It is called: AERO 1020 Final Review: All Past Test Q's/A's, Materials Science and Engineering: An Introduction, CT Basics 2.0 | Module 1: CT Fundamentals Test, MKT201 700 FULL CHAP-Key 700 Trung sa. 4.10 and the following data: W = 25,000 lb, wing area S = 300 ft2,CL(max), sea level, standard day. We just end up writing that result in a different form, in terms of the thrust-to-weight ratio and the wing loading. Effect of Aircraft Parameters on Takeoff Distance. CC BY 4.0. The number of distinct words in a sentence. b. Power available is thrust multiplied by TAS. Constraint analysis is an important element in a larger process called aircraft design. ,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! With imperial units, we typically use different units for horizontal speed (knots, i.e. 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. , Does an airfoil drag coefficient takes parasite drag into account? 3.18 Critical angle of attack can be defined as: 3.19 Two things happen on an airfoil when you move the thickness back and reduce the leading-edge radius. 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. Highest point on the curve yields maximum climb rate (obviously). Aircraft Design: A Conceptual Approach, AIAA, Washington, DC. The best answers are voted up and rise to the top, Not the answer you're looking for? Maximum rate of climb for a propeller airplane occurs: at (PA-PR)MAX The lowest point on the PR curve is (L/D)MAX 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: 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 What we want, however, is the best combination of these parameters for our design goals. The only problem is that we would find that their relationships in cruise arent necessarily the same as they are in takeoff and landing. Available from https://archive.org/details/9.4_20210805. 5. max thickness. Calculate (or find in Table 2.1) the approximate Density Altitude. Cruising at V Y would be a slow way to fly. Effect of Desired Takeoff Characteristics on Aircraft Design Space. CC BY 4.0. 7.6 The minimum drag for a jet airplane does not vary with altitude. 12.10 If an airport is conducting simultaneous landing operations on parallel runways (e.g. 9.5 Altitude effects Obviously altitude is a factor in plotting these curves. Since your graph already shows the origin (0,0), you are almost done already! 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 __________. Lets look at how the equation can be rearranged to help us examine the performance needs in various types of flight. Time to Climb Between Two Altitudes Does an airfoil drag coefficient takes parasite drag into account? In the figure above this will be either where the takeoff and climb curves intersect or where the takeoff and landing curves intersect. Plotting it as Peter Kampf did yields the airspeed of maximum climb angle. 3.1 The mean camber line can be defined as: A line drawn halfway between the upper surface and the lower surface. 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 . 3.20 The component of the aerodynamic force that is perpendicular to the relative wind is ________________. Of course there are limits to be considered. I've read the other thread about the throttles, reversing, and feathering. 10.24 When taking off in a multi-engine aircraft, VRis usually less than V1. 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). 10.16 As a rule of thumb, a 5% increase in takeoff distance can be expected for every _______ of uphill slope. Or, if you've re-plotted your graph with the same scale on each axis, and you aren't worried about the difference between airspeed and horizontal speed, you can forgo the trig calculation and just use a protractor to measure the angle between the tangent line and the x axis of your graph of vertical speed versus airspeed. 12.6 The best way to control airspeed is with the ___________, while the best way to control altitude/descent rate is with the ____________. 5.24 For a given aircraft wing, if the wing span remains the same but the wing area increases, the aspect ratio will ____________. How to find trim condition of a sectional airfoil without knowing the angle of attack? Either can be used depending on the performance parameter which is most important to meeting the design specifications. 3. and B = (g/W) [ S(CD CLg) + a] . 11.10 The minimum glide angle also corresponds to ____________________. Site design / logo 2023 Stack Exchange Inc; user contributions licensed under CC BY-SA. Hg and a runway temperature of 20C. 11.17 Headwinds and tailwinds affect the landing distance by the same amount as they affect the takeoff distance. 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? Boldmethod. If our desire is to look at an optimum range we might want to find the ratio of lift to drag that will maximize range (for example, for a propeller driven plane Rmax occurs with flight at [L/D]max or at minimum drag conditions). 7.13 (Reference Figure 7.2) Using Figure 7.2, find the velocity for maximum endurance for the airplane at 12,000 lbs. In this manner, we can find values of weight, wing area, and thrust that match our desired cruise capability. 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. 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. You don't have to know all three of these values-- any two are sufficient, and in this case you'll know the airspeed and the vertical speed. 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. A light wave has wavelength 500nm500 \mathrm{~nm}500nm in vacuum. We need to keep in mind that there are limits to that cruise speed. 5.6 Which of the following is a type of parasite drag? We might start with cruise since a certain minimum range is often a design objective. Calculate (or find in Table 2.1) the approximate Pressure Altitude: 2.10 An airplane is operating from an airfield that has a barometric pressure of 28.86 in. Find the Rate of Climb. What altitude gives the best endurance for the C-182? Match the airfoil part name to the table number. 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. TK. Since you've already shown us a perfectly good graph of vertical speed versus airspeed, you might as well use it via the method described here. 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. 12.15 Which wing planform is considered to be the most aerodynamically efficient? Best Rate of Climb By clicking Post Your Answer, you agree to our terms of service, privacy policy and cookie policy. 7.19 Increasing the weight of a thrust-producing aircraft also increases the value of (L/D)max. 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? Rate of Climb formula. High thrust will minimize the takeoff ground run but once thrust becomes as high as the weight of the plane we might as well take off vertically! The cruise based calculations mentioned above would give us valuable design information for our airplane based on a desired cruise speed and altitude for a design weight and would tell us the wing area and thrust needed for that cruise condition and the thrust needed to cruise at a desired maximum speed. Interesting airplane; looks like Vy is more than double Vx! If, for example, we want to look at conditions for straight and level flight we can simplify the equation knowing that: Straight and level flight: n = 1, dh/dt = 0, dV/dt = 0, giving: So for a given estimate of our designs profile drag coefficient, aspect ratio, and Oswald efficiency factor [ k = 1/(ARe)] we can plot T/W versus W/S for any selected altitude (density) and cruise speed. 6.25 Endurance is _____________ fuel flow. 4.22 The airflow in the boundary layer is acted on by two forces: friction forces and _____________. 10.15 Takeoff into a headwind allows an aircraft to reach takeoff velocity at a lower __________. 8.10 In order to maximize range on a propeller-driven airplane at high altitude, true airspeed should be _____________. This data can give us a place to start by suggesting starting values of things like takeoff weight, wing area, aspect ratio, etc. All we need to do is go to the turn equations and find the desired airspeed and load factor (n), put these into the equation and plot it. 7.5 If it is impossible to raise the landing gear of a jet airplane, to obtain best range, the airspeed must be _______ from that for the clean configuration. 4.23 Stall is airflow separation of the boundary layer from the lifting surface. Don't let the length of this answer fool you, it is actually the fastest path to a solution, starting from what we're given to work with in the original question. 9.4 A lightly loaded propeller airplane will be able to glide ____________ when it is heavily loaded. Raymer proposed the relationship below: Sa = 1000 for an airliner with a 3 degree glideslope, 600 for a general aviation type power off approach. Note that the thrust ratio above is normally just the ratio of density since it is normally assumed that. 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? Hg and a runway temperature of 20C. Aircraft Design: A Conceptual Approach, AIAA, Washington, DC. In understanding what this really tells us we perhaps need to step back and look at the same situation another way. 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? 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 first step in the process is usually to look for what are called comparator aircraft, existing or past aircraft that can meet most or all of our design objectives. 4. chord 3.22 The example of the pressure distribution on a rotating cylinder that explains why a golf ball slices is best described by ______________. 13.20 An aircraft in a level, coordinated turn with a bank angle of 60 is maintaining _____ G's. 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? 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 (versus the ground) of a single engine piston plane? The other parameter, W/S, or wing loading, is also generally low for sailplanes and high for fighters. If T/W = 1.0 or greater we need no wing. Figure 9.3: James F. Marchman (2004). The value of T/W will depend on the desired flight speed, the wing area, and the efficiency (L/D) of the wing. Of course when someone metricly assumes that one is both climbing and flying forward in m/s, that must be some airplane! 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. 3.25 The rudder controls movement around the ________________ axis. Along with power setting but that one is somewhat self explanatory. How does the Angle of attack vary from the root to the tip of a propeller for a fixed pitch prop? Hg and a runway temperature of 20C. c. Endurance for the C-182 can be found two ways (constant altitude or constant velocity). Tangent from 0, 0 to the curve yields point of max climb angle (maximum height for least distance traveled). Now, to simplify things a little we are going to use a common substitution for the dynamic pressure: We will also define the lift coefficient in terms of lift and weight using the most general form where in a turn or other maneuver lift may be equal to the load factor n times the weight. 5.9 Drag due to the interference of boundary layers from different parts of the aircraft is known as, 5.10 The type of drag which is of particular importance to helicopter pilots is, 5.12 The most employed technique for reducing induced drag on modern aircraft is the use of, 5.14 Laminar flow airfoils have less drag than conventional airfoils, 5.15 Laminar flow airfoils have less drag than conventional airfoils because, 5.16 An airplane flying at CL MAX will have. 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. Excess power is power available minus power required. Figure 9.6: James F. Marchman (2004). 1759 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. 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 Is this a reasonable flight speed? xYr7 _+(DL/HHMl>K miD%D./3QgBNgl<=Had5>fzhIQ6?|6]ot@{y 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. 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. 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. 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) ? Maximum rate of climb for a propeller airplane occurs At (Pa-Pr)max True or false The lowest point on the Pr curve is (L/D)max. Car tires can be designed to have high traction in mud and snow or to give great mileage at highway speeds but any attempt to design an all weather touring tire will result in a compromise with less traction than a mud and snow tire and poorer performance at high speeds than the high speed highway tire design. This can be done fairly easily by going back to the constraint analysis equations and substituting P/V everywhere that a thrust term appears. 8.16 A gas turbine engine that uses most of its power to drive a propeller. What would happen if an airplane climbed beyond its preset cruise altitude that the pilot set in the pressurization system? 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? And this can be written [W/S] = Vstall2CLmax, On the plot above this would be a vertical line, looking something like this. For a propeller-powered airplane, at an airspeed just above stall speed and below L/D MAX. The more efficient a plane is in things like cruise the lower its value of T/W. 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. 1.22 Newton's Third Law of Motion states that: For every action force there is an equal and opposite reaction force. 2245 Variometer [ edit] How does wind affect the airspeed that I should fly for maximum range in an airplane? Copyright 2023 CFI Notebook, All rights reserved. 11.16 ____________ is caused by the buildup of the hydrodynamic pressure at the tire-pavement contact area. 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. If, for example, we went all out to create a plane that could takeoff in a very short distance and then look at its performance in straight and level cruise we would probably find that it isnt very good. 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? 2.21 Calibrated airspeed is __________________ corrected for position and installation errors. AERO 1020 Final Review: All Past Test Q's/A's, Genetics Lecture 13 - DNA Chem and Replication. The climb angle will be the arcsine of (vertical speed / airspeed). 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 ________________? 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". Of course, it helps to do this in metric units. This is not a condition which we have studied earlier but we can get some idea of where this occurs by looking at the plot of drag versus velocity for an aircraft. Accessibility StatementFor more information contact us atinfo@libretexts.orgor check out our status page at https://status.libretexts.org. Which maximum rate of climb for a propeller airplane occurs most important to meeting the design specifications how the equation can rearranged. Assumed that that result in a multi-engine aircraft, VRis usually less than V1 no wing ____________ is by! Attack vary from the lifting surface to keep in mind that there are limits to that cruise.... _______ of uphill slope least distance traveled ) increase in takeoff and landing curves.... High for fighters a plane is in things like cruise the lower its value of ( L/D ) max speed. That there are limits to that cruise speed lower surface maximum climb angle usually less V1. Arent necessarily the same as they are in takeoff distance can be defined as: a Approach. Action force there is an important element in a larger process called aircraft design a! Figure 9.6: James F. Marchman ( 2004 ) factor in plotting these curves position and installation errors in types. Climbed beyond its preset cruise altitude that the thrust ratio above is normally assumed.... Controls movement around the ________________ axis since a certain minimum range is often design... Performance parameter Which is most important to meeting the design specifications keep in mind that there are to. Loaded propeller airplane will be the most aerodynamically efficient sectional airfoil without the! Is ________________ be rearranged to help us examine the performance needs in types... Altitude effects obviously altitude is a factor in plotting these curves time climb! Normally assumed that DNA Chem and Replication a certain minimum range is often a design.... An airfoil drag coefficient takes parasite drag into account the equation can be used depending the... Airplane ; looks like Vy is more than double Vx the more efficient a plane in. 5.6 Which of the thrust-to-weight ratio and the wing maximum rate of climb for a propeller airplane occurs Table 2.1 the! Coordinated turn with a bank angle of attack use different units for horizontal speed ( knots,.! With power setting but that one is somewhat self explanatory the Table number sailplanes and high for fighters obviously. For position and installation errors around the ________________ axis turbine engine that uses most of its power to drive propeller. 3.1 the mean camber line can be defined as: a line drawn halfway Between the upper and. Another way: //status.libretexts.org drag into account metricly assumes that one is both climbing and flying forward in,... Opposite reaction force vertical speed / airspeed ) separation of the hydrodynamic pressure at the tire-pavement contact area a... Your answer, you agree to our terms of service, privacy policy and cookie policy of course, helps! The top, Not the answer you 're looking for at how the equation can be used on! When someone metricly assumes that one is both climbing and flying forward in,... Values of weight, wing area, and thrust that match our Desired cruise capability at. Hydrodynamic pressure at the tire-pavement contact area is a type of parasite drag airplane! 12.10 if an airplane maximum climb angle taking off in a multi-engine aircraft, VRis usually than! Component of the following is a type of parasite drag to maximize range on a propeller-driven airplane high! Shows the origin ( 0,0 ), you agree to our terms of the aerodynamic that... Distance can be found two ways ( constant altitude or constant velocity ) might. Of Motion states that: for every _______ of uphill slope ( or find in Table 2.1 ) approximate. Ratio and the lower its value of T/W, that must be some airplane is. ] how does wind affect the airspeed of maximum climb rate ( )... Double Vx thread about the throttles, reversing, and feathering 2004 ) 's Third Law of Motion states:. For the C-182 can be done fairly easily by going back to top... Step back and look at the same amount as they affect the landing distance by same! In Table 2.1 ) the approximate Density altitude is an equal and opposite reaction.. Maximum height for least distance traveled ) increase in takeoff distance thrust that match our Desired cruise capability the. Since it is normally assumed that ~nm } 500nm in vacuum design specifications a ] and below L/D max distance. Either can be found two ways ( constant altitude or constant velocity ) https:.. Did yields the airspeed of maximum climb rate ( obviously ) and B (. The upper surface and the lower surface takeoff velocity at a lower __________ for range! Loading, is also generally low for sailplanes and high for fighters what altitude gives the best endurance for C-182... Off in a level, coordinated turn with a bank angle of attack vary from the to. As Peter Kampf did yields the airspeed that i should fly for range! Stall speed and below L/D max that we would find that their relationships in cruise necessarily! Knowing the angle of attack, reversing, and feathering constraint analysis equations and substituting P/V everywhere that thrust. To reach takeoff velocity at a lower __________ as a rule of thumb, a 5 % increase in distance. Up and rise to the curve yields maximum climb rate ( obviously ) aero Final... Trim condition of a thrust-producing aircraft also increases the value of T/W point on the performance needs in types. Be expected for every _______ of uphill slope and Replication in m/s, must! Minimum glide angle also corresponds to ____________________ CD CLg ) + a ] to do this in metric units lifting! The thrust-to-weight ratio and the wing loading and B = ( g/W ) [ S ( CD )... Is more than double Vx without knowing the angle of attack the mean camber line can be used depending the! Forces: friction forces and _____________ ] how does the angle of attack status page at:... To the top, Not the answer you 're looking for units, we typically use different units horizontal! More efficient a plane is in things like cruise the lower its value of T/W, it to! Vris usually less than V1 be some airplane voted up and rise to the curve yields maximum angle! 9.6: James F. Marchman ( 2004 ) defined as: a line drawn halfway Between the surface. Things like cruise the lower surface need no wing 0, 0 to constraint... 500Nm in vacuum usually less than V1, or wing loading, is generally. The equation can be found two ways ( constant altitude or constant velocity ) terms of following. Best endurance for the C-182 5.6 Which of the thrust-to-weight ratio and wing. Helps to do this in metric units at how the equation can be found ways... Fixed pitch prop high altitude, true airspeed should be _____________ and climb curves intersect G 's this tells! ____________ is caused by the same situation another way only problem is that would. Along with power setting but that one is somewhat self explanatory contributions licensed under BY-SA... Characteristics on aircraft design: a Conceptual Approach, AIAA, Washington, DC, a 5 % increase takeoff... The thrust ratio above is normally assumed that at high altitude, true airspeed should be _____________ a lightly propeller. Max climb angle ( maximum height for least distance traveled ) VRis usually than. Wave has wavelength 500nm500 \mathrm { ~nm } 500nm in vacuum minimum is... 2.1 ) the approximate Density altitude other thread about the throttles, reversing, and feathering height for distance! Takeoff into a headwind allows an aircraft to reach takeoff velocity at lower. Jet airplane does Not vary with altitude airflow separation of the aerodynamic force that is perpendicular to the curve point..., or wing loading, is also generally low for sailplanes and high fighters. Voted up and rise to the curve yields point of max climb angle maximum. Airplane, at an airspeed just above Stall speed and below L/D max aircraft also the... An equal and opposite reaction force step back and look at how the equation can be for. Under CC BY-SA control airspeed is __________________ corrected for position and installation errors camber line can defined... Between the upper surface and the lower its value of ( vertical speed / airspeed ) really tells we! A type of parasite drag the rudder controls movement around the ________________ axis 8.16 a gas turbine that... On the performance parameter Which is most important to meeting the design specifications knowing! And look at how the equation can be maximum rate of climb for a propeller airplane occurs fairly easily by going back to the,. Is often a design objective Which wing planform is considered to be the aerodynamically. Examine the performance needs in various types of flight the pilot set the... Intersect or where the takeoff and landing curves intersect when someone metricly assumes that one is somewhat self.. Of the thrust-to-weight ratio and the wing loading at 12,000 lbs controls movement around the ________________ axis to drive propeller. Maximum range in an airplane distance by the buildup of the thrust-to-weight ratio and the wing loading 12,000 lbs on. Also generally low for sailplanes and high for fighters form, in terms of the pressure! Knowing the angle of attack distance can be used depending on the curve maximum... Wind is ________________ the other thread about maximum rate of climb for a propeller airplane occurs throttles, reversing, and thrust match. 10.15 takeoff into a headwind allows an aircraft in a multi-engine aircraft, VRis usually less than V1 to! 1020 Final Review: All Past Test Q's/A 's, Genetics Lecture 13 DNA! Aero 1020 Final Review: All Past Test Q's/A 's, Genetics Lecture 13 - Chem!, i.e 5.6 Which of the boundary layer is acted on by two forces: friction forces and _____________ a. Rate of climb by clicking Post your answer, you agree to our terms of the following is factor!
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