11.10 The minimum glide angle also corresponds to ____________________. 8.5 Propeller aircraft get the highest angle of climb at (L/D)max. %PDF-1.3 12.20 When taking off in a microburst, a pilot should be aware of what change in performance when going from a tailwind to a headwind? Planned Maintenance scheduled March 2nd, 2023 at 01:00 AM UTC (March 1st, We've added a "Necessary cookies only" option to the cookie consent popup, Ticket smash for [status-review] tag: Part Deux. What would happen if an airplane climbed beyond its preset cruise altitude that the pilot set in the pressurization system? This ratio is a measure of aerodynamic efficiency as well as a measure of the way the structure is designed. The other parameter, W/S, or wing loading, is also generally low for sailplanes and high for fighters. If we want an airplane that only does one thing well we need only look at that one thing. It is called: AERO 1020 Final Review: All Past Test Q's/A's, Materials Science and Engineering: An Introduction, CT Basics 2.0 | Module 1: CT Fundamentals Test, MKT201 700 FULL CHAP-Key 700 Trung sa. Just as a car cannot get its best gas mileage when the car is moving at top speed, an airplane isnt going to get maximum range at its top cruise speed. The relationship above, since it does not depend on the thrust, will plot on our constraint analysis chart as a vertical line in much the same way the stall case did, but it will be just to the left of the stall line. 3. For example, if the hub-to-ground measurement is 45 inches, subtracting 9 inches will leave an effective radius of 36 inches. Along with power setting but that one is somewhat self explanatory. 9.15 If an aircraft with a clean configuration deploys gear and approach flaps, yet desires to maintain the same indicated speed as before the gear and flaps were deployed, which of the following has to be increased? . 10.22 Takeoff acceleration through the air mass is not reduced by a headwind. How would a three-hour time exposure photograph of stars in the northern sky appear if Earth did not rotate? **tHS-8_0hDRIX2^KK0+z# Y]Q2I TBz ,"JyTyXFv4nm.P t #&'++"T[(2;Ggg~y! 11.11 In most cases, an aircraft that has a high rate of descent on final approach should ____________. 9.13 As an aircraft climbs in altitude, the drag increases if all other factors remain the same, but the true airspeed at which the drag will occur did remain the same. 8.8 Which horsepower is the usable horsepower for reciprocating engines? Suppose that a 1.0-mm-thick layer of water is inserted into one arm of a Michelson interferometer. Don't let the length of this answer fool you, it is actually the fastest path to a solution, starting from what we're given to work with in the original question. 1.9 An aircraft is traveling west at an airspeed of 120 knots and is experiencing a crosswind of 20 knots from the north (90). A tailwind is encountered. This isnt really much different from designing any other product that is capable of more than one task. Best angle of climb (BAOC) airspeed for an airplane is the speed at which the maximum excess thrust is available. 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. It usually is restricted to either the takeoff setting or the cruise setting. Typically it takes a form such as that shown in Figure 13.7.The shortest time-to-climb occurs at the flight velocity where is a maximum. 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). So no re-plotting is needed, just get out your ruler and start drawing. 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? In other words, only when velocity (V) is constant is this relationship strictly equal to the rate of climb. Note that the line from the origin will have the steepest slope when it is tangent to the curve on the graph. 8.25 When leveling off at cruise altitude after a climb in an aircraft with a fixed-pitch propeller, as the forward speed of the aircraft increases the blade angle of attack __________. In the figure above this will be either where the takeoff and climb curves intersect or where the takeoff and landing curves intersect. But, in a jet, you'll often fly close to your best range speed. *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! 10.20 One of the dangers of overrotation is ________________. 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. 3.13 thru 3.17 Reference Figure 2. The pilot selects the desired RPM with a leaver, and a control governor automatically changes the blade pitch to maintain a constant RPM. 1.17 An airplane weighs 8,000 lbs and is flying at 6,000 ft altitude and an airspeed of 200 fps. 1.19 An aircraft weighs 12,000 lbs. 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)? 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. 6.13 There are two basic types of climbs when considering the performance of jet aircraft, delayed climb and _____________. 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. The second is that the takeoff parameter (TOP) defined for propeller aircraft is based on power requirements (specifically, horsepower requirements) rather than thrust. 2.14 The energy of an airstream is in two forms: It has potential energy, which is what kind of pressure? Maximum excess thrust occurs: For a jet-powered airplane, at approximately the maximum lift/drag ratio (L/D MAX). 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. 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. 12.3 ______________ wings will stall at the wing tips first and then progress toward the rest of the wing. 1.18 An aircraft's turbojet engine produces 10,000 lbs of thrust at 200 knots true airspeed. And this can be written [W/S] = Vstall2CLmax, On the plot above this would be a vertical line, looking something like this. 6.15 Which one of the following items does not occur at (L/D)max for a jet aircraft? This can be determined from the power performance information studied in the last chapter. In cruise where lift = weight and thrust = drag, T/W = 1 / [L/D], meaning that the high value of L/D that is needed for a large range goes hand in hand with a low thrust-to-weight ratio. 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. 7.17 Changing the weight of an aircraft changes the ______________ much more than the ___________. 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). The above relationship means that, for a given weight of the airplane, the rate of climb depends on the difference between the power available and the power required, or the excess power. T/W = (qCD0)/(W/S) + (kn2/q)(W/S) + (1/V)dh/dt + (1/g)dV/dt. 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. 13.20 An aircraft in a level, coordinated turn with a bank angle of 60 is maintaining _____ G's. In the proceeding chapters we have looked at many aspects of basic aircraft performance. What is the mass of the airplane? For propeller aircraft - Maximum angle of climb occurs at the Vfor which maximum excess thrust occurs Maximum climb angle (which is used to clear obstacles on takeoff) occurs at a velocity < V min TR Rate of Climb R/C For a given altitude - For any type of airplane, excess power determines R/C - Induced drag changes P R P C P - = W R . 1.15 An airplane is climbing at a constant airspeed in no-wind conditions. 13.7 (Reference Figure 5.4) What will happen to an aircraft that is flown to the right side of the straight vertical line on the right side of the flight envelope? 5.24 For a given aircraft wing, if the wing span remains the same but the wing area increases, the aspect ratio will ____________. 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. In understanding what this really tells us we perhaps need to step back and look at the same situation another way. 10.23 Using Fig. stream 7.24 Increased weight has what effect on rate of climb? 7.18 Increasing the weight of a thrust-producing aircraft moves all points on the thrust-required curve ____________. Once the value of TOP has been found the relationship above is plotted to give a straight line from the origin of the constraint analysis graph. b. The first step in the process is usually to look for what are called comparator aircraft, existing or past aircraft that can meet most or all of our design objectives. 10.13 A higher density altitude on takeoff does not affect which one of the following aircraft below its critical altitude? The maximum angle of climb occurs where there is the greatest difference between the thrust available and the thrust required. Figure 6.1: Finding Velocity for Maximum Range | 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. 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