12.11 What two things are necessary for an aircraft to enter a spin? 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? Note that the line from the origin will have the steepest slope when it is tangent to the curve on the graph. Raymer, Daniel P. (1992). 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. 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. 1.18 An aircraft's turbojet engine produces 10,000 lbs of thrust at 200 knots true airspeed. where A = g[(T0/W) ]. Making statements based on opinion; back them up with references or personal experience. MathJax reference. , Does an airfoil drag coefficient takes parasite drag into account? What is the equivalent power that it is producing? we rewrite this in terms of the ratios above to allow us to make our constraint analysis plots functions of TSL and WTO. False Propeller aircraft are more efficient than jet aircraft because: They process more air and don't accelerate it as much Turboprop aircraft are classified as power producers because: Both A and C: The goal of maximum wing loading may not be as obvious to the novice designer but this means the wing area is kept to a minimum which gives lower drag. 7.20 When a pilot lowers the landing gear, _______________ is increased. We also acknowledge previous National Science Foundation support under grant numbers 1246120, 1525057, and 1413739. This can be done fairly easily by going back to the constraint analysis equations and substituting P/V everywhere that a thrust term appears. 11.4 How does an increase in altitude affect landing performance? For a propeller-powered airplane, at an airspeed just above stall speed and below L/D MAX. Find the potential energy. To get best range now the pilot must, Slow down by an amount less than the wind speed, 6.8 To obtain maximum range a jet airplane must be flown at, 6.9 Maximum rate of climb for a jet airplane occurs at, 6.10 Maximum climb angle for a jet aircraft occurs at. 5.4 When an aircraft enters ground effect, what effect does it have on induced drag? 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? 7.9 A lightly loaded jet aircraft will be able to glide further but at a lower airspeed than when it is heavily loaded. I frequently, but not always, have a severe imbalance between the two engines. 10.13 A higher density altitude on takeoff does not affect which one of the following aircraft below its critical altitude? Hence, what we have done through the specific excess power relationship is nothing but a different way to get a familiar result. Of course, it helps to do this in metric units. ,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! 6.13 There are two basic types of climbs when considering the performance of jet aircraft, delayed climb and _____________. Hg and a runway temperature of 20C. 6.24 For a thrust-producing aircraft, the maximum climb angle occurs where the maximum _________ exists. 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. What would happen if an airplane climbed beyond its preset cruise altitude that the pilot set in the pressurization system? In reality, the landing distance is pretty much determined by the stall speed (the plane must touch down at a speed higher than stall speed, often about 1.2 VStall) and the glide slope (where obstacle clearance is part of the defined target distance). 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 __________. c. Endurance for the C-182 can be found two ways (constant altitude or constant velocity). To learn more, see our tips on writing great answers. Inverse Relationship between Thrust to Weight Ratio and Weight to Surface Area Ratio. CC BY 4.0. 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. The steepest climb angle occurs when the ratio of vertical speed to horizontal speed is maximized. 7.22 The value of (L/D)max changes when the gear and flaps are lowered. Obviously altitude is a factor in plotting these curves. The formula is derived from the power available and power . Figure 6.1: Finding Velocity for Maximum Range If there is an increase in air pressure, it will: Affect air density by increasing the density. 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. How to find trim condition of a sectional airfoil without knowing the angle of attack? Find the Groundspeed. Best Rate of Climb 11.15 Foot brakes should be utilized before the nosewheel touches the ground during landing. Design is a process of compromise and no one design is ever best at everything. 5. max thickness. Find the maximum range and the maximum endurance for both aircraft. '!,9rA%-|$ikfZL G1.3}(ihM The ones that spring to mind are A/C weight, temperature, and density altitude. nautical miles per hour) and vertical speed (feet per minute). It does this by looking at two important ratios, the thrust-to-weight ratio (T/W), the wing loading or ratio of weight-to-planform area (W/S). 2.24 Calculate the density altitude for an aircraft at an airport with a pressure altitude of 5,000 feet when the current temperature is 13 degrees C. 2.25 Using Table 2.1, calculate the dynamic pressure, q, at 8,000 feet density altitude and 250 knots TAS. As a flight instructor and aircraft enthusiast, I have long admired the . 6.23 Vy is also known as __________________. (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.). Adapted from Raymer, Daniel P. (1992). Or in some cases the power-to-weight ratio (P/W) is used instead of T/W. We would also need to look at these requirements and our design objectives. 3.6 Air passing over a cambered airfoil at 0o AOA yields, A higher velocity over the top of the wing compared to the bottom of the wing. }*vxqS?Vi5Li^E[NIW_~;O`"P?yz].O^7x%zGv!6ytG6)R=7?Y>zJ4L} +|l\ } It says that we need a higher thrust-to-weight ratio to climb than to fly straight and level. A light wave has wavelength 500nm500 \mathrm{~nm}500nm in vacuum. That's the actual angle of the slope of the straight line you drew on the graph. What other design objectives can be added to the constraint analysis plot to further define our design space? For example, lets look at stall. What is the arrow notation in the start of some lines in Vim? 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. 11.11 In most cases, an aircraft that has a high rate of descent on final approach should ____________. 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 Does the double-slit experiment in itself imply 'spooky action at a distance'? 13.21 As the weight of an aircraft decreases, the VA. 13.22 ______________ of the total lift is the centripetal force that causes radial acceleration. 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. 2.22 _____________________ results when the CAS has been corrected for compressibility effects. 3.20 The component of the aerodynamic force that is perpendicular to the relative wind is ________________. Power available is thrust multiplied by TAS. 5.18 The best engine-out glide ratio occurs at. 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. 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. a. If we assume a coordinated turn we find that once again the last two terms in the constraint analysis relationship go to zero since a coordinated turn is made at constant altitude and airspeed. 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. CC BY 4.0. 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. 10.1 Regarding takeoff performance, an increase in the aircraft weight will result in, 10.2 Takeoff thrust is primarily influenced by what factor(s), 10.3 An increase in density altitude has what effect on takeoff performance. 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. 3.23 The following are all examples of primary flight controls except _____________. 2.18 Density altitude is found by correcting _______________ for _______________. 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. 11.9 If in descending, gliding flight, a component of ________ acts in the same direction as thrust. 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? Sometimes this is called a "service ceiling" for jet powered aircraft. 10.18 If the ______________ is exceeded, the aircraft cannot be brought to stop in the remaining runway. With metric units for speed (meters per second), this is the case. Excess thrust is the difference between the total drag of the aircraft, and the thrust output of the powerplant. Tangent from 0, 0 to the curve yields point of max climb angle (maximum height for least distance traveled). From the spreadsheet, this climb angle can be read. 7.17 Changing the weight of an aircraft changes the ______________ much more than the ___________. 4.17 Laminar flow involves the rapid intermixing of the air levels over a wing. 4.19 Assume an aircraft with the CL-AOA curve of 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. The aircraft will experience structural damage or failure. Power required is the power needed to maintain straight and level flight, i.e., to overcome drag and to go fast enough to give enough lift to equal the weight. 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. It allows the aircraft to reach takeoff velocity at a lower groundspeed than for a no-wind condition. If we were to look at the relationships we found for any of these we could see how we might design an airplane to best accomplish the task at hand. Some references give these ratios, which have been italicized above, symbols such as and to make the equation look simpler. 4.20 An increase in CL(max)and a decrease in stall AOA will be noted when ___________. 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 Since your graph already shows the origin (0,0), you are almost done already! 7.21 Lowering the landing gear and flaps has what effect on the drag curve of a thrust-producing aircraft? 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 One that is fairly easy to deal with is turning. 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 __________. This makes sense when one realizes that, unless reverse thrust is used in the landing ground run, thrust does not play a major role in landing. 5.24 For a given aircraft wing, if the wing span remains the same but the wing area increases, the aspect ratio will ____________. Find the Rate of Climb. d. 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