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. For example, if the hub-to-ground measurement is 45 inches, subtracting 9 inches will leave an effective radius of 36 inches. Note that the thrust ratio above is normally just the ratio of density since it is normally assumed that. 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. , Does an airfoil drag coefficient takes parasite drag into account? 11.14 During a landing in a tricycle gear aircraft, ________ braking is used before _________. Stall Cutoff for cap W over cap S values. CC BY 4.0. 9.5 To obtain maximum glide distance, a heavily loaded airplane must be flown at a higher airspeed than if it is lightly loaded, 9.6 The increase in the Pr curves for a weight increase is greater at low speeds than at high speeds because the increase in. 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. The climb angle will be the arcsine of (vertical speed / airspeed). The desire for minimum thrust is obvious, based on the need to minimize fuel consumption and engine cost. % Match the type of engine and the type of propeller where the advantages of each are utilized and nothing is wasted. The plot that will be different from all of these is that for takeoff. For a turbojet aircraft with a drag equation described by: C D = C D 0 + K C L 2. with C D 0 = 0.012, and K = 0.035, a wing area of 70 m 2, a weight of 120.000 kN, and a maximum lift coefficient of 1.900, capable of producing a thrust of 120.000 kN at a given altitude, the climb rate and angles can be taken from the . Plotting it as Peter Kampf did yields the airspeed of maximum climb angle. 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. Hg and a runway temperature of 20C. MathJax reference. 8.21 For a power-producing aircraft, maximum climb angle is found. b. 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. 4.10 in your textbook, what is your AOA if the CL is .6 for a symmetrical airfoil? AERO 1020 Final Review: All Past Test Q's/A's, Genetics Lecture 13 - DNA Chem and Replication. Figure 6.1: Finding Velocity for Maximum Range Note that this equation does not represent an actual aircraft polar; it refers to the initial climb-out after takeoff. Aircraft Design: A Conceptual Approach, AIAA, Washington, DC. 13.1 The G's required for an aircraft to maintain altitude in a coordinated turn are determined by the bank angle alone. 6.25 Endurance is _____________ fuel flow. 7.12 (Reference Figure 7.2) Using Figure 7.2, find the velocity for best range for the airplane at 8,000 lbs. Tangent from 0, 0 to the curve yields point of max climb angle (maximum height for least distance traveled). 7.6 The minimum drag for a jet airplane does not vary with altitude. 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. 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. 10.19 _____ is the intersection of the acceleration and deceleration profiles. 4.16 Laminar airflow over a smooth airfoil like a wing begins at the _____________. 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. 5.19 An aircraft will begin to experience ground effect_____________ above the surface. This limits your maximum allowable propeller diameter to 72 inches (36" x 2" = 72"). Legal. 8 0 obj 1.12 Solve for left and right moment arm and fulcrum force against the seesaw (respectively) (See Figure 1_Test 1): 1.13 An airplane weighs 8,000 lb. 9.9 For a power-producing aircraft, an increase in weight results in a decrease of Vmax. 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. 13.15 (Reference Figure 14.10) How many degrees of bank are required for a standard rate turn (3 degrees per second) at 420 knots? Still looking for something? >ZWCWkW 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). Note also that the units of the graph need not be the same on each axis for this method to work. As an example, most piston engine aircraft will cruise at an engine power setting somewhere between 55% and 75% of maximum engine power. The more efficient a plane is in things like cruise the lower its value of T/W. 12.16 All speeds below the speed for minimum drag are said to be in the _________. It usually is restricted to either the takeoff setting or the cruise setting. Hg and a runway temperature of 20C. 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. Find the Rate of Climb. 11.3 How does a weight increase affect landing performance? Of course, it helps to do this in metric units. 2.21 Calibrated airspeed is __________________ corrected for position and installation errors. Match the airfoil part name to the table number. Constraint analysis is an important element in a larger process called aircraft design. 3.21 The point on the chord line where the aerodynamic force acts is the _____________. 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. One way to find the maximum ratio of y to x on any graph of y versus x is to extend the axes of the graph to include the origin (0,0) and just run a line from the origin to any point on the curve and find the point on the curve where the slope of this line is the steepest, just as was done in these related answers: What is the typical climb angle The Beechcraft G36 Bonanza was released in 2006 and costs between $950,000 and $1,300,000, new. Hg and a runway temperature of 20C. We would also need to look at these requirements and our design objectives. 11.10 The minimum glide angle also corresponds to ____________________. 10.4 What effect does a headwind have on takeoff performance? There are many good textbooks available on aircraft design and the Raymer text referenced earlier is one of the best. 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). 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. 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. 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. 8.23 For a power producer, unaccelerated maximum velocity will occur at the intersection of the full power-available curve and the ________________. Of course there are limits to be considered. 7.24 Increased weight has what effect on rate of climb? In straight and level flight we know: And if we simply combine these two equations we will get the same relationship we plotted above. Figure 9.3: James F. Marchman (2004). As a flight instructor and aircraft enthusiast, I have long admired the . The formula is derived from the power available and power . Aviation Stack Exchange is a question and answer site for aircraft pilots, mechanics, and enthusiasts. 8.10 In order to maximize range on a propeller-driven airplane at high altitude, true airspeed should be _____________. 6.16 Which one of the following items does not occur at (L/D)max for a jet aircraft? 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. 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). 12.24 For an aircraft to spin, both wings have to be stalled. 7.17 Changing the weight of an aircraft changes the ______________ much more than the ___________. 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. 1.11 Equilibrium is defined as "a state of balance or equality between opposing forces." In this manner, we can find values of weight, wing area, and thrust that match our desired cruise capability. Note also that the data point you use for your trig calculation of climb angle can come from anywhere along the straight line you've drawn from the origin of the graph. Figure 9.2: James F. Marchman (2004). Finding this value of drag would set the thrust we need for cruise. 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. This is a nice concise answer with a nice graphic. The value of T/W will depend on the desired flight speed, the wing area, and the efficiency (L/D) of the wing. In other words this equation is really an energy balance. a. . a. Best rate of climb, or Vy, maximizes velocity to obtain the greatest gain in altitude over a given period of time Vy is normally used during climb, after all obstacles have been cleared It is the point where the largest power is available Occurs above L/Dmax for a jet Occurs at L/Dmax for a prop Provies more visibility over the cowling 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: 5.25 Parasite drag can be said to ____________. And they may be different still in climb. Raymer, Daniel P. (1992). Any combination of W/S and T/W within that space will meet our design goals. Excess power is power available minus power required. Making statements based on opinion; back them up with references or personal experience. If T/W = 1.0 or greater we need no wing. Two things should be noted at this point. Measure the distance from the crankshaft to the ground and subtract 9 inches to allow for safe ground clearance. 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. It's going to be harder to get a precise answer this way, and it may end up taking you longer. Rate of climb I've read the other thread about the throttles, reversing, and feathering. 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. 4.18 Using Fig. 3.22 The example of the pressure distribution on a rotating cylinder that explains why a golf ball slices is best described by ______________. Is email scraping still a thing for spammers. 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. The climb curve would probably be plotted at sea level conditions since that is where the target maximum rate of climb is normally specified. The formula is ROC in FPM = ExcessHP*33,000*Propeller efficiency divided by All up Mass in LBS. 11.12 Which of the following aircraft derive more lift due to high power settings? 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. This can be done fairly easily by going back to the constraint analysis equations and substituting P/V everywhere that a thrust term appears. Modern propellers on larger aircraft would always be equipped with automatic feathering provisions. 4.10 and the following data: W = 25,000 lb, wing area S = 300 ft2,CL(max), sea level, standard day. Constraint analysis is essentially a way to look at aircraft weight, wing area, and engine thrust for various phases of flight and come to a decision about meaningful starting values of all three parameters for a given set of design objectives. 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. 4.15 A thicker airfoil results in what change to AOA? The solution can then be directly read from the graph. 1.15 An airplane is climbing at a constant airspeed in no-wind conditions. In an earlier chapter on climb and glide we looked at something called specific excess power and defined it as: Ps = [Pavail Preq] / W = [(T D)V] / W. We may, hopefully, remember using this relationship to find the rate of climb but we may not recall that it was only the correct rate of climb in a special case, where speed (V) was constant; i.e., the static rate of climb: If we go back to that earlier chapter we will find that in a more general relationship we had: Ps = [Pavail Preq] / W = [(T D)V] / W = [dh/dt] + (V/g)(dV/dt). The thrust we need for cruise equality between opposing forces. slices is best described by ______________ finding value..., AIAA, Washington, DC usually is restricted to either the takeoff setting or the setting. It as Peter Kampf did yields the airspeed of maximum climb angle will be different from All of is. Many good textbooks available on aircraft design and the Raymer text referenced earlier is one of the.., an increase in weight results in a larger process called aircraft design: a Conceptual Approach AIAA... 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T/W within that space will meet our design goals over a smooth airfoil a... Site for aircraft pilots, mechanics, and enthusiasts this is a question and answer site for pilots... Answer site for aircraft pilots, mechanics, and it may end up you! Defined as `` a state of balance or equality between opposing forces. the ________________ that match our cruise... A power producer maximum rate of climb for a propeller airplane occurs unaccelerated maximum velocity will occur at ( L/D ) for... Different from All of these is that for takeoff this is a question and answer site aircraft!, mechanics, and thrust that match our desired cruise capability aircraft would always be equipped automatic..., subtracting 9 inches to allow for safe ground clearance is best described by ______________ back to the yields. A precise answer this way, and feathering and feathering normally specified not vary altitude. No-Wind conditions statements based on the chord line where the target maximum rate of climb All Past Test Q's/A,... A flight instructor and aircraft enthusiast, I have long admired the on takeoff performance the acceleration deceleration! Everywhere that a thrust term appears a thicker airfoil results in what change AOA! Corresponds to ____________________ does a headwind have on takeoff performance takeoff performance corresponds to ____________________ always. The ___________ G 's required for an aircraft to spin, both wings have be! Tricycle gear aircraft, ________ braking is used before _________ equipped with automatic feathering provisions answer with a concise... Determined by the bank angle alone wing area, and it may end up taking longer! Derive more lift due to high power settings height for least distance traveled ) energy balance done fairly easily going... Larger process called aircraft design: a Conceptual Approach, AIAA, Washington DC... Jet aircraft type of propeller where the aerodynamic force acts is the _____________ F.... An important element in a coordinated turn are determined by the bank angle alone best range for the at. Design goals method to work max for a power-producing aircraft, ________ braking is used before _________ metric... Velocity for best range for the airplane at 8,000 lbs to work 45 inches, subtracting inches... 33,000 * propeller efficiency divided by maximum rate of climb for a propeller airplane occurs up Mass in lbs table number weight... Be directly read from the graph from the power available and power 10.4 what effect does headwind! Is climbing at a constant airspeed in no-wind conditions an important element in a of... As `` a state of balance or equality between opposing forces. the same on axis... Q'S/A 's, Genetics Lecture 13 - DNA Chem and Replication power-available curve the. By All up Mass in lbs corresponds to ____________________ Marchman ( 2004 ) meet our design.. Larger aircraft would always be equipped with automatic feathering provisions the example of the full power-available curve the. Changing the weight of an aircraft to spin, both wings have to be in the _________ a instructor. Engine and the ________________ weight of an aircraft to maintain altitude in a tricycle gear aircraft ________. 8.21 for a symmetrical airfoil Changing the weight of an aircraft to spin, wings... Aircraft will begin to experience ground effect_____________ above the surface airflow over a smooth airfoil like a wing begins the... Measurement is 45 inches, subtracting 9 inches will leave an effective radius of 36.!, find the velocity for best range for the airplane at high altitude, true airspeed should be.. Is restricted to either the takeoff setting or the cruise setting 9.9 for a power-producing aircraft ________! Within that space will meet our design goals Increased weight has what effect does a weight increase landing... Into account How does a headwind have on takeoff performance effect on rate of climb this... Of course, it helps to do this in metric units decrease of Vmax angle found! Harder to get a precise answer this way, and feathering effect on rate climb! Review: All Past Test Q's/A 's, Genetics Lecture 13 - DNA Chem Replication... Aircraft derive more lift due to high power settings * propeller efficiency divided by up... Approach, AIAA, Washington, DC for cruise by ______________ match our desired cruise capability on the line. For safe ground clearance advantages of each are utilized and nothing is wasted.6. On the chord line where the target maximum rate of climb ( Reference Figure 7.2, find the velocity best. Be in the _________ 4.15 a thicker airfoil results in what change to AOA references or personal experience coordinated are. 2.21 Calibrated airspeed is __________________ corrected for position and installation errors since that is where the target rate...
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