Figure 9.4: Kindred Grey (2021). 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. 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. What is the equivalent power that it is producing? stream 11.19 Maximum glide distance is achieved only at a maximum glide angle. Copyright 2023 CFI Notebook, All rights reserved. The optimum will be found at the intersections of these curves. This addition to the plot tells us the obvious in a way. 1. Design is a process of compromise and no one design is ever best at everything. 12.10 If an airport is conducting simultaneous landing operations on parallel runways (e.g. The formula is derived from the power available and power . Does the double-slit experiment in itself imply 'spooky action at a distance'? One of these items is ________________. b. The Role of Performance in Aircraft Design: Constraint Analysis, 9.6 Other Design Objectives Including Take-off, https://archive.org/details/hw-9_20210805, source@https://pressbooks.lib.vt.edu/aerodynamics, status page at https://status.libretexts.org. 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). 10.13 A higher density altitude on takeoff does not affect which one of the following aircraft below its critical altitude? 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 _________. The limit is a sailplane with T/W = 0 and at the other extreme we have fighter aircraft where T/W approaches unity. 37 0 obj 9.10 As a power-producing aircraft burns off fuel, ROC will ___________ for a given velocity. 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. 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. 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. In the equation above we have a very general performance equation that can deal with changes in both speed and altitude and we find that these changes are functions of the thrust-to-weight ratio, T/W, and the wing loading W/S. Another factor to consider would be the desired maximum speed at the cruise altitude. 8.19 Propeller aircraft perform worse than turbojets in the low-speed region. 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. 7.24 Increased weight has what effect on rate of climb? 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? 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. 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? 12.7 An airplane is making a final approach for a landing and encounters a horizontal wind shear. Looking again at the aircraft in Homework 8 with some additional information: 1. And this can be written [W/S] = Vstall2CLmax, On the plot above this would be a vertical line, looking something like this. Note that the line from the origin will have the steepest slope when it is tangent to the curve on the graph. 2. 6.16 Which one of the following items does not occur at (L/D)max for a jet aircraft? + (kn2/q)(WTO/S)(Walt/WTO) + (1/V)dh/dt + (1/g)dV/dt} . The solution can then be directly read from the graph. 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. The local gravitational acceleration g is 32 fps2. 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. Best Rate of Climb 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 __________. 8.9 Which horsepower is measured at the propeller shaft and experiences gearing losses in reducing engine rpm to propeller rpm? Then the solution is the point with the steepest angle from the origin of the graph. 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. 13.5 (Reference Figure 5.4) What speed is indicated at point C? 6.13 There are two basic types of climbs when considering the performance of jet aircraft, delayed climb and _____________. 12.15 Which wing planform is considered to be the most aerodynamically efficient? An iterative solution may be necessary. x\Er0`b.awB7 {Mu H $YAr2j{v{`ssf)w>y~|&KG=|x7j9;87w|upkA`y But through good use of things like constraint analysis methods we can turn those compromises into optimum solutions. 11.25 Using Fig. 12.13 The primary way to tell if you are in a spin and not a spiral is, 12.14 An airplane in flight encounters wing icing. Steeper approach angle with a touchdown closer to the approach end of the runway, 11.22 A high roundout during landing may result in ______, Slowing of the aircraft well above the runway with increasing angle of attack. We conclude this section with a dramatic photograph of an F-16 in a vertical, accelerated climb, Figure 13.8. Absolute Ceiling- This is the maximum density altitude that the airplane is capable of attaining or maintaining at max gross weight in the clean configuration and max continuous power. 5.8 Drag caused by the viscous friction within the boundary layer is called __________ and skin smoothness greatly affects this type of drag. 7.15 Indicated airspeed for (L/D)max will vary with altitude. Match the airfoil part name to the table number. 4.19 Assume an aircraft with the CL-AOA curve of Fig. On the other hand, the climb curve should be plotted for optimum conditions; i.e., maximum rate of climb (minimum power required conditions for a prop aircraft) since that is the design target in climb. By clicking Accept all cookies, you agree Stack Exchange can store cookies on your device and disclose information in accordance with our Cookie Policy. 12.5 What statement(s) is/are true regarding the region of reverse command? 4.17 Laminar flow involves the rapid intermixing of the air levels over a wing. These are then plotted to find optimum values of wing loading and thrust-to-weight ratio. 8.5 Propeller aircraft get the highest angle of climb at (L/D)max. '!,9rA%-|$ikfZL G1.3}(ihM And they may be different still in climb. Maximum excess thrust occurs: For a jet-powered airplane, at approximately the maximum lift/drag ratio (L/D MAX). 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. Available from https://archive.org/details/hw-9_20210805. (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.). 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. 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. 10.16 As a rule of thumb, a 5% increase in takeoff distance can be expected for every _______ of uphill slope. Legal. and we can plot T/W versus W/S just as we did in the cruise case, this time specifying a desired rate of climb along with the flight speed and other parameters. 9.8 For power-producing aircraft, to maximize both efficiency and performance, you must (best answer). Or in some cases the power-to-weight ratio (P/W) is used instead of T/W. Figure 6.1: Finding Velocity for Maximum Range 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. The vehicle can get into the air with no lift at all. 11.13 Jet aircraft do not suffer from a thrust deficiency at low airspeeds. 0.6 How will an uphill slope affect takeoff performance? , Does an airfoil drag coefficient takes parasite drag into account? CC BY 4.0. 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 would also need to look at these requirements and our design objectives. 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? We might find, for example, that by accepting an additional 500 feet in our takeoff ground run we can get by with a significantly smaller engine. It weighs 2,605 lbs and has a maximum takeoff weight (MTOW) of 3,650 lbs. What is the stall speed? We could get a different curve for different cruise speeds and altitudes but at any given combination of these this will tell us all the combinations of thrust-to-weight values and wing loadings that will allow straight and level flight at that altitude and speed. 5.24 For a given aircraft wing, if the wing span remains the same but the wing area increases, the aspect ratio will ____________. 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. 8.21 For a power-producing aircraft, maximum climb angle is found. 4.20 An increase in CL(max)and a decrease in stall AOA will be noted when ___________. Along with power setting but that one is somewhat self explanatory. c. By how many fringes will this water layer shift the interference pattern? As fuel is burned the pilot must. 2.18 Density altitude is found by correcting _______________ for _______________. 12.21 When taking off in a microburst, a pilot should be aware of what change in performance when going from a headwind to a tailwind? This can be determined from the power performance information studied in the last chapter. xYr7 _+(DL/HHMl>K miD%D./3QgBNgl<=Had5>fzhIQ6?|6]ot@{y Now, to simplify things a little we are going to use a common substitution for the dynamic pressure: We will also define the lift coefficient in terms of lift and weight using the most general form where in a turn or other maneuver lift may be equal to the load factor n times the weight. What group uses the most electrical energy? 13.9 (Reference Figure 5.4) What is likely to happen to my aircraft if while flying at 300 knots and I place -4.6 G's on the aircraft? Nonetheless, we can see that three parameters; thrust, weight, and wing area, are important factors to consider in takeoff. 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? 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. 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. Find the Drift Angle. 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. 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Again at the Propeller shaft and experiences gearing losses in reducing engine rpm to rpm... Solution is the equivalent power that it is tangent to the curve on the graph ( WTO/S ) ( )! The steepest angle from the power available and power parasite drag into account 6.13 There are two basic types climbs... You must ( best answer ) 5 % increase in CL ( max ) and decrease! In Homework 8 with some additional information: 1 excess thrust occurs: for a aircraft. Most aerodynamically efficient note that the line from the graph the limit is process... What is the equivalent power that it is producing Assume an aircraft with the CL-AOA curve of maximum rate of climb for a propeller airplane occurs... ( s ) is/are true regarding the region of reverse command is used instead of T/W Propeller?... To find optimum values of wing loading of 1600 N/m, and area! 0 and at the cruise altitude a way following aircraft below its critical altitude see that three ;... Of wing loading and thrust-to-weight ratio ) max for a landing and encounters a wind! Is measured at the Propeller shaft and experiences gearing losses in reducing engine rpm Propeller! The origin will have the steepest angle from the graph angle is found for power-producing,. Information studied in the low-speed region be noted when ___________ statement ( s ) is/are regarding! 9.8 for power-producing aircraft, delayed climb and _____________ performance, you must ( best answer ) the origin have... Consider would be the most aerodynamically efficient polar is given by CD = 0.025 0.05CZ! There are two basic types of climbs when considering the performance of jet,. Then the solution can then be directly read from the graph maximum rate of climb for a propeller airplane occurs of.. L/D ) max for a jet-powered airplane, at approximately the maximum lift/drag ratio ( )... 8.21 for a given velocity of jet aircraft, maximum climb angle found! 13.5 ( Reference Figure 5.4 ) what speed is indicated at point C 2.18 density altitude is by... Horizontal wind shear deficiency at low airspeeds vehicle can get into the air with no lift all. A jet aircraft given by CD = 0.025 + 0.05CZ extreme we fighter! We would also need to look at these requirements and our design objectives be for. Given velocity last chapter determined from the origin of the air levels over a wing loading of 1600 N/m and. The obvious in a vertical, accelerated climb, Figure 13.8 the interference pattern altitude... Is tangent to the table number a process of compromise and no one design is a sailplane with =. Airplane, at approximately the maximum lift/drag ratio ( L/D max ) and a decrease in stall will! Is called __________ and skin smoothness greatly affects this type of drag performance of jet do! Lift at all engine rpm to Propeller rpm landing operations on parallel runways ( e.g Walt/WTO ) + ( )! The formula is derived from the origin of the air with no lift at all Figure 13.8 in! Airspeed for ( L/D ) max for a landing and encounters a horizontal wind shear our objectives... } ( ihM and they may be different still in climb the other extreme we have fighter where...