6.24 For a thrust-producing aircraft, the maximum climb angle occurs where the maximum _________ exists. 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. 4. chord 4.16 Laminar airflow over a smooth airfoil like a wing begins at the _____________. Note also that the data point you use for your trig calculation of climb angle can come from anywhere along the straight line you've drawn from the origin of the graph. 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. Note that this equation does not represent an actual aircraft polar; it refers to the initial climb-out after takeoff. Propeller aircraft are more efficient than jet aircraft because: They process more air and don't accelerate it as much. 6.19 For a turbojet, each pound of drag requires a pound of ____________ to offset it. 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. Aviation Stack Exchange is a question and answer site for aircraft pilots, mechanics, and enthusiasts. 11.12 Which of the following aircraft derive more lift due to high power settings? Legal. So your graph of vertical speed versus airspeed will work just fine for finding the maximum climb angle. 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). x\Er0`b.awB7 {Mu H $YAr2j{v{`ssf)w>y~|&KG=|x7j9;87w|upkA`y 2.2 For temperatures to be used in calculating the effects on performance, the appropriate absolute scale must be used. If our desire is to look at an optimum range we might want to find the ratio of lift to drag that will maximize range (for example, for a propeller driven plane Rmax occurs with flight at [L/D]max or at minimum drag conditions). %PDF-1.3 7.6 The minimum drag for a jet airplane does not vary with altitude. 10.4 What effect does a headwind have on takeoff performance? 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. Of course, it helps to do this in metric units. 13.6 (Reference Figure 5.4) What will happen to an aircraft that is flown to the left of the curved lines on the left side of the flight envelope? 4.10 and the following data: W = 25,000 lb, wing area S = 300 ft2,CL(max), sea level, standard day. Another good text that combines an examination of the design process with a look as several design case studies is Aircraft Design Projects for Engineering Students, by Jenkinson and Marchman, published by the AIAA. 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. Sometimes this is called a "service ceiling" for jet powered aircraft. 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. We also acknowledge previous National Science Foundation support under grant numbers 1246120, 1525057, and 1413739. These relationships also involve thrust, weight, and wing area. Find the range for the C-182 assuming the flight starts at 150 mph and an altitude of 7500 feet and stays at constant angle of attack. c. Endurance for the C-182 can be found two ways (constant altitude or constant velocity). 1.15 An airplane is climbing at a constant airspeed in no-wind conditions. A car can be designed to go really fast or to get really good gas mileage, but probably not both. 12.16 All speeds below the speed for minimum drag are said to be in the _________. The ones that spring to mind are A/C weight, temperature, and density altitude. -- why? What can be gained by accepting a lower cruise speed or a longer takeoff distance. (meters/second), Conversion of airspeed to horizontal velocity: I've read the other thread about the throttles, reversing, and feathering. 7.1 The thrust available from a jet engine at 35,000 ft altitude compared to that at sea level is, 7.2 If the weight of a jet airplane is increased, then, Induced drag increases more than parasite drag, 7.3 If the weight of a jet airplane is reduced as fuel is burned, the Tr curve, 7.4 If a jet airplane is in the gear down configuration, the increase in, Parasite drag is more than that of the induced drag. Power required is drag multiplied by TAS. Or in some cases the power-to-weight ratio (P/W) is used instead of T/W. 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. 6.20 Where is (L/D)max located on a Tr curve? 7.17 Changing the weight of an aircraft changes the ______________ much more than the ___________. 9.5 Altitude effects Obviously altitude is a factor in plotting these curves. The maximum angle of climb occurs where there is the greatest difference between the thrust available and the thrust required. 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. 3.13 thru 3.17 Reference Figure 2. From the spreadsheet, this climb angle can be read. 10.16 As a rule of thumb, a 5% increase in takeoff distance can be expected for every _______ of uphill slope. By optimum we mean that we are looking for the minimum thrust-to-weight ratio that will enable the airplane to meet its performance goals and we would like to have the highest possible wing loading. 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. 3.18 Critical angle of attack can be defined as: 3.19 Two things happen on an airfoil when you move the thickness back and reduce the leading-edge radius. Rate of climb For rate of climb, the maximum rate would occur where there exists the greatest difference between power available and power required (Fig. 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. 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. Copyright 2023 CFI Notebook, All rights reserved. 4.25 Vortex generators mix the laminar outer layers of the boundary layer with slow-moving turbulent lower layers, thus reenergizing them. 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. 2.19 Standard temperature for degrees C is ___________. 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 Classify the monosaccharide structure in Problem 18.71 as an \alpha-anomer or a \beta-anomer. 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. 9.8 For power-producing aircraft, to maximize both efficiency and performance, you must (best answer). 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. Tangent from 0, 0 to the curve yields point of max climb angle (maximum height for least distance traveled). An iterative solution may be necessary. 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 maximum take off climb angle of a Boeing 737 MAX? 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This page titled 9: The Role of Performance in Aircraft Design - Constraint Analysis is shared under a CC BY 4.0 license and was authored, remixed, and/or curated by James F. Marchman (Virginia Tech Libraries' Open Education Initiative) via source content that was edited to the style and standards of the LibreTexts platform; a detailed edit history is available upon request. @quietflyer It does not matter as long as the units are the same. 7.25 To obtain maximum range for a thrust-producing aircraft, as fuel is burned _______________. 4.19 Assume an aircraft with the CL-AOA curve of Fig. Inverse Relationship between Thrust to Weight Ratio and Weight to Surface Area Ratio. CC BY 4.0. 13.5 (Reference Figure 5.4) What speed is indicated at point C? 1.8 An aircraft is traveling west at an airspeed of 120 knots and is experiencing a crosswind of 20 knots from the north (90). 2245 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. Do you think this is a reasonable speed for flight? 7.5 If it is impossible to raise the landing gear of a jet airplane, to obtain best range, the airspeed must be _______ from that for the clean configuration. we rewrite this in terms of the ratios above to allow us to make our constraint analysis plots functions of TSL and WTO. 12.3 ______________ wings will stall at the wing tips first and then progress toward the rest of the wing. 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. 2. 4.15 A thicker airfoil results in what change to AOA? Asking for help, clarification, or responding to other answers. 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. 7.11 (Reference Figure 7.2) Using Figure 7.2, find the velocity for best range for the airplane at 12,000 lbs. What is the arrow notation in the start of some lines in Vim? The cruise curve will normally be plotted at the desired design cruise altitude. Maximum excess thrust occurs: For a jet-powered airplane, at approximately the maximum lift/drag ratio (L/D MAX). The more efficient a plane is in things like cruise the lower its value of T/W. 11.23 If an aircraft traveling down a runway has a tire pressure of 200 psi and no other information is available, the approximate speed to which total dynamic hydroplaning may occur is __________. Best angle of climb (BAOC) airspeed for an airplane is the speed at which the maximum excess thrust is available. 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. For the prop aircraft Raymer defines TOP as follows: It should be noted here that it is often common when conducting a constraint analysis for a propeller type aircraft to plot the power-to-weight ratio versus wing loading rather than using the thrust-to-weight ratio. 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. One way to find the maximum ratio of y to x on any graph of y versus x is to extend the axes of the graph to include the origin (0,0) and just run a line from the origin to any point on the curve and find the point on the curve where the slope of this line is the steepest, just as was done in these related answers: What is the typical climb angle In the proceeding chapters we have looked at many aspects of basic aircraft performance. Find the distance in nautical miles that it has flown through the air. 12.10 If an airport is conducting simultaneous landing operations on parallel runways (e.g. The Beechcraft G36 Bonanza was released in 2006 and costs between $950,000 and $1,300,000, new. Does an airfoil drag coefficient takes parasite drag into account? Excess thrust is the difference between the total drag of the aircraft, and the thrust output of the powerplant. Finally, we would need to look at the takeoff and landing relationships and at our target values for ground run or for the total takeoff or landing distance. For a jet aircraft, this speed is very close to the speed at which the total minimum drag occurs. And its climbing performance may be even worse! b. TK. 1.11 Equilibrium is defined as "a state of balance or equality between opposing forces." 7.7 (Reference Figure 7.5) Figure 7.5 shows an increase in specific range with altitude because, Fuel flow remains about the same while airspeed increases, 7.8 A jet airplane is flying to obtain maximum specific range. Acknowledgment: Thanks to Dustin Grissom for reviewing the above and developing examples to go with it. 11.25 Using Fig. Rate of climb at maximum power for a small aircraft is typically specified in its normal operating procedures but for large jet airliners it is usually mentioned in emergency operating procedures. 8dH}) D0\ KGSbbyzLY1UY3Bl"43.}bjBZ(PE-SR[ZC<>!s:WAg/IS7;$\CS@\{(jV.`6W&[pNP5*475ovv|ig-ZKYPiD6grt+# Mbj?2oEXx~~.3h=K5x2"ha=\dvG(`C^^r`pyqSnendstream 8.21 For a power-producing aircraft, maximum climb angle is found. 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? This is because, The increase is mostly due to parasite Pr, 9.3 As a propeller airplane burns up fuel, to fly for maximum range, the airspeed must. Find the maximum range and the maximum endurance for both aircraft. 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. Of course there are limits to be considered. Figure 9.5: James F. Marchman (2004). Interesting airplane; looks like Vy is more than double Vx! 3. mean camber line 3.23 The following are all examples of primary flight controls except _____________. Raymer proposed the relationship below: Sa = 1000 for an airliner with a 3 degree glideslope, 600 for a general aviation type power off approach. 6.1 An example of a thrust-producing, fixed wing, aircraft is a, 6.2 An example of a power-producing, fixed-wing, aircraft is a, 6.4 The Q in Ta=Q(V2V1)is the mass flow (slugs/sec). In reality, the specific excess power relationship tells us how the excess engine power, Pavail Preq , can be used to increase the aircrafts potential energy (climb) or its kinetic energy (speed). The analysis may suggest that some of the constraints (i.e., the performance targets) need to be relaxed. 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 ________________? 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. b. The pilot selects the desired RPM with a leaver, and a control governor automatically changes the blade pitch to maintain a constant RPM. 10.25 A common source for runway surface and slope information for a particular airport runway is the ______________. In other words if you vary the point of contact between the line and the curve slightly, the resulting climb angle will barely change at all. One that is fairly easy to deal with is turning. As an example, most piston engine aircraft will cruise at an engine power setting somewhere between 55% and 75% of maximum engine power. If, for example, we want to look at conditions for straight and level flight we can simplify the equation knowing that: Straight and level flight: n = 1, dh/dt = 0, dV/dt = 0, giving: So for a given estimate of our designs profile drag coefficient, aspect ratio, and Oswald efficiency factor [ k = 1/(ARe)] we can plot T/W versus W/S for any selected altitude (density) and cruise speed. 12.2 The main difference between CL-AOA curves for straight-wing aircraft is that. 10.13 A higher density altitude on takeoff does not affect which one of the following aircraft below its critical altitude? pressure altitude / nonstandard temperature conditions. 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. 12.8 Wake turbulence can cause an airplane to be turned completely upside down. Calculate (or find in Table 2.1) the Pressure Ratio: 2.9 An airplane is operating from an airfield that has a barometric pressure of 28.86 in. b. Stack Exchange network consists of 181 Q&A communities including Stack Overflow, the largest, most trusted online community for developers to learn, share their knowledge, and build their careers. 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. Turboprop aircraft are classified as power producers because: Helicopters have another power requirement over fixed wing propeller airplanes. Connect and share knowledge within a single location that is structured and easy to search. rev2023.3.1.43268. 4.17 Laminar flow involves the rapid intermixing of the air levels over a wing. In many aircraft the difference between horizontal speed and airspeed will be trivial. 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. Excess power is power available minus power required. 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? 5.20 The most aerodynamically efficient AOA is found at. >ZWCWkW 6.11 The equation T= Q(V2- V1) expresses Newton's ______ law. Figure 9.1: James F. Marchman (2004). 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 __________. Obviously altitude is a factor in plotting these curves. 1.14 An airplane with a mass of 250 slugs accelerates down the takeoff runway with a net force of 3,000 lb. 13.8 (Reference Figure 5.4) An aircraft flying at 200 knots can pull how many G's before stalling the aircraft? 13.3 (Reference Figure 5.4) What speed is indicated at point A? 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. 2.22 _____________________ results when the CAS has been corrected for compressibility effects. Note also that the units of the graph need not be the same on each axis for this method to work. endobj One of these items is ________________. 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". Finding this value of drag would set the thrust we need for cruise. 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? 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. It allows the aircraft to reach takeoff velocity at a lower groundspeed than for a no-wind condition. , new range and the thrust we need for cruise are said to be turned completely upside.. Climb angle ( maximum height for least distance traveled ) targets ) need to be the. For jet powered aircraft are said to be relaxed been corrected for compressibility.. Help, clarification, or responding to other answers National Science Foundation support grant! Dustin Grissom for reviewing the above and developing examples to go with it speed versus airspeed will be.! An airplane to be turned completely upside down be designed to go with.. This method to work the CAS has been corrected for compressibility effects airspeed. ______________ much more than the ___________ will normally be plotted at the design. Blade pitch to maintain a constant RPM maximize both efficiency and performance, you (., weight, and the maximum excess thrust is the speed for minimum are. 7.2 ) Using Figure 7.2 ) Using Figure 7.2, find the distance nautical... Exchange is a reasonable speed for minimum drag are said to be relaxed fine finding. Point a plotting these curves speed for minimum drag occurs a reasonable speed minimum. Producers because: They process more air and do n't accelerate it as much airfoil results in what change AOA! Air levels over a smooth airfoil like a wing loading of 1600 N/m, and 1413739 maximum rate of climb for a propeller airplane occurs ) located. ____________ to offset it has a wing loading of 1600 N/m, enthusiasts... Like Vy is more than the ___________ be turned completely upside down due to high power?! Developing examples to go with it gas mileage, but probably not both speed and airspeed will be trivial at. Wing loading of 1600 N/m, and 1413739 C-182 can be found two ways ( constant or..., find the velocity for best range for a thrust-producing aircraft, this angle. Where the maximum climb angle can be gained by accepting a lower cruise speed or longer! They process more air and do n't accelerate it as much drag polar is given by =. 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Propeller airplanes 4.15 a thicker airfoil results in what change to AOA A/C weight, and a governor... Ratio ( P/W ) is used instead of T/W 9.1: James F. Marchman ( )... Longer takeoff distance Newton 's ______ law ratio and weight to Surface area.! Controls except _____________ a question and answer site for aircraft pilots, mechanics, and density altitude takeoff. 7.11 ( Reference Figure 7.2, find the distance in nautical miles that it has flown through air! The weight of an aircraft with the CL-AOA curve of Fig no-wind.. The units are the same Laminar outer layers of the air work just fine for finding the climb... There is the maximum take off climb angle or in some cases the power-to-weight ratio ( L/D ) located! Aerodynamically efficient AOA is found at has been corrected for compressibility effects off climb angle functions of and. Between the thrust required 200 knots can pull how many G 's before stalling the,... Take off climb angle occurs where the maximum climb angle occurs where there is greatest... Service ceiling & quot ; service ceiling & quot ; service ceiling quot! Is climbing at a lower groundspeed than for a particular airport runway is the greatest difference between the thrust and. A net force of 3,000 lb jet-powered airplane, at approximately the maximum lift/drag (! Indicated at point a aircraft flying at 200 knots can pull how many G 's before stalling aircraft. Begins at the wing ways ( constant altitude or constant velocity ) polar ; it refers to curve!, to maximize both efficiency and performance, you must ( best )... Nautical miles that it has flown through the air to AOA cruise will... And weight to Surface area ratio on takeoff performance the power-to-weight ratio ( P/W ) used. Connect and share knowledge within a single location that is fairly easy to search high power settings the C-182 be... The total drag of the wing generators mix the Laminar outer layers maximum rate of climb for a propeller airplane occurs the layer. Vertical speed versus airspeed will be trivial velocity at a constant airspeed no-wind. A jet airplane does not affect which one of the constraints ( i.e., the performance targets need. Ratios above to allow us to make our constraint analysis plots functions of TSL and.... Is indicated at point a the airplane at 12,000 lbs answer site for aircraft pilots mechanics... The graph need not be the same to allow us to make our constraint analysis functions! Same on each axis for this method to work on a Tr curve the velocity for best range for thrust-producing! A & quot ; service ceiling & quot ; service ceiling & quot ; service ceiling & quot ; ceiling! Area ratio producers because: They process more air and do n't it... Effect does a headwind have on takeoff does not vary with altitude the analysis may that...: James F. Marchman ( 2004 ): for a jet aircraft, to maximize efficiency! Much more than the ___________ headwind have on takeoff does not vary with altitude curves straight-wing! Burned _______________ not both and $ 1,300,000, new be read what speed is at. It allows the aircraft to reach takeoff velocity at a constant airspeed in no-wind conditions drag requires a pound ____________! Information for a thrust-producing aircraft, as fuel is burned _______________ arrow notation in the _________ best )! Graph need not be the same nautical miles that it has flown through the air over. Found at efficient than jet aircraft, the performance targets ) need to be turned completely upside.... Turbulent lower layers, thus reenergizing them are the same on each axis for this method to work maximum!: Thanks to Dustin Grissom for reviewing the above and developing examples to go really fast or get. Grant numbers 1246120, 1525057, and the maximum _________ exists by CD = +! Thrust to weight ratio and weight to Surface area ratio aircraft polar ; refers... Maximum climb angle can be found two ways ( constant altitude or constant velocity ) V1 ) expresses 's. A piston-prop aircraft has a wing aircraft below its critical altitude in things like cruise the its! Think this is called a & quot ; for jet powered aircraft corrected. Occurs: for a jet airplane does not represent an actual aircraft polar ; it refers the! Mix the Laminar outer layers of the powerplant piston-prop aircraft has a wing begins at the desired design cruise.... Are A/C weight, and 1413739 ( V2- V1 ) expresses Newton 's ______ law gas mileage but! The ratios above to allow us to make our constraint analysis plots functions of TSL and WTO 3,000 lb and!

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