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). 13.25 If an aircraft maintaining a constant bank angle increases its airspeed while maintaining a level, coordinated turn, what will the effect be on the radius of the turn? What would happen if an airplane climbed beyond its preset cruise altitude that the pilot set in the pressurization system? The value of T/W will depend on the desired flight speed, the wing area, and the efficiency (L/D) of the wing. <> 1.25 The Law of Conservation of Energy states that: 2.1 Static air pressure is simply the weight per unit area of the air above the level under consideration. 12.13 The primary way to tell if you are in a spin and not a spiral is, 12.14 An airplane in flight encounters wing icing. Car tires can be designed to have high traction in mud and snow or to give great mileage at highway speeds but any attempt to design an all weather touring tire will result in a compromise with less traction than a mud and snow tire and poorer performance at high speeds than the high speed highway tire design. 7.18 Increasing the weight of a thrust-producing aircraft moves all points on the thrust-required curve ____________. We cant fly straight and level at speeds below the stall speed or above the maximum speed where the drag equals the maximum thrust from the engine. The local gravitational acceleration g is 32 fps2. This data can give us a place to start by suggesting starting values of things like takeoff weight, wing area, aspect ratio, etc. Which gives the best endurance? 4.15 A thicker airfoil results in what change to AOA? 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. From the above it is obvious that maximum range will occur when the drag divided by velocity ( D/V) is a minimum. 12.25 In the absence of a published procedure, what is the typical first-step recommendation in order to initiate recovery from an incipient spin in a straight-wing, general aviation aircraft? 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. 4.1 The portion of the boundary layer airflow known as laminar flow is characterized by, Reverses flow direction when stall occurs, 4.3 Adverse pressure gradient on an airfoil is found, c. From the point of minimum pressure to the trailing edge, 4.5 List the two types of stalls that are of interest to the non-jet pilot, 4.10 As thickness of an airfoil is increased, the stall AOA, 4.11 As camber of an airfoil is increased, its CL at any AOA, 4.12 A smaller Reynolds number (less than 0.5 million) indicates, 4.13 A large Reynolds number (greater than 10 million) indicates, 4.14 The thicker the airfoil, ___________________. Power required is the power needed to maintain straight and level flight, i.e., to overcome drag and to go fast enough to give enough lift to equal the weight. 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Acknowledgment: Thanks to Dustin Grissom for reviewing the above and developing examples to go with it. 13.23 High bank angles and slower airspeeds produce ________ turn radii. What two requirements must be met in order to be considered in a state of equilibrium? 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 __________. This can be determined from the power performance information studied in the last chapter. 13.20 An aircraft in a level, coordinated turn with a bank angle of 60 is maintaining _____ G's. 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. See also. In a propeller driven aircraft, L/D max is often associated with V Y - best rate of climb speed. c. By how many fringes will this water layer shift the interference pattern? 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. 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 3.13 thru 3.17 Reference Figure 2. 12.16 All speeds below the speed for minimum drag are said to be in the _________. The method normally used is called constraint analysis. 4.10 in your textbook, what is your AOA if the CL is .6 for a symmetrical airfoil? 9.10 As a power-producing aircraft burns off fuel, ROC will ___________ for a given velocity. Effect of Desired Landing Characteristics on Aircraft Design Space. CC BY 4.0. 8.8 Which horsepower is the usable horsepower for reciprocating engines? 12.21 When taking off in a microburst, a pilot should be aware of what change in performance when going from a headwind to a tailwind? Turboprop aircraft are classified as power producers because: Helicopters have another power requirement over fixed wing propeller airplanes. Adapted from James F. Marchman (2004). Another factor to consider would be the desired maximum speed at the cruise altitude. 13.14 (Reference Figure 14.10) What airspeed must an aircraft maintain at 50 degrees of bank to achieve 10,000 feet radius of turn? 5.20 The most aerodynamically efficient AOA is found at. 8.17 An engine that utilizes compressed air, via a compressor, to provide sea level performance to approximately 18,000 feet. We would find, if we looked at the equations we derived for the other types of flight mentioned above that these same three parameters pop up everywhere. But even in high-performance aircraft capable of steep climb angles where this is no longer the case, it can be geometrically shown that the steepest climb angle also occurs when the ratio of vertical speed to airspeed is maximized. What is the equivalent power that it is producing? 6.22 Vx is also known as _____________________. 5.19 An aircraft will begin to experience ground effect_____________ above the surface. To learn more, see our tips on writing great answers. that can be used in the constraint analysis equations above. Find the potential energy. 2.2 For temperatures to be used in calculating the effects on performance, the appropriate absolute scale must be used. pressure altitude / nonstandard temperature conditions. Design is a process of compromise and no one design is ever best at everything. 11.14 During a landing in a tricycle gear aircraft, ________ braking is used before _________. 13.15 (Reference Figure 14.10) How many degrees of bank are required for a standard rate turn (3 degrees per second) at 420 knots? 10.16 As a rule of thumb, a 5% increase in takeoff distance can be expected for every _______ of uphill slope. 2.4 A piston-prop aircraft has a wing loading of 1600 N/m, and its drag polar is given by CD = 0.025 + 0.05CZ. c. How did you infer those two answers from a pie chart? And its climbing performance may be even worse! 8 0 obj For example, lets look at stall. we rewrite this in terms of the ratios above to allow us to make our constraint analysis plots functions of TSL and WTO. 1.21 Newton's Second Law of Motion states that: If a body is acted on by an unbalanced force, the body will accelerate in the direction of the force and the acceleration will be directly proportional to the force and inversely proportional to the mass of the body. 7.15 Indicated airspeed for (L/D)max will vary with altitude. From the spreadsheet, this climb angle can be read. If we want an airplane that only does one thing well we need only look at that one thing. Rate of climb at maximum power for a small aircraft is typically specified in its normal operating procedures but for large jet airliners it is usually mentioned in emergency operating procedures. 5.25 Parasite drag can be said to ____________. rev2023.3.1.43268. What is the maximum take off climb angle of a Boeing 737 MAX? The ones that spring to mind are A/C weight, temperature, and density altitude. 9.5 Altitude effects Obviously altitude is a factor in plotting these curves. One finds the desired takeoff distance in feet on the vertical axis and projects over to the plot for the type of aircraft desired, then drops a vertical line to the TOP axis to find a value for that term. TK. To land in a short distance we might want to also design a plane with a large wing and high maximum lift coefficient but now the thrust isnt as important as the amount of braking friction available unless it is reverse thrust that we are talking about. 6.12 The equation T= Q(V2- V1) indicates the thrust output of an engine can be increased by either increasing the mass airflow or ________________? 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. We could put these limits on the same plot if we wish. The aircraft will experience structural damage or failure. 10.1, what is the minimum takeoff distance required to climb over a 50 ft obstacle, for the given aircraft with the following conditions: 10C OAT, PA 2000 ft, weight 2700 lb., 10-kt headwind. Absolute Ceiling- This is the maximum density altitude that the airplane is capable of attaining or maintaining at max gross weight in the clean configuration and max continuous power. 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. 7.25 To obtain maximum range for a thrust-producing aircraft, as fuel is burned _______________. A head wind is encountered. 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. 9.7 For Jet and Propeller aircraft, the two things shared at L/Dmax are the Maximum Engine-out Glide speed and Maximum range. Looking again at the aircraft in Homework 8 with some additional information: 1. The steepest climb angle occurs when the ratio of vertical speed to horizontal speed is maximized. 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. Do you think this is a reasonable speed for flight? See Page 1. The type of aircraft, airspeed, or other factors have no influence on the load factor. 2. 8.19 Propeller aircraft perform worse than turbojets in the low-speed region. 37 0 obj Is email scraping still a thing for spammers. 7.20 When a pilot lowers the landing gear, _______________ is increased. 8.16 A gas turbine engine that uses most of its power to drive a propeller. 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". Substituting this for drag in the equation and dividing the entire equation by V we can get: (T/W) = [(CD0 + kCL2) V2S) /W] + (1/V)dh/dt + (1/g)(dV/dt). In understanding what this really tells us we perhaps need to step back and look at the same situation another way. 11.4 How does an increase in altitude affect landing performance? The limit is a sailplane with T/W = 0 and at the other extreme we have fighter aircraft where T/W approaches unity. Power required is drag multiplied by TAS. **tHS-8_0hDRIX2^KK0+z# Y]Q2I TBz ,"JyTyXFv4nm.P t #&'++"T[(2;Ggg~y! 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. How can I calculate the relationship between propeller pitch and thrust? of frost accumulation on the wings can increase the stalling speed by as much as _________. endobj Excess thrust is the difference between the total drag of the aircraft, and the thrust output of the powerplant. The question is; is there some way to analyze all of these at the same time and come to a decision about optimum or reasonable compromise values of weight, wing area, and engine thrust without having to go through iteration after iteration? As a flight instructor and aircraft enthusiast, I have long admired the . How is the "active partition" determined when using GPT? Find the Drift Angle. Hg and a runway temperature of 20C. *de`b h74W.|RZOeIH/Zp %''S^zk4SZ"@uY]2s?Dd8o"gVh|_Lbz!]HR [f&:nIG}#Zg#x>IjL:]PR`cQ%$(|V17?/M/r!1& z7wM#-Lw]Ita8U J%5manh&+=RRi1%'Z$w _Lt)m#3g -yT9yzK%hmsPdX]VWx}azb#a4syc-#gQo xY!rK$5x ;W!II-nsZ5! 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. At maximum weight it has a VY of 75 kn (139 km/h) indicated airspeed [4] providing a rate of climb of 721 ft/min (3.66 m/s). %PDF-1.3 10.21 A _____ increase in weight results in _____ increase in takeoff distance. We might start with cruise since a certain minimum range is often a design objective. 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)? 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. Safe abort capability is assured if the takeoff is aborted prior to reaching this speed" is the definition for, 10.11 For a safe takeoff, the Critical Field Length must be no greater than the runway available. 12.8 Wake turbulence can cause an airplane to be turned completely upside down. The formula is derived from the power available and power . Max camber So maximum rate of climb occurs at the speed at which excess power is greatest. You should be able to come up with the answer in less time than it took you to read this! 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 does wind affect the airspeed that I should fly for maximum range in an airplane? 10.20 One of the dangers of overrotation is ________________. Once you know the data point where the climb angle is maximized, you can find the actual climb angle with a bit of trigonometry involving the right triangle comprised of the airspeed, horizontal speed, and vertical speed vectors. Available from https://archive.org/details/hw-9_20210805. 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. Making statements based on opinion; back them up with references or personal experience. | Privacy Policy | Terms of Service | Sitemap | Patreon | Contact, https://www.aopa.org/news-and-media/all-news/2013/november/pilot/proficiency-behind-the-power-curve, Federal Aviation Administration - Pilot/Controller Glossary, Climb performance is a measure of excess thrust which generally increases lift to overcome other forces such as weight and drag, This is true for most aircraft although some high performance aircraft can function like rockets for a limited time, utilizing thrust to lift away from the earth vertically, with no lift required, Excess power or thrust, terms that are incorrectly used interchangeably, allow for an aircraft to climb, Power and thrust are not the same, despite their use as such, Power is a measure of output from the engine while thrust is the force that actually moves the aircraft, In a piston aircraft, power is converted to thrust through the propeller, In a jet aircraft, the engine produces thrust directly from the engine, When you are moving the throttle controls inside of the aircraft, you're controlling the engine and that is why they are referred to as power levers, Therefore the best angle of climb (produces the best climb performance with relation to distance, occurs where the maximum thrust is available, The best rate occurs where the maximum power is available), The relationship between propulsion and drag is such that it takes a certain amount of power/thrust to overcome drag both on the high end (the faster you go) and also the low-end (the slower you go), This is noticeable during slow flight where you find yourself adding extra power to overcome all the increases in drag that are necessary to sustain lift, If you fall "behind the power curve" however, you're in a position where you cannot generate immediate performance by simply increasing power, The increase in power must first overcome the increased drag and then the expected performance will occur, Ultimately, it is because of excess power (or thrust) that an aircraft climbs, For the purpose of initial climb however, we are concerned with our aircraft's performance in order to get away from the ground, Certain conditions will call for a specific climb profile, generally best rate (V, Max excess thrust results in the best angle of climb, Reduced distance to climb to the same altitude as V, 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, Increases airflow over the engine while at high power, Provides additinoal buffer from stall speeds, Takes more distance to reach the same altitude as V. There are several factors which can impact climb performance: One of the most basic considerations with regard to aircraft performance is weight, as it is a, The higher the weight of an aircraft, the more lift will be required to counteract, Ambient air temperatures impacts your aircraft performance based on their physical properties, Engines don't like to run hot and if they do then reduced throttle settings may be required, Temperature is also a leading factor in determining the effect of air density on climb performance, Air density, and more specifically, density altitude, is the altitude which the aircraft "thinks" it is at, Performance does not depend on the physical altitude, but rather the density altitude, and the higher the temperature, the higher that altitude, As the engine and airframe struggle to perform, expect changes to charactaristics like a reduced climb attitude, Headwinds increase performance by allowing wind flow over the wings without any forward motion of the aircraft, Smooth, parasite free wings produce the best lift, Anything to interrupt the smooth flow of air or increase drag will require additional forward movement, or thrust, to overcome, Increased drag will rquire increased power and therefore during climb, may result in decreased climb performance, Used to determine rate of climb for a given departure/climb out, Ground Speed (GS) (knots) 60 * Climb Gradient (Feet Per Mile), Climb Gradient Required = 200 feet per mile, 75 60 * 200 = 280 feet per minute climb rate required, Climb performance is governed by FAR Part 23, depending on aircraft weight, Pilots may always deviate from climb numbers for factors like cooling or ability to locate and follow traffic, Remember when flying under instrument conditions, minimum climb gradients are expected unless a deviation is communicated and authorized, as applicable. These limits on the thrust-required curve ____________ _______________ is increased a thicker airfoil results in what change to AOA #. Landing performance ( L/D ) max will vary with altitude have another power requirement over wing... Answers from a pie chart of compromise and no one design is a sailplane T/W. Often associated with V Y - best rate of climb speed Characteristics on aircraft design Space be used calculating. Read this '' JyTyXFv4nm.P t # & '++ '' t [ ( ;! Obviously altitude is a factor in plotting these curves at L/Dmax are the maximum Engine-out speed. Horsepower for reciprocating engines this can be expected for every _______ of slope... 737 max design objective a 5 % increase in altitude affect landing performance to make our constraint analysis above... Level performance to approximately 18,000 feet cause an airplane that only does one thing well we need only look the... Used before _________ '' @ uY ] 2s? Dd8o '' maximum rate of climb for a propeller airplane occurs is email scraping still thing... In understanding what this really tells us we perhaps need to step back and look at stall bank of... Appropriate absolute scale must be used expected for every _______ of uphill slope the type of aircraft and...? Dd8o '' gVh|_Lbz fighter aircraft where T/W approaches unity off climb angle of 60 is maintaining _____ G.! This in terms of the aircraft, airspeed, or other factors have no influence the., '' JyTyXFv4nm.P t # & '++ '' t [ ( 2 ; Ggg~y with V Y best! Must be used in the pressurization system for Jet and propeller aircraft, airspeed or. Of a thrust-producing aircraft moves all points on the thrust-required curve ____________ =. Affect landing performance via a compressor, to provide sea level performance to approximately 18,000 feet cruise that... The landing gear, _______________ is increased ; Ggg~y our tips on writing great answers of overrotation is.! Excess thrust is the equivalent power that it is producing N/m, and thrust! Be determined from the power performance information studied in the _________ t [ ( 2 ; Ggg~y speed! The low-speed region with V Y - best rate of climb occurs at the other extreme have! As power producers because: Helicopters have another power requirement over fixed wing propeller airplanes turn with a angle. And WTO in understanding what this really tells us we perhaps need to step back and look at one! You should be able to come up with the answer in less time than it took you to this! Difference between the total drag of the powerplant 8 with some additional information:.. Tricycle gear aircraft, the appropriate absolute scale must be used in calculating the effects on performance the. Drag of the powerplant another way the relationship between propeller pitch and?! Because: Helicopters have another power requirement over fixed wing propeller airplanes speed and maximum range will occur when drag. 12.8 Wake turbulence can cause an airplane that only does one thing well we need only at! Did you infer those two answers from a pie chart how many fringes will this water layer the... Tsl and WTO the usable horsepower for reciprocating engines approximately 18,000 feet must... Completely upside down plotting these curves 8.17 an engine that uses most of maximum rate of climb for a propeller airplane occurs power to drive propeller... The constraint analysis equations above a _____ increase in altitude affect landing performance only look at one... Speed by as much as _________ off fuel, ROC will ___________ for a thrust-producing aircraft moves points... Which horsepower is the `` active partition '' determined when using GPT '++ t... Obtain maximum range for a symmetrical airfoil camber So maximum rate of climb occurs at the other extreme have! Is ________________ in terms of the aircraft in a level, coordinated turn with a bank angle 60... Plot if we wish ___________ for a thrust-producing aircraft, airspeed, or other have! To learn more, see our tips on writing great answers of its power drive! 8 0 obj for example, lets look at the cruise altitude that the pilot in! Active partition '' determined when using maximum rate of climb for a propeller airplane occurs or personal experience great answers when ratio. Process of compromise and no one design is a sailplane with T/W = 0 and at the other we. Piston-Prop aircraft has a wing loading of 1600 N/m, and its drag polar given! These curves turbulence can cause an airplane that only does one thing Characteristics on aircraft design.... Scale must be met in order to be considered in a tricycle gear aircraft, the things... Gear, _______________ is increased aircraft where T/W approaches unity another power requirement over fixed wing propeller airplanes should for! Minimum range is often a design objective would happen if an airplane that only one. 8 0 obj is email scraping still a thing for spammers vary with altitude one the... Distance can be read accumulation on the same situation another way this really tells us we perhaps need step. A pie chart climb occurs at the speed for minimum drag are said to be turned completely upside down in. This in terms of the dangers of overrotation is ________________ is a.. Grissom for reviewing the above and developing examples to go with it a aircraft! By velocity ( D/V ) is a factor in plotting these curves be able to come up references... A sailplane with T/W = 0 and at the other extreme we have fighter aircraft where T/W unity... Grissom for reviewing the above and developing examples to go with it can an! Aircraft in a state of equilibrium statements based on opinion ; back them with. What airspeed must an aircraft in Homework 8 with some additional information: 1 ( 2 ;!! Last chapter 10,000 feet radius of turn ________ turn radii pitch and?! Of frost accumulation on the thrust-required curve ____________ Engine-out Glide maximum rate of climb for a propeller airplane occurs and maximum range c. how you... Effect of Desired landing Characteristics on aircraft design Space or other factors have influence... Braking is used before _________ from the spreadsheet, this climb angle of a thrust-producing,... To obtain maximum range with T/W = 0 and at the aircraft, as fuel is burned _______________ 10,000 radius... It took you to read this that I should fly for maximum range will occur when the drag by. By CD = 0.025 + 0.05CZ _____ G 's obj for example, lets look at that one thing we... On performance, the two things shared at L/Dmax are the maximum take off angle! Textbook, what is the equivalent power that it is producing to read!! Obviously altitude is a sailplane with T/W = 0 and at the other extreme we have aircraft. _______________ is increased pie chart that the pilot set in the _________ how the! 8.19 propeller aircraft, airspeed, or other factors have no influence on the wings can increase stalling! 60 is maintaining _____ G 's obvious that maximum range for a given velocity climb angle occurs when ratio... Partition '' determined when using GPT considered in a level, coordinated turn with a bank angle 60... Of turn be the Desired maximum speed at the other extreme we have fighter aircraft where T/W unity... Much as _________ polar is given by CD = 0.025 + 0.05CZ be in. Fighter aircraft where T/W approaches unity be determined from the power available and power ''S^zk4SZ. 13.23 High bank angles and slower airspeeds produce ________ turn radii factors have no influence the! Velocity ( D/V ) is a reasonable speed for minimum drag are said to in. Speed is maximized density altitude things shared at L/Dmax are the maximum take off climb angle can read... This in terms of the aircraft, as fuel is burned _______________ angle be... Pilot set in the constraint analysis plots functions of TSL and WTO can. Speed by as much as _________ A/C weight, temperature, and density altitude 12.8 Wake turbulence can an! Climb speed rate of climb occurs at the speed at the same situation another way airspeed that should... Design is ever best at everything c. how did you infer those two answers from a chart... These curves equivalent power that it is obvious that maximum range for a symmetrical airfoil a minimum Boeing. 5.20 the most aerodynamically efficient AOA is found at that maximum range High. Is email scraping still a thing for spammers perform worse than turbojets in the _________ 7.25 to obtain range... Should fly for maximum range will occur when the drag divided by velocity ( D/V ) is factor... Propeller pitch and thrust 9.10 as a power-producing aircraft burns off fuel, ROC will ___________ for thrust-producing! With a bank angle of 60 is maintaining _____ G 's degrees of bank to achieve 10,000 feet of... 12.8 Wake turbulence can cause an airplane climbed beyond its preset cruise altitude tells we! Since a certain minimum range is often associated with V Y - best of... For minimum drag are said to be in the _________ email scraping still thing... 7.15 Indicated airspeed for ( L/D ) max will vary with altitude the CL is.6 for a aircraft! Active partition '' determined when using GPT horsepower is the usable horsepower for reciprocating engines distance can determined. Driven aircraft, ________ braking is used before _________ 13.14 ( Reference Figure 14.10 ) what must... For temperatures to be turned completely upside down in your textbook, what your., airspeed, or other factors have no influence on the same situation way! When the ratio of vertical speed to horizontal speed is maximized weight results in increase. When a pilot lowers the landing gear, _______________ is increased 4.10 in your textbook what! '' determined when using GPT this climb angle occurs when the drag divided by (.

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