11.20 The power-off stalling speed in a specified configuration is called: 11.21 During a stabilized approach, if an aircraft maintains constant airspeed and constant power but adds flaps, the pilot can expect a _________. 12.5 What statement(s) is/are true regarding the region of reverse command? 8.14 A propeller where the pitch setting can only be adjusted on the ground and requires that the engine be stopped is known as: 8.15 An engine where the fuel-air mixture is forced into the cylinders by natural atmospheric pressure upon opening of the inlet valves. Note that just as the drag equation is a function of both V and 1/V, this is a function of both W/S and 1/(W/S). a. 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. (As a point of trivia, it looks like if the horizontal units on your graph are knots and the vertical units are feet/min, then the angle computed with the arcsine is about 4% larger, or about 0.6 degrees larger, than the angle computed with the arctangent.). How to properly visualize the change of variance of a bivariate Gaussian distribution cut sliced along a fixed variable? Note that the thrust ratio above is normally just the ratio of density since it is normally assumed that. 7.23 Increased weight has what effect on angle of climb? 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). This ratio is a measure of aerodynamic efficiency as well as a measure of the way the structure is designed. 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. Propeller aircraft are more efficient than jet aircraft because: They process more air and don't accelerate it as much. Accessibility StatementFor more information contact us atinfo@libretexts.orgor check out our status page at https://status.libretexts.org. In a propeller driven aircraft, L/D max is often associated with V Y - best rate of climb speed. The maximum angle of climb occurs where there is the greatest difference between the thrust available and the thrust required. What can be gained by accepting a lower cruise speed or a longer takeoff distance. 1.12 Solve for left and right moment arm and fulcrum force against the seesaw (respectively) (See Figure 1_Test 1): 1.13 An airplane weighs 8,000 lb. We would also need to look at these requirements and our design objectives. Hg and a runway temperature of 20C. 17-57). 1.11 Equilibrium is defined as "a state of balance or equality between opposing forces." Still looking for something? 4.20 An increase in CL(max)and a decrease in stall AOA will be noted when ___________. 9 0 obj 5.22 The value of (L/D)max and the angle of attack for which it occurs does not vary with altitude but does vary with weight. We need to keep in mind that there are limits to that cruise speed. 6.11 The equation T= Q(V2- V1) expresses Newton's ______ law. 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. 10.19 _____ is the intersection of the acceleration and deceleration profiles. 12.3 ______________ wings will stall at the wing tips first and then progress toward the rest of the wing. What is the equivalent power that it is producing? 11.15 Foot brakes should be utilized before the nosewheel touches the ground during landing. AERO 1020 Final Review: All Past Test Q's/A's, Genetics Lecture 13 - DNA Chem and Replication. 1. For example you can choose a point where the straight line crosses one of the airspeed or vertical speed indices, or where it crosses an intersection of both airspeed and vertical speed indices. The formula is ROC in FPM = ExcessHP*33,000*Propeller efficiency divided by All up Mass in LBS. How does a fixed-pitch propeller changes the blade's angle of attack? ,8Ot_8KOgiy*I&lw4d^ "(y
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I4xiZM A8xrABZ|*NTwD! Or, if you've re-plotted your graph with the same scale on each axis, and you aren't worried about the difference between airspeed and horizontal speed, you can forgo the trig calculation and just use a protractor to measure the angle between the tangent line and the x axis of your graph of vertical speed versus airspeed. It would not, however tell us if this would result in a good ability to climb or the ability to takeoff and land in a reasonable distance. The other parameter, W/S, or wing loading, is also generally low for sailplanes and high for fighters. 9.11 As a power-producing aircraft burns off fuel, airspeed should be ____________ to maintain maximum range. How many "extra" wavelengths does the light now travel in this arm? We conclude this section with a dramatic photograph of an F-16 in a vertical, accelerated climb, Figure 13.8. Effect of R & e Variation on max Range Cessna 182. CC BY 4.0. we rewrite this in terms of the ratios above to allow us to make our constraint analysis plots functions of TSL and WTO. 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. Max camber Has the term "coup" been used for changes in the legal system made by the parliament? . 13.18 During a turn in an aircraft, the vertical component of lift is also known as______________. Interesting airplane; looks like Vy is more than double Vx! and B = (g/W) [ S(CD CLg) + a] . In the figure above this will be either where the takeoff and climb curves intersect or where the takeoff and landing curves intersect. Figure 9.4: Kindred Grey (2021). 0.6 How will an uphill slope affect takeoff performance? A car can be designed to go really fast or to get really good gas mileage, but probably not both. '!,9rA%-|$ikfZL G1.3}(ihM In understanding what this really tells us we perhaps need to step back and look at the same situation another way. Copyright 2023 CFI Notebook, All rights reserved. As fuel is burned the pilot must. 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? One way to approach this would be to go back to the equations in earlier chapters and iterate among them, trying to find wing areas, weights, and engine sizes that would accomplish our design objectives. Power required to overcome induce drag varies: a. inversely with V b. inversely with V2 c. inversely with V3 d. directly with V. 14. 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. 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? The type of aircraft, airspeed, or other factors have no influence on the load factor. 1.16 An airplane weighs 8,000 lbs and is flying at 6,000 ft altitude and an airspeed of 200 fps. 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. 2.22 _____________________ results when the CAS has been corrected for compressibility effects. 4.16 Laminar airflow over a smooth airfoil like a wing begins at the _____________. 1.17 An airplane weighs 8,000 lbs and is flying at 6,000 ft altitude and an airspeed of 200 fps. 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. 6.23 Vy is also known as __________________. We need to note that to make the plot above we had to choose a cruise speed. 11.16 ____________ is caused by the buildup of the hydrodynamic pressure at the tire-pavement contact area. Figure 9.5: James F. Marchman (2004). Or in some cases the power-to-weight ratio (P/W) is used instead of T/W. For rate of climb for a propeller aircraf (this is the power available minus the power required, divided by aircraf weight): V v = P p W DV W = P p W V 3 C D 0 2 . 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. We know an expression for the rate of climb for a propeller aircraf V v = P p W DV W We assume the climb angle is small enough that lif approximately equals weight. 5. max thickness. To subscribe to this RSS feed, copy and paste this URL into your RSS reader. It can be noted that in the A and B terms respectively we have the thrust-to-weight ratio and the inverse of the wing loading (W/S); hence, for a given set of takeoff parameters and a desired ground run distance (STO) a plot can be made of T/W versus W/S. 12.8 Wake turbulence can cause an airplane to be turned completely upside down. Figure 9.7: Effect of R & e Variation on max Range Cessna 182. Cruising at V Y would be a slow way to fly. 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. Figure 9.7: Kindred Grey (2021). Power available is thrust multiplied by TAS. 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. It usually is restricted to either the takeoff setting or the cruise setting. Since your graph already shows the origin (0,0), you are almost done already! Power required is drag multiplied by TAS. 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. 9.82 1.10 An aircraft is in a steady climb, at an airspeed of 100 knots, and the flight path makes a 10 angle with the horizontal. Calculate (or find in Table 2.1) the approximate Pressure Altitude: 2.10 An airplane is operating from an airfield that has a barometric pressure of 28.86 in. What other design objectives can be added to the constraint analysis plot to further define our design space? Excess power is power available minus power required. 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. 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 __________. 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. 8.13 A propeller where the blade pitch setting is either hydraulically or electrically controlled. Learn more about Stack Overflow the company, and our products. 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. In essence this is a pretty powerful relationship and it can be used to analyze many flight situations and to determine an airplanes performance capabilities. In fact, the equations used to find the maximum range for either a jet or a prop aircraft assume flight at very low speeds, speeds that one would never really use in cruise unless desperate to extend range in some emergency situation. 4.23 Stall is airflow separation of the boundary layer from the lifting surface. 12.16 All speeds below the speed for minimum drag are said to be in the _________. The number of distinct words in a sentence. 7.11 (Reference Figure 7.2) Using Figure 7.2, find the velocity for best range for the airplane at 12,000 lbs. <> Acknowledgment: Thanks to Dustin Grissom for reviewing the above and developing examples to go with it. Cosine of Climb Angle x Airspeed = Horizontal Velocity. How can I get the velocity-power curve for a particular aircraft? 7.21 Lowering the landing gear and flaps has what effect on the drag curve of a thrust-producing aircraft? Would the reflected sun's radiation melt ice in LEO? Hg and a runway temperature of 20C. Best angle of climb (BAOC) airspeed for an airplane is the speed at which the maximum excess thrust is available. The mass flow depends on, 6.5 Specific fuel consumption of a turbine engine at 35,000 feet altitude compared to that at sea level is, 6.6 Fuel flow for a jet at 100% rpm at altitude compared to that at sea level is, 6.7 A pilot is flying a jet aircraft at the speed for best range under no wind conditions. 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. In the proceeding chapters we have looked at many aspects of basic aircraft performance. Maximum excess thrust occurs: For a jet-powered airplane, at approximately the maximum lift/drag ratio (L/D MAX). 3.2 An aircraft in a coordinated, level banked turn. One that is fairly easy to deal with is turning. And to add a description to the axes of a plot. Often a set of design objectives will include a minimum turn radius or minimum turn rate. Under what conditions can the maximum angle of climb be achieved for jet and propeller aircraft? This addition to the plot tells us the obvious in a way. Since you've already shown us a perfectly good graph of vertical speed versus airspeed, you might as well use it via the method described here. 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. 2. 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. 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. 11.3 How does a weight increase affect landing performance? 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. For a propeller-powered airplane, at an airspeed just above stall speed and below L/D MAX. 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)? 3.21 The point on the chord line where the aerodynamic force acts is the _____________. 8.20 As altitude increases, power available from a turboprop engine _____________. 6.22 Vx is also known as _____________________. Does an airfoil drag coefficient takes parasite drag into account? 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. Of course, it helps to do this in metric units. For a jet aircraft, this speed is very close to the speed at which the total minimum drag occurs. 8.17 An engine that utilizes compressed air, via a compressor, to provide sea level performance to approximately 18,000 feet. 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. Sometimes this is called a "service ceiling" for jet powered aircraft. Some references give these ratios, which have been italicized above, symbols such as and to make the equation look simpler. 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. Raymer, Daniel P. (1992). Doing this will add another curve to our plot and it might look like the figure below. The cruise ceiling is the altitude at which the maximum climb rate is 300 ft/min Definition - Combat Ceiling The combat ceiling is the altitude at which the maximum rate of climb is 500 ft/sec or 2.5 m/s. 1.18 An aircraft's turbojet engine produces 10,000 lbs of thrust at 200 knots true airspeed. It also gives a better ride to the airplane passengers. 12.10 If an airport is conducting simultaneous landing operations on parallel runways (e.g. 12.15 Which wing planform is considered to be the most aerodynamically efficient? 9.14 As the altitude for a given aircraft increases, the VX will ___________ and the VY will ___________. The cruise based calculations mentioned above would give us valuable design information for our airplane based on a desired cruise speed and altitude for a design weight and would tell us the wing area and thrust needed for that cruise condition and the thrust needed to cruise at a desired maximum speed. 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, ___________________. How is the "active partition" determined when using GPT? 8.19 Propeller aircraft perform worse than turbojets in the low-speed region. 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 __________. Wing loading for sailplanes is usually in the range of 5-8 pounds per square foot, around 17 lb/ft2 for general aviation planes, and over 100 lb/ft2 for fighters. But unless the data is already loaded up into a spreadsheet ready for re-plotting to a new scale, there's a much faster way to solve the problem. 10.24 When taking off in a multi-engine aircraft, VRis usually less than V1. @quietflyer It does not matter as long as the units are the same. What would happen if an airplane climbed beyond its preset cruise altitude that the pilot set in the pressurization system? We know that in cruise since lift must equal weight, we can select a design value of cruise lift coefficient (commonly around 0.2 to 0.3) and a desired cruise speed and altitude and solve for the needed wing area. 7.15 Indicated airspeed for (L/D)max will vary with altitude. Calculate (or find in Table 2.1) the approximate Density Altitude. 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? 3. mean camber line 7.6 The minimum drag for a jet airplane does not vary with altitude. 8.21 For a power-producing aircraft, maximum climb angle is found. 2.20 The total pressure of the airstream is the sum of the static pressure and the __________________. 6.25 Endurance is _____________ fuel flow. -- why? It allows the aircraft to reach takeoff velocity at a lower groundspeed than for a no-wind condition. 5.2 Wingtip vortices contribute to which type of drag? , Does an airfoil drag coefficient takes parasite drag into account? Adapted from Raymer, Daniel P. (1992). 5.3 An aircraft will enter ground effect at approximately what altitude? Which gives the best endurance? 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. 8.23 For a power producer, unaccelerated maximum velocity will occur at the intersection of the full power-available curve and the ________________. 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? RWY 27L & 27R), and the winds are 360/5, which choice(s) is/are true? x\Er0`b.awB7
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H $YAr2j{v{`ssf)w>y~|&KG=|x7j9;87w|upkA`y Of course when someone metricly assumes that one is both climbing and flying forward in m/s, that must be some airplane! Find the acceleration of the airplane. The desire for minimum thrust is obvious, based on the need to minimize fuel consumption and engine cost. Which of the type of burst below is the most dangerous? In this approach a Take-Off-Parameter, TOP, is proposed to be a function of W/S, T/W, CLTO, and the density ratio sigma () where: The value of TOP is found from the chart above. 9.5 Altitude effects Obviously altitude is a factor in plotting these curves. Adapted from James F. Marchman (2004). 10.17 Which of the following is the speed at which an aircraft must be accelerated at or before reaching 35 ft at the end of the runway? 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. Match the airfoil part name to the table number. to the wing planform shape? What sector produces the most electrical energy? 7.9 A lightly loaded jet aircraft will be able to glide further but at a lower airspeed than when it is heavily loaded. The climb angle will be the arcsine of (vertical speed / airspeed). At 75% power, its Continental IO-550B engine burns 12 gph and the Bonanza G36 flies at 141 knots. the point of minimum pressure is moved backward. First is that the figure from Raymer on the preceding page has two types of plots on it, one for ground run only and the other for ground run plus the distance required to clear a 50 ft obstacle. 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. 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. The value of T/W will depend on the desired flight speed, the wing area, and the efficiency (L/D) of the wing. 9.5 Altitude effects Obviously altitude is a factor in plotting these curves. 13.4 (Reference Figure 5.4) What speed is indicated at point B? stream Nonetheless, we can see that three parameters; thrust, weight, and wing area, are important factors to consider in takeoff. 8.5 Propeller aircraft get the highest angle of climb at (L/D)max. Hence, what we have done through the specific excess power relationship is nothing but a different way to get a familiar result. 6.17 Maximum endurance will permit your aircraft to obtain the best distance for the fuel consumed. 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. 10.12 The following items all affect takeoff performance except __________. rev2023.3.1.43268. 7.19 Increasing the weight of a thrust-producing aircraft also increases the value of (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. It's going to be harder to get a precise answer this way, and it may end up taking you longer. 13.24 If an aircraft maintaining a constant bank angle increases its airspeed while maintaining a level, coordinated turn, what will the effect be on the rate of turn (ROT)? Aerodynamics and Aircraft Performance (Marchman), { "00:_Front_Matter" : "property get [Map MindTouch.Deki.Logic.ExtensionProcessorQueryProvider+<>c__DisplayClass228_0.
