View Full Version : Clearly doin' something stooopid..
Grass strip basher 1st Apr 2006, 10:39 Morning fellow Ppruners
Apologies for the hassle but was wondering if someone could help me with this question... just can't seem to get to the right answer... its a BGS question bank classic so I am sure some of you will have seen it before...
A 50 ton twin engine aeroplane performs a straight, steady, wings level climb. If the lift/drag ratio is 12 and the thrust is 60 000N per engine, the climb gradient (@<hidden>) is: (assume g = 10m/s2)?
50 tonnes = 50,000kg which x 10 gives 500,000N of weight
2 x engines so 120,000N of thrust
So I assume you now use sin@<hidden> = (TD)/W or Sin@<hidden> =(T/w)(Cd/Cl)?
but can't seem to get to one of the answers offered.... exam on Monday gulp :uhoh:
BEagle 1st Apr 2006, 11:05 Is one of the answers 9.28 degrees?
Grass strip basher 1st Apr 2006, 11:22 Nope... I don't think it was but I get 910 degrees as well ... must be doing something wrong... the explanation under the "info" tab was a bit strange in that is said something along the lines of the drag = 500,000/12= 41,667... then "you have the formula so do the rest!".... as the aircraft is in a climb the weight does not = lift so surely this is wrong?
Fletch 1st Apr 2006, 11:36 Is one of the answers 2.1
BEagle 1st Apr 2006, 11:42 I'm sure that sin@<hidden> = (T/W)  (Cd/Cl) is correct; in which case the answer would seem to be inv sin (120/(50 x 9.81))  (1/12)
i.e. inv sin (0.2446  0.0833) = inv sin 0.1613 = 9.28 deg.....
What were their answers?
Grass strip basher 1st Apr 2006, 12:00 Beagle that is exactly the same calc I did... think one of the answers was 15.7 but none were the 910 degrees we both arrive at.... think another one of the answers was 3... :confused:
bjkeates 1st Apr 2006, 12:19 I notice you're using sin and inv.sin in these calculations. I don't know much about the calculation you're doing, but a simple thing to check is that you've got your calculator in the correct mode  make sure it's set to Degrees, not Radians or Grads  this could be giving you an error.
Grass strip basher 1st Apr 2006, 12:23 Its asking for a climb gradient... not climb angle.... climb gradient is sin @<hidden> which = 0.15666 so 15.7% which is one of the answers... thanks for your help.... lesson learnt RTFQ... Good luck to everyone else sitting exams on Monday
BEagle 1st Apr 2006, 14:07 Ah  of course. The Eurocratic JAA which loves to quantify aircraft climb values in the same way they measure road gradients...
Why is 'g' expressed as 10 rather than 9.81 m/s/s?
Bandit Man 1st Apr 2006, 14:16 well if you say that then i can say why do they not take acceleration due to gravity as 9.80665 m/sē?
High Wing Drifter 1st Apr 2006, 16:21 Ah  of course. The Eurocratic JAA which loves to quantify aircraft climb values in the same way they measure road gradients...
Gradients are much more practical than degrees! Seems like good sense to me :)
For example: RoD = Gradient * GS as opposed to Sin(Deg) * GS !!
Surprised 9.3% wasn't one of the available answers. Perhaps the examiner was feeling uncharacteristically kind that day.
BEagle 1st Apr 2006, 19:36 Bandit Man  because 'g' varies with latitude and location  hence to use the value to the degree of accuracy you quote is pointless. The value you quote is only 0.034% less than the average value of 9.81 m/s/s, whereas using 10 m/s/s incurs an error of around 30 times greater than that.
In the question you have to assume that Lift does indeed equal weight. Thus you get (12000041667)/500000 = 0.15666
Now using small angle approximation sin a = tan a = opp/adj
Thus you have a ratio of 15.6/100 or 15.7%.
Tan1 and Sin1 don't come into it.
I expect to see one in the exam on Monday, but with different numbers
Bandit Man 1st Apr 2006, 20:49 I know BEagle, i just was trying to point out that its just an approximation to make the calculation for the question simpler.
Just thought I'd remark that by stating the aeroplane is in a "straight, steady, wings level climb", the question presents all the information one needs to make the assumption that lift does in fact equal weight. The straight and level stuff indicates that the aircraft is being subjected to no acceleration forces. If lift were greater than weight, it would accelerate upwards, i.e. would climb at an everincreasing rate.
Good luck tomorrow, Grass strip basher!
mbcxharm 3rd Apr 2006, 07:49 Going slightly off thread here really but using g=9.81 is also pointless since 2 of the numbers you are given are only accurate to one significant figure and the other only accurate to 2 sig. figs. 10 is perfectly reasonable and banditman's point is a good one.
Grass strip basher 3rd Apr 2006, 13:44 It did come up in the exam today! Thanks to those who offered help.... now I just hope I got it right :uhoh:
