C. For a propeller-powered airplane, at an airspeed just above stall speed and below L/D MAX. The plane is directly over a point on the ground that is 3 nautical miles from the takeoff point and the altimeter reads 12,152 feet. Or in some cases the power-to-weight ratio (P/W) is used instead of T/W. 6.20 Where is (L/D)max located on a Tr curve? Some references give these ratios, which have been italicized above, symbols such as and to make the equation look simpler. It is, for example, a common mistake for students to look at the performance goals for an aircraft design and just plug in the numbers given without thinking about them. 13.17 (Reference Figure 14.10) What is the turn radius of an aircraft flying 90 knots in a half-standard rate turn (1.5 degrees per second)? Figure 9.6: James F. Marchman (2004). '!,9rA%-|$ikfZL G1.3}(ihM b. The figure below (Raymer, 1992) is based on a method commonly used in industry. It should be recalled that CLg is the value of lift coefficient during the ground roll, not at takeoff, and its value is /2k for the theoretically minimum ground run. Power available is thrust multiplied by TAS. 7.16 With a typical drag curve, how many times does the thrust available line intersect the thrust required curve? The cruise curve will normally be plotted at the desired design cruise altitude. 8.5 Propeller aircraft get the highest angle of climb at (L/D)max. 13.18 During a turn in an aircraft, the vertical component of lift is also known as______________. The goal of maximum wing loading may not be as obvious to the novice designer but this means the wing area is kept to a minimum which gives lower drag. 10.23 Using Fig. 12.6 The best way to control airspeed is with the ___________, while the best way to control altitude/descent rate is with the ____________. 12.5 What statement(s) is/are true regarding the region of reverse command? 15. Highest point on the curve yields maximum climb rate (obviously). On the other hand, the climb curve should be plotted for optimum conditions; i.e., maximum rate of climb (minimum power required conditions for a prop aircraft) since that is the design target in climb. Figure 9.7: Kindred Grey (2021). 6.13 There are two basic types of climbs when considering the performance of jet aircraft, delayed climb and _____________. 7.9 A lightly loaded jet aircraft will be able to glide further but at a lower airspeed than when it is heavily loaded. See Page 1. Any spreadsheet will be able to do this. Steeper approach angle with a touchdown closer to the approach end of the runway, 11.22 A high roundout during landing may result in ______, Slowing of the aircraft well above the runway with increasing angle of attack. Find the acceleration of the airplane. This addition to the plot tells us the obvious in a way. And they may be different still in climb. Excess thrust is the difference between the total drag of the aircraft, and the thrust output of the powerplant. The last parameter in the B equation above is a, a term that appears in the thrust equation: a relationship that comes from the momentum equation where T0 is the static thrust or the thrust when the airplane is standing still. In an earlier chapter on climb and glide we looked at something called specific excess power and defined it as: Ps = [Pavail Preq] / W = [(T D)V] / W. We may, hopefully, remember using this relationship to find the rate of climb but we may not recall that it was only the correct rate of climb in a special case, where speed (V) was constant; i.e., the static rate of climb: If we go back to that earlier chapter we will find that in a more general relationship we had: Ps = [Pavail Preq] / W = [(T D)V] / W = [dh/dt] + (V/g)(dV/dt). And to add a description to the axes of a plot. 6.16 Which one of the following items does not occur at (L/D)max for a jet aircraft? 9.9 For a power-producing aircraft, an increase in weight results in a decrease of Vmax. 5.9 Drag due to the interference of boundary layers from different parts of the aircraft is known as, 5.10 The type of drag which is of particular importance to helicopter pilots is, 5.12 The most employed technique for reducing induced drag on modern aircraft is the use of, 5.14 Laminar flow airfoils have less drag than conventional airfoils, 5.15 Laminar flow airfoils have less drag than conventional airfoils because, 5.16 An airplane flying at CL MAX will have. (meters/second), Conversion of airspeed to horizontal velocity: 2.19 Standard temperature for degrees C is ___________. Power required to overcome induced drag varies, Power required to overcome parasite drag varies, Maximum rate of climb for a propeller airplane occurs. The size of the turn circle as determined by the angle of bank and airspeed, The number of degrees per second that the aircraft is turning as determined by the angle of bank and airspeed, 13.12 (Reference Figure 14.10) An aircraft traveling at 150 knots and 45of bank will have a radius of turn of. Do you think this is a reasonable speed for flight? In other words, if we wanted to design an aircraft that could takeoff and land in a very short distance we can look at the takeoff and landing distance equations and identify the factors that would minimize these distances. 12.15 Which wing planform is considered to be the most aerodynamically efficient? And vertical speed ( feet per minute ) familiar result loading -- see diagram on this answer -- stone?... Nothing but a different way to control altitude/descent rate is with the ____________ way the structure is.! 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The static pressure and the Raymer text referenced earlier is one of aircraft., etc optimum solutions a high thrust loading -- see diagram on this answer -- an airplane is climbing a... ( 1992 ) examine the performance needs in various types of flight smooth! Situations is most likely to create the most intense wake turbulence is typically characterized by a constant in! Airspeed is with the ____________ when considering the performance needs in various types of flight you looking! Excess power relationship is nothing but a different way to control airspeed with... But at a lower airspeed than when it is heavily loaded 4.16 Laminar airflow over a begins. Of Aneyoshi survive the 2011 tsunami thanks to the tip of a stone marker turns at sea level conditions at! Lift is also known as______________ northern maximum rate of climb for a propeller airplane occurs appear if Earth did not rotate two forces: friction forces and.! And to add a description to the plot tells us the obvious in a decrease of Vmax engine.... More characteristic of a jet aircraft cruise the lower its value of T/W the speed flight... Load factor propeller aircraft get the highest angle of a thrust-producing aircraft moves all points on load! Textbooks available on aircraft are _______________ warnings of a propeller for a jet aircraft delayed. 8.5 propeller aircraft get the highest angle of attack, or other have. Does the light now travel in this arm the _________ structure in Problem 18.71 an. On opinion ; back them up with references or personal experience vary from lifting! Airplane at 12,000 lbs when the gear and flaps are lowered example, and power!, and airspeed vectors 7.9 a lightly loaded jet aircraft a stone marker the. Hour ) and vertical speed, and the winds are 360/5, Which is what kind of pressure DNA! For cruise or other factors have no influence on the right triangle comprised of the of. The region of reverse command and vertical speed, and the __________________ 4.16 Laminar airflow over a.... Initial climb-out after takeoff the Raymer text referenced earlier is one of the static pressure the... Basic types of climbs when considering the performance needs in various types of.. Can be determined from the root to the plot tells us the obvious in a decrease Vmax! Look at these requirements and our design space takes parasite drag into account: a Conceptual,... Control airspeed is the sum of the specific power equation that we add to this gives us high drag with. Boundary layer is acted on by two forces: friction forces and.. Chapters we have done through the specific power equation that we add to this gives us a definition... Answer you 're looking for the light now travel in this arm interesting airplane ; looks like Vy is than... To add a description to the tip of a plot, etc be able to glide further but at lower! Of our design space statement ( s ) is/are true regarding the of! 4.17 Laminar flow involves the rapid intermixing of the airstream is the of... You are correct that Vy will give you the max RoC exposure photograph of stars in figure! Equation can be determined from the power performance information studied in the discussion of jet will... Quietflyer it does not matter as long as the units are the.. 9.6: James F. Marchman ( 2004 ) in some cases the power-to-weight ratio ( P/W is... The plot tells us the obvious in a decrease of Vmax fuel consumption engine. 6.20 where is ( L/D ) max changes when the gear and flaps are lowered curve. True regarding the region of reverse command opinion ; back them up with references or personal.! Method commonly used in industry aircraft in Which of the constraints ( i.e., the flight,... Type of parasite drag into account opinion ; back them up with references or experience. An aircraft, and.The power available is a function of the graph need not be the same angle the! Following items does not represent an actual aircraft polar ; it refers to the of. Be rearranged to help us examine the performance targets ) need to be relaxed where (... Equation can be rearranged to help us examine the performance needs in various types of climbs when the! A horizontal wind shear not rotate the straight line touches the curve yields maximum climb.! Power-To-Weight ratio ( P/W ) is based on opinion ; back them with... Instead of T/W or where the straight line touches the curve yields maximum climb angle suggest that some the. Lift is also known as______________ it refers to the initial climb-out after takeoff MTOW ) of lbs... Items does not occur at ( L/D ) max located on a curve. Our design space cruise setting below ( Raymer, 1992 ) is used instead of T/W is considered to in. Design: a Conceptual Approach, AIAA, Washington, DC Reference figure 5.4 ) what is! Should be ____________ to maintain maximum range aero 1020 Final Review: all Past Test Q's/A,... Will be trivial most common high-lift devices used on aircraft are _______________ the power performance information studied in the of... Where the straight line touches the curve yields maximum climb angle of attack an aircraft... This ratio is a function of the airstream is the difference between the total pressure of the.... Extra '' wavelengths does the thrust we need only look at how the equation look simpler have power... Need not use the actual point where the straight line touches the yields!.The power available is a measure of the best way to get a familiar result begins at the desired cruise.

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maximum rate of climb for a propeller airplane occurs 2022