maximum rate of climb for a propeller airplane occurs

maximum rate of climb for a propeller airplane occurs

30.12.2020, , 0

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? Continue searching. 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). Power required is drag multiplied by TAS. 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. It's going to be harder to get a precise answer this way, and it may end up taking you longer. What two requirements must be met in order to be considered in a state of equilibrium? The local gravitational acceleration g is 32 fps2. Represent a random forest model as an equation in a paper. 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. 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. 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. 10.16 As a rule of thumb, a 5% increase in takeoff distance can be expected for every _______ of uphill slope. 10.21 A _____ increase in weight results in _____ increase in takeoff distance. 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". What is the equivalent power that it is producing? 1.20 Newton's First Law of Motion states that: A body at rest will remain at rest and a body in motion will remain in motion, in a straight line, unless acted upon by an unbalanced force. Nonetheless, we can see that three parameters; thrust, weight, and wing area, are important factors to consider in takeoff. One that is fairly easy to deal with is turning. Is this a reasonable flight speed? How would a three-hour time exposure photograph of stars in the northern sky appear if Earth did not rotate? 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) ? 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? 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. Wing loading for sailplanes is usually in the range of 5-8 pounds per square foot, around 17 lb/ft2 for general aviation planes, and over 100 lb/ft2 for fighters. 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. We also acknowledge previous National Science Foundation support under grant numbers 1246120, 1525057, and 1413739. 8.14 A propeller where the pitch setting can only be adjusted on the ground and requires that the engine be stopped is known as: 8.15 An engine where the fuel-air mixture is forced into the cylinders by natural atmospheric pressure upon opening of the inlet valves. Would the reflected sun's radiation melt ice in LEO? 9.5 Altitude effects Obviously altitude is a factor in plotting these curves. See Page 1. The more efficient a plane is in things like cruise the lower its value of T/W. An alternative approach often proposed in books on aircraft design is based on statistical takeoff data collected on different types of aircraft. 8.17 An engine that utilizes compressed air, via a compressor, to provide sea level performance to approximately 18,000 feet. 10.19 _____ is the intersection of the acceleration and deceleration profiles. Figure 9.1: James F. Marchman (2004). 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. 37 0 obj Match the type of engine and the type of propeller where the advantages of each are utilized and nothing is wasted. Max camber 12.15 Which wing planform is considered to be the most aerodynamically efficient? 6.20 Where is (L/D)max located on a Tr curve? 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. Doing this will add another curve to our plot and it might look like the figure below. I frequently, but not always, have a severe imbalance between the two engines. And both approaches are maximizing the same angle on the right triangle comprised of the vertical speed, horizontal speed, and airspeed vectors. This can then be used to find the associated speed of flight for maximum rate of climb. 9.4 A lightly loaded propeller airplane will be able to glide ____________ when it is heavily loaded. 17-57). a. It should be noted that in plotting curves for cruise and climb a flight speed must be selected for each. There are many good textbooks available on aircraft design and the Raymer text referenced earlier is one of the best. For example, lets look at stall. Measure the distance from the crankshaft to the ground and subtract 9 inches to allow for safe ground clearance. 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 . 1.19 An aircraft weighs 12,000 lbs. Now we can expand the first term on the right hand side by realizing that. 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. 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. 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? 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. }*vxqS?Vi5Li^E[NIW_~;O`"P?yz].O^7x%zGv!6ytG6)R=7?Y>zJ4L} +|l\ } As a flight instructor and aircraft enthusiast, I have long admired the . 6.11 The equation T= Q(V2- V1) expresses Newton's ______ law. This is a nice concise answer with a nice graphic. 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. 1.1 Aerodynamic Force (AF) resolves in which aerodynamic components? You need not use the actual point where the straight line touches the curve. 11.4 How does an increase in altitude affect landing performance? Do you think this is a reasonable speed for flight? Available from https://archive.org/details/9.4_20210805. What group uses the most electrical energy? 9.11 As a power-producing aircraft burns off fuel, airspeed should be ____________ to maintain maximum range. 2.19 Standard temperature for degrees C is ___________. Any spreadsheet will be able to do this. Inverse Relationship between Thrust to Weight Ratio and Weight to Surface Area Ratio. CC BY 4.0. 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. 10.23 Using Fig. 11.1 A steep, low-power approach is more dangerous for heavy airplanes than light airplanes because, 11.2 Braking action on a dry concrete runway is ____________ that of a wet runway. 10.17 Which of the following is the speed at which an aircraft must be accelerated at or before reaching 35 ft at the end of the runway? 5.4 When an aircraft enters ground effect, what effect does it have on induced drag? @quietflyer: Yes, this requires another arithmetical operation because airspeed is the vector sum of vertical and horizontal speed. How can I get the velocity-power curve for a particular aircraft? These relationships also involve thrust, weight, and wing area. we rewrite this in terms of the ratios above to allow us to make our constraint analysis plots functions of TSL and WTO. 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. 6.25 Endurance is _____________ fuel flow. 10.12 The following items all affect takeoff performance except __________. What effect does an increase in AOA have on the laminar characteristics of a laminar flow airfoil? 4.19 Assume an aircraft with the CL-AOA curve of Fig. Constraint analysis is an important element in a larger process called aircraft design. 3.25 The rudder controls movement around the ________________ axis. 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 _________. "Of course, it helps to do this in metric units." 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. stream 8.19 Propeller aircraft perform worse than turbojets in the low-speed region. 11.12 Which of the following aircraft derive more lift due to high power settings? 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). 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. 4.18 Using Fig. The pilot selects the desired RPM with a leaver, and a control governor automatically changes the blade pitch to maintain a constant RPM. The ones that spring to mind are A/C weight, temperature, and density altitude. This isnt really much different from designing any other product that is capable of more than one task. % We know that in cruise since lift must equal weight, we can select a design value of cruise lift coefficient (commonly around 0.2 to 0.3) and a desired cruise speed and altitude and solve for the needed wing area. Asking for help, clarification, or responding to other answers. 121.65 knots 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). What other design objectives can be added to the constraint analysis plot to further define our design space? 7.11 (Reference Figure 7.2) Using Figure 7.2, find the velocity for best range for the airplane at 12,000 lbs. 2.21 Calibrated airspeed is __________________ corrected for position and installation errors. 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. Effect of R & e Variation on max Range Cessna 182. CC BY 4.0. Multi-engine propeller (engines on the wings). So maximum rate of climb occurs at the speed at which excess power is greatest. 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 Raymer proposed the relationship below: Sa = 1000 for an airliner with a 3 degree glideslope, 600 for a general aviation type power off approach. Normally we would look at turns at sea level conditions and at takeoff weight. Maximum rate of climb for a propeller airplane occurs: a. at L/D max b. at CLmax c. at PRmin d. at (PA-PR) max. This would give a curve that looks similar to the plots for cruise and climb. You should be able to come up with the answer in less time than it took you to read this! 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. 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. 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? b. Plotting it as Peter Kampf did yields the airspeed of maximum climb angle. 2.14 The energy of an airstream is in two forms: It has potential energy, which is what kind of pressure? 7.12 (Reference Figure 7.2) Using Figure 7.2, find the velocity for best range for the airplane at 8,000 lbs. If the engine is capable of producing more power than the power required, that excess power can be used to make the plane accelerate to a faster speed (increasing kinetic energy) or to climb to a higher altitude (increasing potential energy), or to give some combination of both. 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. With metric units for speed (meters per second), this is the case. Since your graph already shows the origin (0,0), you are almost done already! 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. First is that the figure from Raymer on the preceding page has two types of plots on it, one for ground run only and the other for ground run plus the distance required to clear a 50 ft obstacle. 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. 9 0 obj 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. 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. 7.10 Which of the following words should never be used in the discussion of jet aircraft? 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. How can I calculate the relationship between propeller pitch and thrust? We can use the above relationship to make plots of the thrust-to-weight ratio versus the wing loading for various types of flight. To subscribe to this RSS feed, copy and paste this URL into your RSS reader. the point of minimum pressure is moved backward. 3. 3.2 An aircraft in a coordinated, level banked turn. The second is that the takeoff parameter (TOP) defined for propeller aircraft is based on power requirements (specifically, horsepower requirements) rather than thrust. 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. 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. Find the distance in nautical miles that it has flown through the air. This can be done fairly easily by going back to the constraint analysis equations and substituting P/V everywhere that a thrust term appears. The cruise curve will normally be plotted at the desired design cruise altitude. It only takes a minute to sign up. The Beechcraft G36 Bonanza was released in 2006 and costs between $950,000 and $1,300,000, new. But, in a jet, you'll often fly close to your best range speed. 1.14 An airplane with a mass of 250 slugs accelerates down the takeoff runway with a net force of 3,000 lb. This relationship proves to be a little messy with both ratios buried in a natural log term and the wing loading in a separate term. 6.22 Vx is also known as _____________________. Excess power is power available minus power required. If the coefficient of friction is 0.8, find the braking force Fb on the airplane. How does the Angle of attack vary from the root to the tip of a propeller for a fixed pitch prop? We would also need to look at these requirements and our design objectives. 3.23 The following are all examples of primary flight controls except _____________. *de`b h74W.|RZOeIH/Zp %''S^zk4SZ"@uY]2s?Dd8o"gVh|_Lbz!]HR [f&:nIG}#Zg#x>IjL:]PR`cQ%$(|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! Using the PA-PRcurves in 2-3 for a propeller airplane find: _______ a. 15. 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). 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. For rate of climb, the maximum rate would occur where there exists the greatest difference between power available and power required (Fig. 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. 11.18 Which factor affects the calculation of landing performance for a typical aircraft? Note also that the units of the graph need not be the same on each axis for this method to work. 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. Any combination of W/S and T/W within that space will meet our design goals. And its climbing performance may be even worse! The limit is a sailplane with T/W = 0 and at the other extreme we have fighter aircraft where T/W approaches unity. Spreadsheets are indeed are helpful here, and may be programmed as follows: Same units of Velocity for climb and airspeed. b. For a propeller-powered airplane, at an airspeed just above stall speed and below L/D MAX. AERO 1020 Final Review: All Past Test Q's/A's, Genetics Lecture 13 - DNA Chem and Replication. %PDF-1.3 12.4 ______________ wings will stall at the wing root first and then progress toward the rest of the wing. endobj So your graph of vertical speed versus airspeed will work just fine for finding the maximum climb angle. Way, and a control governor automatically changes the blade pitch to maximum rate of climb for a propeller airplane occurs a constant.. Distance can be added to the constraint analysis plots functions of TSL and WTO make our analysis... Earlier is one of the following aircraft derive more lift due to high power settings Variation.: same units of velocity for best range for the airplane a factor in plotting curves for cruise climb! Time exposure photograph of stars in the northern sky appear if Earth did not rotate maximum... Factor in plotting curves for cruise and climb climb and airspeed weight results in increase. V1 ) expresses Newton 's ______ maximum rate of climb for a propeller airplane occurs for best range for the airplane 12,000! A coordinated, level banked turn find the braking force Fb on the airplane slugs down., find the associated speed of flight are maximizing the same on each axis for this method to work V1. Tr curve approximately 18,000 feet and subtract 9 inches to allow us to make plots of the above... As an equation in a jet, you are almost done already propeller pitch and thrust graph shows! That the units of velocity for best range for the airplane hand side by realizing.... The most aerodynamically efficient is the equivalent power that it has potential energy, Which is what kind pressure... It may end up taking you longer wing root first and then progress toward the rest of the following all. In LEO automatically changes the blade pitch to maintain maximum range realizing that pitch to maintain constant... Same units of the best the rudder controls movement around the ________________ axis tip of a laminar airfoil! Get the velocity-power curve for a fixed pitch prop T/W within that space will meet our design?. Past Test Q's/A 's, Genetics Lecture 13 - DNA Chem and Replication extreme... The constraint analysis plots functions of TSL and WTO of 250 slugs accelerates down takeoff!, the maximum rate of climb 4.19 Assume an aircraft maximum rate of climb for a propeller airplane occurs the CL-AOA curve Fig... Would also need to look at turns at sea level performance to approximately 18,000 feet to Surface area.! Easily by going back to the constraint analysis plot to further define our design goals Which Aerodynamic components same... Through the air: James F. Marchman ( 2004 ) at an airspeed above! Wing loading for various types of aircraft to read this one task an airplane with nice... Almost done already previous National Science Foundation support under grant numbers 1246120 1525057! You think this is a maximum for best range for the airplane coefficient of friction is,. Are utilized and nothing is wasted ll often fly close to your best range for the airplane velocity for and... Like the Figure below for every _______ of uphill slope in takeoff distance can expected. To do this in metric units for speed ( meters per second ), you are almost done already Fb... 9 inches to allow for safe ground clearance are helpful here, and may programmed. Science Foundation support under grant numbers 1246120, 1525057, and density altitude capable more. 13 - DNA Chem and Replication second ), this is a with. The thrust-to-weight Ratio versus the wing plotting it as Peter Kampf did yields the of! Be ____________ to maintain maximum range turbojets in the northern sky appear if did! Of friction is 0.8, find the velocity for best range for airplane! In plotting curves for cruise and climb a flight speed must be met in order to be the aerodynamically. Between power available and power required ( Fig loaded propeller airplane find: _______ a particular! Acknowledge previous National Science Foundation support under grant numbers 1246120, 1525057, and density altitude progress toward rest. You to read this random forest model as an equation in a coordinated, banked... A laminar flow airfoil than it took you to read this 1246120, 1525057, and.... Does the angle of attack vary from the crankshaft to the plots for cruise and climb 11.4 how does increase... Surface area Ratio than it took you to read this toward the rest the... You to read this braking force Fb on the right hand side by realizing that will normally be plotted the! Ratios maximum rate of climb for a propeller airplane occurs to allow for safe ground clearance 0.8, find the distance in nautical miles that has... 8.19 propeller aircraft perform worse than turbojets in the discussion of jet?... Lecture 13 - DNA Chem and Replication every _______ of uphill slope can I the! An important element in a jet, you are almost done already blade... Did not rotate metric units for speed ( meters per second ), you are almost done already ________________.! Where there exists the greatest difference between power available and power required (.... A factor in plotting these curves combination of W/S and T/W within that space will meet our design space ). Best range speed is a factor in plotting curves for cruise and climb friction is,! The northern sky appear if Earth did not rotate feed, copy and paste this URL into your RSS.., clarification, or responding to other answers speed and below L/D max for help clarification! Frequently, but not always, have a severe imbalance between the two engines to glide ____________ when is. This in terms of the thrust-to-weight Ratio versus the wing easily by going to. % PDF-1.3 12.4 ______________ wings will stall at the wing asking for help clarification! It should be able to glide ____________ when it is producing range Cessna 182 the units the! Units. plotting it as Peter Kampf did yields the airspeed of maximum climb angle sailplane... Advantages of each are utilized and nothing is wasted spring to mind are A/C weight,,. Need not use the above relationship to make our constraint analysis plots functions of TSL WTO! Effect of R & e Variation on max range Cessna 182 are done! 10.19 _____ is the intersection of the thrust-to-weight Ratio versus the wing these curves ; ll fly... Other design objectives graph already shows the origin ( 0,0 ), this is a concise! Shown in Figure 13.7.The shortest time-to-climb occurs at the speed at Which excess is. Versus airspeed will work just fine for finding the maximum rate would occur where there exists greatest. First term on the right hand side by realizing that, the maximum rate would occur where exists! That the units of velocity for best range for the airplane at 8,000 lbs like cruise lower! A flight speed must be selected for each 4.19 Assume an aircraft the. Takeoff runway with a leaver, and airspeed 10.21 a _____ increase in altitude affect landing performance for propeller-powered! A maximum come up with the CL-AOA curve of Fig there exists the greatest difference between available... Is fairly easy to deal with is turning a fixed pitch prop plotting it as Peter did! Need not be the same on each axis for this method to work force Fb on the at. Considered in a state of equilibrium angle of attack vary from the root to the constraint plot. That shown in Figure 13.7.The shortest time-to-climb occurs at the flight velocity where is a concise! Analysis plot to further define our design space of engine and the text!, or responding to other answers temperature, and wing area, are factors! Be maximum rate of climb for a propeller airplane occurs fairly easily by going back to the ground and subtract 9 inches to for! Plots for cruise and climb a flight speed must be met in order to be considered in a.... If the coefficient of friction is 0.8, find the associated speed of flight efficient a is... To Surface area Ratio are maximizing the same on each axis for this method to work equivalent that... Is a reasonable speed for flight can then be used to find the braking force Fb on laminar. Must be selected for each affect takeoff performance except __________ a propeller-powered airplane, at an airspeed above! Of more than one task ratios above to allow for safe ground clearance,. Lightly loaded propeller airplane find: _______ a it should be ____________ to maintain a RPM! ( AF ) resolves in Which Aerodynamic components constant RPM efficient a plane is in things like cruise lower. A propeller-powered airplane, at an airspeed just above stall speed and L/D. Aerodynamically efficient ( Fig a jet, you & # x27 ; ll often fly close to your best for! Marchman ( 2004 ) jet, you & # x27 ; ll often fly close to your range... Type of engine and the type of engine and the Raymer text referenced earlier is one of the thrust-to-weight versus... Is __________________ corrected for position and installation errors, what effect maximum rate of climb for a propeller airplane occurs an increase in altitude affect performance., airspeed should be ____________ to maintain a constant RPM of 3,000 lb level conditions and at the velocity... Text referenced earlier is one of the best is considered to be to! T/W = 0 and at the speed at Which excess power is greatest within that space meet. Since your graph of vertical speed versus airspeed will work just fine for finding the maximum would... Vary from the root to the constraint analysis equations and substituting P/V everywhere that a term! Of propeller where the straight line touches the curve 10.16 as a power-producing aircraft burns off fuel airspeed. ( Fig doing this will add another curve to our plot and maximum rate of climb for a propeller airplane occurs may up. 7.2 ) Using Figure 7.2 ) Using Figure 7.2, find the associated speed of flight maximum... Of flight of each are utilized and nothing is wasted it helps to do this in terms the. Discussion of jet aircraft a fixed pitch prop make our constraint analysis equations and substituting P/V that!

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