PART66 Licensing Info
Number of questions
Module 8. Basic aerodynamics
For an aircraft climbing at a constant IAS the Mach number will
• remain constant.
Community comments: 7
11.10.2012 / 16:47
Mach no. will increase because local speed of sound will decrease with altitude. Mach no = speed / local speed of sound (which depends from temperature (altitude)).
11.10.2012 / 16:49
11.10.2012 / 17:21
On climbing at constant IAS not only Mach no increases but TAS also increases.
Constant IAS= Mach no. (++)=TAS(++)
Constant Mach no= IAS (--)=TAS(--)
Constant IAS= Mach no. (--)=TAS(--)
Constant Mach no= IAS (++)=TAS(++)
ps: TAS will not vary as an aircraft climbs through Tropopause because of the temperature.(as mention by DIMKY) Speed of sound is constant in this region. ^V^
11.10.2012 / 17:24
Sir Dimky.. would u plz!! ans.these below Que...need ur help!THx! in advance..
A.In transonic speed range:
1.the centre of pressure movement may become ocillatory.
2.the position of the wing centre of pressure remains constant.
3.the centre of pressure initially moves forward then back.
B.The vertical fin of a single engined aircraft is:
1.parallel with both the longitudinal & vertical axis.
2.parallel with the longitudinal axis but not the vertical axis
3.parallel with vertical axis but not the longitudinal axis.
C.Wing loading is:
1. the maximum all up weight multiplied by the total wing area.
2.the maximum all up weight divided by the total wing area.
3.the ratio of the all up weight of the aircraft to its basic weight.
D.An engine which produces an efflux of high speed will be:
2.speed of efflux has no affect on the engine efficiency.
11.10.2012 / 18:50
Please don't dublicate your questions in many topics.
I think answers are:
A - 1
B - 1
C - 2
D - 1
Maybe easarabbit or MridulDev will correct me. :)
12.10.2012 / 06:22
i have my doubts on A & B, rest are spot on.
24.01.2019 / 21:06
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