2.6 The corrections that must be made to indicated airspeed (IAS) to obtain calibrated airspeed (CAS) are: 2.7 The correction from equivalent airspeed (EAS) to true airspeed (TAS) is dependent on: 2.8 An airplane is operating from an airfield that has a barometric pressure of 28.86 in. Assuming you maintain a constant altitude, a decrease in temperature will: The pressure of the air at the level of consideration divided by the sea level standard pressure, Equal to pressure ratio divided by temperature ratio. Find the acceleration of the airplane. What is the stall speed? @quietflyer: Yes, this requires another arithmetical operation because airspeed is the vector sum of vertical and horizontal speed. How to properly visualize the change of variance of a bivariate Gaussian distribution cut sliced along a fixed variable? 11.25 Using Fig. 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 steepest climb angle occurs when the ratio of vertical speed to horizontal speed is maximized. 5.2 Wingtip vortices contribute to which type of drag? I frequently, but not always, have a severe imbalance between the two engines. Hence, what we have done through the specific excess power relationship is nothing but a different way to get a familiar result. 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. 11.10 The minimum glide angle also corresponds to ____________________. Service Ceiling-This is the maximum density altitude where the best rate of climb airspeed (Vx) will produce a 100 fpm climb with both engines at max continuous power. 12.1 Which statement is true with respect to Lift Coefficient (CL) and the Effect of Sweepback on Coefficient of Lift - Angle of Attack (AOA) curves? Therefore both approaches must have the same solution: when the ratio of vertical speed to airspeed is maximized, then the ratio of vertical speed to horizontal speed is also maximized. 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. How sensitive is the maximum range for the Cessna 182 to aspect ratio and the Oswald efficiency factor, i.e. These included takeoff and landing, turns, straight and level flight in cruise, and climb. 9.7 For Jet and Propeller aircraft, the two things shared at L/Dmax are the Maximum Engine-out Glide speed and Maximum range. a. 3.20 The component of the aerodynamic force that is perpendicular to the relative wind is ________________. 4.23 Stall is airflow separation of the boundary layer from the lifting surface. 4.20 An increase in CL(max)and a decrease in stall AOA will be noted when ___________. pressure altitude / nonstandard temperature conditions. 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. 6.11 The equation T= Q(V2- V1) expresses Newton's ______ law. 6.13 There are two basic types of climbs when considering the performance of jet aircraft, delayed climb and _____________. 6.16 Which one of the following items does not occur at (L/D)max for a jet aircraft? Another factor to consider would be the desired maximum speed at the cruise altitude. 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. b. The design process usually begins with a set of design objectives such as these we have examined, a desired range, payload weight, rate of climb, takeoff and landing distances, top speed, ceiling, etc. 6.18 Thrust-producing aircraft have a fuel consumption roughly proportional to thrust output. 12.2 The main difference between CL-AOA curves for straight-wing aircraft is that. @quietflyer It does not matter as long as the units are the same. 9.10 As a power-producing aircraft burns off fuel, ROC will ___________ for a given velocity. Maximum Rate of Climb for a propeller-driven airplane Since the available power is constant with W, the maximum excess power, RIC occurs at the flight velocity for minimum power required therefore: An equation for the maximum rate of climb is obtained by substituting V(R/C)max This can then be used to find the associated speed of flight for maximum rate of climb. 1.15 An airplane is climbing at a constant airspeed in no-wind conditions. I've made the recommended changes and have decent reverse thrust. 12.4 ______________ wings will stall at the wing root first and then progress toward the rest of the wing. 3.9 For a cambered airfoil, the center of pressure (CP), 3.10 For a cambered airfoil, an increase in velocity results in, 3.11 A decrease in the AOA of any airfoil will result in, 3.12 The aerodynamic center (AC) is located at, 25% chord subsonically and 50% chord supersonically. Of course there are limits to be considered. This can be put into the drag equation with the numbers found above to get the thrust or power needed to reach that maximum speed. 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? 9.9 For a power-producing aircraft, an increase in weight results in a decrease of Vmax. We just end up writing that result in a different form, in terms of the thrust-to-weight ratio and the wing loading. + (kn2/q)(WTO/S)(Walt/WTO) + (1/V)dh/dt + (1/g)dV/dt} . 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 __________. Use MathJax to format equations. See Page 1. 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. 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. Power required to overcome induce drag varies: a. inversely with V b. inversely with V2 c. inversely with V3 d. directly with V. 14. In computing FAR 25 climb performance, the effects of one engine inoperative must include not only a decrease in thrust, but an increase in drag due to: 1) windmilling drag of inoperative engine or windmilling or feathered drag of propeller. Turboprop aircraft are classified as power producers because: Helicopters have another power requirement over fixed wing propeller airplanes. 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. To obtain best range the pilot now must, 8.2 Maximum rate of climb for a propeller airplane occurs at, 8.3 The turboprop aircraft has its lowest specific fuel consumption at about 25,000 feet altitude because, This is a compromise between (a) and (b) above, 8.4 The lowest point on the Pr curve is (L/D)max. 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. What other design objectives can be added to the constraint analysis plot to further define our design space? Do German ministers decide themselves how to vote in EU decisions or do they have to follow a government line? And to add a description to the axes of a plot. Find the maximum range and the maximum endurance for both aircraft. 7.16 With a typical drag curve, how many times does the thrust available line intersect the thrust required curve? Find the Rate of Climb. 7.17 Changing the weight of an aircraft changes the ______________ much more than the ___________. 2.13 Using Table 2.1 and the appropriate equation, calculate the dynamic pressure, q, at 7,000 ft density altitude and 140 knots TAS. 4.24 In reference to airfoil lift characteristics, there are two ways that CL(max)of an airfoil could be increased: by increasing its thickness and by ________________________. 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. It usually is restricted to either the takeoff setting or the cruise setting. Figure 9.2: James F. Marchman (2004). 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. Does an airfoil drag coefficient takes parasite drag into account? 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 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. It only takes a minute to sign up. So no re-plotting is needed, just get out your ruler and start drawing. 8.1 The pilot of a propeller airplane is flying at the speed for best range under no-wind conditions. The Beechcraft G36 Bonanza was released in 2006 and costs between $950,000 and $1,300,000, new. It's going to be harder to get a precise answer this way, and it may end up taking you longer. Available from https://archive.org/details/9.4_20210805. 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). Effect of Desired Takeoff Characteristics on Aircraft Design Space. CC BY 4.0. 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. 11.18 Which factor affects the calculation of landing performance for a typical aircraft? b. 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. 12.6 The best way to control airspeed is with the ___________, while the best way to control altitude/descent rate is with the ____________. 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. Normally we would look at turns at sea level conditions and at takeoff weight. Calculate (or find in Table 2.1) the approximate Density Altitude. However Vy is actually only a speed, not a climb rate, and will correspond to slightly different rates of climb depending on a few factors. Legal. 13.4 (Reference Figure 5.4) What speed is indicated at point B? Figure 6.1: Finding Velocity for Maximum Range 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. Figure 9.7: Effect of R & e Variation on max Range Cessna 182. 6.23 Vy is also known as __________________. Fw5| } V e = 2 W S L S C L = 794.1 f p s. The angle of climb for maximum rate of climb (not maximum angle of climb) can then be found as follows: sin = T D W = T W C D / C L = 0.429 0.013 + 0.157 (0.088) 2 0.088 = 0.267. = 15.51 Copyright 2023 CFI Notebook, All rights reserved. 4.21 When analyzing the air moving from the leading edge toward the trailing edge of a wing, until the air reaches the point of minimum pressure it is in a favorable pressure gradient. 4. chord 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? The second is that the takeoff parameter (TOP) defined for propeller aircraft is based on power requirements (specifically, horsepower requirements) rather than thrust. 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. Acknowledgment: Thanks to Dustin Grissom for reviewing the above and developing examples to go with it. In straight and level flight we know: And if we simply combine these two equations we will get the same relationship we plotted above. 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 _________. Under what conditions can the maximum angle of climb be achieved for jet and propeller aircraft? 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. Suppose that a 1.0-mm-thick layer of water is inserted into one arm of a Michelson interferometer. 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. 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? 12.5 What statement(s) is/are true regarding the region of reverse command? The LibreTexts libraries arePowered by NICE CXone Expertand are supported by the Department of Education Open Textbook Pilot Project, the UC Davis Office of the Provost, the UC Davis Library, the California State University Affordable Learning Solutions Program, and Merlot. % Figure 9.4: Kindred Grey (2021). The last parameter in the B equation above is a, a term that appears in the thrust equation: a relationship that comes from the momentum equation where T0 is the static thrust or the thrust when the airplane is standing still. 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? 12.7 An airplane is making a final approach for a landing and encounters a horizontal wind shear. The question with the design of an airplane as with a car or a tire, is how do we arrive at the best compromise that will result in a good all around design while still being better than average in one or two desired areas? 5.4 When an aircraft enters ground effect, what effect does it have on induced drag? The local gravitational acceleration g is 32 fps2. Is this a reasonable flight speed? For a propeller-powered airplane, at an airspeed just above stall speed and below L/D MAX. 5.19 An aircraft will begin to experience ground effect_____________ above the surface. If T/W = 1.0 or greater we need no wing. How can I find the maximum climb angle of a propeller driven aircraft from a graph of vertical velocity against airspeed? stream So maximum rate of climb occurs at the speed at which excess power is greatest. The climb angle will be the arcsine of (vertical speed / airspeed). 9.8 For power-producing aircraft, to maximize both efficiency and performance, you must (best answer). Here we should note that the space to the right of the dashed line for stall is out of bounds since to fly here would require a higher maximum lift coefficient. 9.11 As a power-producing aircraft burns off fuel, airspeed should be ____________ to maintain maximum range. Figure 9.1: James F. Marchman (2004). ,8Ot_8KOgiy*I&lw4d^ "(y ,)r^oZq+#^?u^Jx!u3tpG_$=FJ[)M[U2>c^C:jf%r@cig=" Z#!E:C(qGL^P[li40M=MtvQy{vKHSv,@1i+6>8e;j>PYqV~zT5,e$CR%*n#f%CzL. QZ-o{s[h)9,zIxHDmfw8nO2yZOp_S,1,t'KXP9PXA x!`DVHw$Gn{?J dB~x%~ndpg+>2[B8J*3B}%\3iv}k^v~~h jKj 2qY!ZW` YWDv]m8keDzkbW`@w%=1CUd )bh#7 l&/B3AIuQLKH)q*#%U'9DIayeB47fcoP& I4xiZM A8xrABZ|*NTwD! It tells us that to make the airplane do what we want it to do we are restricted to certain combinations of T/W and W/S. 5.17 An airplane with a heavy load _______________ when lightly loaded. 13.20 An aircraft in a level, coordinated turn with a bank angle of 60 is maintaining _____ G's. 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. 10.4 What effect does a headwind have on takeoff performance? 6.25 Endurance is _____________ fuel flow. Hg and a runway temperature of 20C. <> 13.19 The G's required for an aircraft to maintain altitude in a coordinated turn are determined by ____________. In many aircraft the difference between horizontal speed and airspeed will be trivial. 7.20 When a pilot lowers the landing gear, _______________ is increased. 13. 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. 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. 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. 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. For a propeller-powered airplane, at an airspeed just above stall speed and below L/D MAX. 3.23 The following are all examples of primary flight controls except _____________. Find the Drift Angle. What we want, however, is the best combination of these parameters for our design goals. 11.17 Headwinds and tailwinds affect the landing distance by the same amount as they affect the takeoff distance. 13.3 (Reference Figure 5.4) What speed is indicated at point A? 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? A tailwind is encountered. For low angles of climb (non high performance aircraft) airspeed may be directly compared to vertical velocity, as the cosine of lower angles is very close to 1. Figure 9.3: James F. Marchman (2004). 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. 11.13 Jet aircraft do not suffer from a thrust deficiency at low airspeeds. The maximum rate of climb at a given speed will then depend on the difference between the power available from the engine at that speed and the power required for straight and level flight. 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. Max camber (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.). The standard RoC formula (using FPM and LBS) usually shows the excess HP at sea level at max gross to be around 33% of the rated HP for most GA propeller aircraft. d. If all commercial users agreed to cut their energy usage by 20%, which group would be the biggest user of electrical energy in the United States? 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? 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. 1.17 An airplane weighs 8,000 lbs and is flying at 6,000 ft altitude and an airspeed of 200 fps. This can be determined from the power performance information studied in the last chapter. The analysis may suggest that some of the constraints (i.e., the performance targets) need to be relaxed. 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. 2.5 Bernoulli's equation for subsonic flow states that: If the velocity of an airstream within a tube is increased, the static pressure of the air decreases. 8.21 For a power-producing aircraft, maximum climb angle is found. It says that we need a higher thrust-to-weight ratio to climb than to fly straight and level. 10.25 A common source for runway surface and slope information for a particular airport runway is the ______________. Hg and a runway temperature of 20C. And they may be different still in climb. Has the term "coup" been used for changes in the legal system made by the parliament? 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. *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! 8.23 For a power producer, unaccelerated maximum velocity will occur at the intersection of the full power-available curve and the ________________. By clicking Post Your Answer, you agree to our terms of service, privacy policy and cookie policy. As one of my students once put it, the thrust-to-weight ratio (T/W) is a measure of how much of a rocket your plane is. 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. A head wind is encountered. Variometer [ edit] 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.
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