maximum rate of climb for a propeller airplane occursmaximum rate of climb for a propeller airplane occurs

From the spreadsheet, this climb angle can be read. I've been asked to find the maximum climb angle of a propeller driven aircraft from the graph of vertical velocity against airspeed: All you need to do is to plot vertical versus horizontal speed using the same scale on both axes. Do German ministers decide themselves how to vote in EU decisions or do they have to follow a government line? Then the solution is the point with the steepest angle from the origin of the graph. The cruise curve will normally be plotted at the desired design cruise altitude. What would happen if an airplane climbed beyond its preset cruise altitude that the pilot set in the pressurization system? 1.18 An aircraft's turbojet engine produces 10,000 lbs of thrust at 200 knots true airspeed. Best angle of climb (BAOC) airspeed for an airplane is the speed at which the maximum excess thrust is available. This can then be used to find the associated speed of flight for maximum rate of climb. How to find trim condition of a sectional airfoil without knowing the angle of attack? 6.22 Vx is also known as _____________________. 2.14 The energy of an airstream is in two forms: It has potential energy, which is what kind of pressure? A head wind is encountered. 4.20 An increase in CL(max)and a decrease in stall AOA will be noted when ___________. 11.9 If in descending, gliding flight, a component of ________ acts in the same direction as thrust. These two ratios are tied together in aircraft performance through the same power relationship that we looked at when we first examined climb and glide. 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. We need to keep in mind that there are limits to that cruise speed. 2. chord line 9.5 Altitude effects Obviously altitude is a factor in plotting these curves. What altitude gives the best range for the C-182? 9.4 A lightly loaded propeller airplane will be able to glide ____________ when it is heavily loaded. nautical miles per hour) and vertical speed (feet per minute). We could put these limits on the same plot if we wish. Note also that the units of the graph need not be the same on each axis for this method to work. 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. These included takeoff and landing, turns, straight and level flight in cruise, and climb. Available from https://archive.org/details/hw-9_20210805. 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 __________. It usually is restricted to either the takeoff setting or the cruise setting. Using the PA-PRcurves in 2-3 for a propeller airplane find: _______ a. 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. To land in a short distance we might want to also design a plane with a large wing and high maximum lift coefficient but now the thrust isnt as important as the amount of braking friction available unless it is reverse thrust that we are talking about. Calculate (or find in Table 2.1) the Density Ratio: 2.12 An airplane is operating from an airfield that has a barometric pressure of 28.86 in. Did the residents of Aneyoshi survive the 2011 tsunami thanks to the warnings of a stone marker? 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. 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. 12.7 An airplane is making a final approach for a landing and encounters a horizontal wind shear. This can be determined from the power performance information studied in the last chapter. Cruising at V Y would be a slow way to fly. 3.13 thru 3.17 Reference Figure 2. 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 __________. The aircraft will experience structural damage or failure. 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. And a big wing area gives us high drag along with high lift. 8.9 Which horsepower is measured at the propeller shaft and experiences gearing losses in reducing engine rpm to propeller rpm? The pilot selects the desired RPM with a leaver, and a control governor automatically changes the blade pitch to maintain a constant RPM. 4.10 and the following data: W = 25,000 lb, wing area S = 300 ft2,CL(max), sea level, standard day. Arc Sine ratio of Vv/Airspeed = climb angle We can use the above relationship to make plots of the thrust-to-weight ratio versus the wing loading for various types of flight. Figure 6.1: Finding Velocity for Maximum Range But, in a jet, you'll often fly close to your best range speed. Rate of Climb formula. It says that we need a higher thrust-to-weight ratio to climb than to fly straight and level. Best Rate of Climb 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. One that is fairly easy to deal with is turning. Legal. With metric units for speed (meters per second), this is the case. 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. 10.22 Takeoff acceleration through the air mass is not reduced by a headwind. That portion of total drag associated with the production of lift. How is maximum rate of climb defined in aircraft specifications? What is the mass of the airplane? Highest point on the curve yields maximum climb rate (obviously). How does wind affect the airspeed that I should fly for maximum range in an airplane? Nonetheless, we can see that three parameters; thrust, weight, and wing area, are important factors to consider in takeoff. Just as an aside, the vertical speed can't be higher than the airspeed, so it's not even. Accessibility StatementFor more information contact us atinfo@libretexts.orgor check out our status page at https://status.libretexts.org. When I started the engines this time I found for left and right: RPM 90% 52% ITT 735 735 N1 63 63 N2 90 52 FF 20 49 PSI 83 77 If the coefficient of friction is 0.8, find the braking force Fb on the airplane. The number of distinct words in a sentence. 7.13 (Reference Figure 7.2) Using Figure 7.2, find the velocity for maximum endurance for the airplane at 12,000 lbs. In cruise where lift = weight and thrust = drag, T/W = 1 / [L/D], meaning that the high value of L/D that is needed for a large range goes hand in hand with a low thrust-to-weight ratio. 12.11 What two things are necessary for an aircraft to enter a spin? Note here that the weight in the equation is the landing weight but that in calculating this landing distance for design purposes the takeoff weight is usually used for general aviation aircraft and trainers and is assumed to be 0.85 times the takeoff weight for jet transports. 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. In this manner, we can find values of weight, wing area, and thrust that match our desired cruise capability. 9.11 As a power-producing aircraft burns off fuel, airspeed should be ____________ to maintain maximum range. Note that with a curve shaped like the one you've included in the question, the precision of your final answer is not going to be extremely sensitive to how well you are able to determine the exact point where the line from the origin is tangent to the graph. Find the acceleration of the airplane. To takeoff in a short distance we might want a high maximum lift coefficient to get a low takeoff speed, a large wing area to give a lot of lift at low speed, and a lot of thrust to accelerate to takeoff distance in as short a ground run as possible. Fw5| } These relationships also involve thrust, weight, and wing area. 3.20 The component of the aerodynamic force that is perpendicular to the relative wind is ________________. 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. Hg and a runway temperature of 20C. Continue searching. 10.24 When taking off in a multi-engine aircraft, VRis usually less than V1. 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. 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? Match the airfoil part name to the table number. 5.7 Streamlining the fuselage, engine nacelles, pods, and external stores help reduce this type of drag. 9.7 For Jet and Propeller aircraft, the two things shared at L/Dmax are the Maximum Engine-out Glide speed and Maximum range. The maximum angle of climb occurs where there is the greatest difference between the thrust available and the thrust required. 2.20 The total pressure of the airstream is the sum of the static pressure and the __________________. pressure altitude / nonstandard temperature conditions. Any combination of W/S and T/W within that space will meet our design goals. 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. rev2023.3.1.43268. b. In straight and level flight we know: And if we simply combine these two equations we will get the same relationship we plotted above. 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? Propeller aircraft are more efficient than jet aircraft because: They process more air and don't accelerate it as much. 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. -- why? 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. 8 0 obj While you are at it, just the sake of curiosity you might want to also calculate the arctangent of (vertical speed / airspeed) for the same data point. Spreadsheets are indeed are helpful here, and may be programmed as follows: Same units of Velocity for climb and airspeed. 7.16 With a typical drag curve, how many times does the thrust available line intersect the thrust required curve? 9.1 The power-required curves for an increase in altitude show that the, Pr increases by the same amount as the velocity, 9.2 A propeller aircraft in the dirty condition shows that the Pr moves up and to the left over the clean configuration. Figure 9.7: Effect of R & e Variation on max Range Cessna 182. Raymer proposed the relationship below: Sa = 1000 for an airliner with a 3 degree glideslope, 600 for a general aviation type power off approach. In other words this equation is really an energy balance. How can I find the maximum climb angle of a propeller driven aircraft from a graph of vertical velocity against airspeed? Modern propellers on larger aircraft would always be equipped with automatic feathering provisions. 11.15 Foot brakes should be utilized before the nosewheel touches the ground during landing. The type of aircraft, airspeed, or other factors have no influence on the load factor. 13.3 (Reference Figure 5.4) What speed is indicated at point A? Effect of R & e Variation on max Range Cessna 182. CC BY 4.0. 3.24 The most common high-lift devices used on aircraft are _______________. 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). Hg and a runway temperature of 20C. 7.21 Lowering the landing gear and flaps has what effect on the drag curve of a thrust-producing aircraft? 9.14 As the altitude for a given aircraft increases, the VX will ___________ and the VY will ___________. What altitude gives the best endurance for the C-182? 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? The steepest climb angle occurs when the ratio of vertical speed to horizontal speed is maximized. 5.18 The best engine-out glide ratio occurs at. 13.8 (Reference Figure 5.4) An aircraft flying at 200 knots can pull how many G's before stalling the aircraft? 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 question is; is there some way to analyze all of these at the same time and come to a decision about optimum or reasonable compromise values of weight, wing area, and engine thrust without having to go through iteration after iteration? The other parameter, W/S, or wing loading, is also generally low for sailplanes and high for fighters. Doing this will add another curve to our plot and it might look like the figure below. Has the term "coup" been used for changes in the legal system made by the parliament? <> As an example, most piston engine aircraft will cruise at an engine power setting somewhere between 55% and 75% of maximum engine power. The constraint analysis may be performed several times, looking at the effects of varying things like wing aspect ratio on the outcome. 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. Still looking for something? 2245 The method normally used is called constraint analysis. How to properly visualize the change of variance of a bivariate Gaussian distribution cut sliced along a fixed variable? Time to Climb Between Two Altitudes And this can be written [W/S] = Vstall2CLmax, On the plot above this would be a vertical line, looking something like this. 10.7 "The speed to which the airplane can be accelerated, lose an engine, and then either continue the takeoff with the remaining engine or stop, in the same total runway distance" is the definition for, 10.8 "The total length of runway required to accelerate on all engines to critical engine failure speed, experience an engine failure, and then continue to takeoff or stop" is the definition for, 10.9 "The maximum speed that the aircraft can obtain under normal acceleration and then stop in the available runway" is the definition for, 10.10 "The minimum indicated airspeed at which an engine failure can be experienced and the takeoff safely continued. The second is that the takeoff parameter (TOP) defined for propeller aircraft is based on power requirements (specifically, horsepower requirements) rather than thrust. For climb at constant speed dV/dt = 0 and our equation becomes, T/W = (qCD0)/(W/S) + (kn2/q)(W/S) + (1/V)dh/dt. The climb curve would probably be plotted at sea level conditions since that is where the target maximum rate of climb is normally specified. Finding this value of drag would set the thrust we need for cruise. 12.3 ______________ wings will stall at the wing tips first and then progress toward the rest of the wing. This process would become even more cumbersome as we added other design objectives such as a minimum turning radius or a minimum stall speed. 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. 11.14 During a landing in a tricycle gear aircraft, ________ braking is used before _________. Represent a random forest model as an equation in a paper. 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? If we want an airplane that only does one thing well we need only look at that one thing. Would the reflected sun's radiation melt ice in LEO? So maximum rate of climb occurs at the speed at which excess power is greatest. That's the actual angle of the slope of the straight line you drew on the graph. Naturally, for this calculation you'll need to use the same units for both values-- a conversion may be necessary. I've made the recommended changes and have decent reverse thrust. endobj 3.25 The rudder controls movement around the ________________ axis. 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. Hg and a runway temperature of 20C. The ones that spring to mind are A/C weight, temperature, and density altitude. 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. 4.15 A thicker airfoil results in what change to AOA? How does the Angle of attack vary from the root to the tip of a propeller for a fixed pitch prop? Does an airfoil drag coefficient takes parasite drag into account? 8.13 A propeller where the blade pitch setting is either hydraulically or electrically controlled. 2.2 For temperatures to be used in calculating the effects on performance, the appropriate absolute scale must be used. 6.17 Maximum endurance will permit your aircraft to obtain the best distance for the fuel consumed. These two ratios are both very reflective of the design philosophy and objectives of any particular airplane. 12.4 ______________ wings will stall at the wing root first and then progress toward the rest of the wing. a. 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. And both approaches are maximizing the same angle on the right triangle comprised of the vertical speed, horizontal speed, and airspeed vectors. The desire for minimum thrust is obvious, based on the need to minimize fuel consumption and engine cost. It can tell us how much speed we can gain by descending to a lower altitude, converting potential energy to kinetic energy, or how we can perhaps climb above the static ceiling of the aircraft by converting excess speed (kinetic energy) into extra altitude (potential energy). 11.3 How does a weight increase affect landing performance? In this final plot the space above the climb and takeoff curves and to the left of the landing line is our acceptable design space. Match the type of engine and the type of propeller where the advantages of each are utilized and nothing is wasted. we rewrite this in terms of the ratios above to allow us to make our constraint analysis plots functions of TSL and WTO. 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). 1.11 Equilibrium is defined as "a state of balance or equality between opposing forces." So no re-plotting is needed, just get out your ruler and start drawing. Which gives the best endurance? See Page 1. The formula is ROC in FPM = ExcessHP*33,000*Propeller efficiency divided by All up Mass in LBS. 13. We also acknowledge previous National Science Foundation support under grant numbers 1246120, 1525057, and 1413739. Maximum excess thrust occurs: For a jet-powered airplane, at approximately the maximum lift/drag ratio (L/D MAX). 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. Power required to overcome induced drag varies, Power required to overcome parasite drag varies, Maximum rate of climb for a propeller airplane occurs. 3.2 An aircraft in a coordinated, level banked turn. 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? By clicking Accept all cookies, you agree Stack Exchange can store cookies on your device and disclose information in accordance with our Cookie Policy. 10.1, what is the minimum takeoff distance required to climb over a 50 ft obstacle, for the given aircraft with the following conditions: 10C OAT, PA 2000 ft, weight 2700 lb., 10-kt headwind. 7.10 Which of the following words should never be used in the discussion of jet aircraft? % 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 . What is the wavelength of this light as it travels through water (nwater=1.33)\left(n_{\text {water }}=1.33\right)(nwater=1.33) ? 11.19 Maximum glide distance is achieved only at a maximum glide angle. 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. 3.1 The mean camber line can be defined as: A line drawn halfway between the upper surface and the lower surface. 10.23 Using Fig. Available from https://archive.org/details/9.4_20210805. This addition to the plot tells us the obvious in a way. 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. 9.10 As a power-producing aircraft burns off fuel, ROC will ___________ for a given velocity. 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. 11.18 Which factor affects the calculation of landing performance for a typical aircraft? Adapted from Raymer, Daniel P. (1992). , Does an airfoil drag coefficient takes parasite drag into account? 3. mean camber line 1. 0.6 How will an uphill slope affect takeoff performance? 5.4 When an aircraft enters ground effect, what effect does it have on induced drag? 5.25 Parasite drag can be said to ____________. The figure below (Raymer, 1992) is based on a method commonly used in industry. Substituting this for drag in the equation and dividing the entire equation by V we can get: (T/W) = [(CD0 + kCL2) V2S) /W] + (1/V)dh/dt + (1/g)(dV/dt). + (kn2/q)(WTO/S)(Walt/WTO) + (1/V)dh/dt + (1/g)dV/dt} . Plotting it as Peter Kampf did yields the airspeed of maximum climb angle. Copyright 2023 CFI Notebook, All rights reserved. Find the Drift Angle. The greatest danger(s) is that. a. 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. To subscribe to this RSS feed, copy and paste this URL into your RSS reader. 3.21 The point on the chord line where the aerodynamic force acts is the _____________. stream 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. How would a three-hour time exposure photograph of stars in the northern sky appear if Earth did not rotate? 8.17 An engine that utilizes compressed air, via a compressor, to provide sea level performance to approximately 18,000 feet. 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 c. By how many fringes will this water layer shift the interference pattern? 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. TK. 6.15 Which one of the following items does not occur at (L/D)max for a jet aircraft? >ZWCWkW 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. This isnt really much different from designing any other product that is capable of more than one task. 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. Suppose that a 1.0-mm-thick layer of water is inserted into one arm of a Michelson interferometer. 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? 12.6 The best way to control airspeed is with the ___________, while the best way to control altitude/descent rate is with the ____________. 7.20 When a pilot lowers the landing gear, _______________ is increased. For propeller aircraft - Maximum angle of climb occurs at the Vfor which maximum excess thrust occurs Maximum climb angle (which is used to clear obstacles on takeoff) occurs at a velocity < V min TR Rate of Climb R/C For a given altitude - For any type of airplane, excess power determines R/C - Induced drag changes P R P C P - = W R . Of course there are limits to be considered. Looking again at the aircraft in Homework 8 with some additional information: 1. 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. 6.21 The lowest values of ct occur between 95 and 100% rpm. Partner is not responding when their writing is needed in European project application. 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. At 75% power, its Continental IO-550B engine burns 12 gph and the Bonanza G36 flies at 141 knots. What group uses the most electrical energy? 1759 The limit is a sailplane with T/W = 0 and at the other extreme we have fighter aircraft where T/W approaches unity. Do you think this is a reasonable speed for flight? 4.10 in your textbook, what is your AOA if the CL is .6 for a symmetrical airfoil? 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? We would also need to look at these requirements and our design objectives. 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 7.24 Increased weight has what effect on rate of climb? 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. @quietflyer: Yes, this requires another arithmetical operation because airspeed is the vector sum of vertical and horizontal speed. 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 ________________? 4.19 Assume an aircraft with the CL-AOA curve of Fig. 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. xYr7 _+(DL/HHMl>K miD%D./3QgBNgl<=Had5>fzhIQ6?|6]ot@{y And they may be different still in climb. CC BY 4.0. MathJax reference. This presents somewhat of a problem since we are plotting the relationships in terms of thrust and weight and thrust is a function of altitude while weight is undoubtedly less in cruise than at takeoff and initial climb-out. 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. Raymer also suggests multiplying the first term on the right in the distance equation above by 0.66 if thrust reversers are to be used and by 1.67 when accounting for the safety margin required for commercial aircraft operating under FAR part 25.

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