@ AVIATORZ
Q1 There is a theoretical table of pressure at various altitudes. It goes like this,
850 HPa - 5000 Ft
700 HPa- 10000 Ft
500 HPa- 20000 Ft
300 HPa- 30000 Ft
200 HPa- 40000 Ft
50 HPa - 68000 Ft
The question states 18000 Ft, hence pressure would be just a little more than 500 HPa.
Q 2 Mach No.= TAS/LSS
Inc. of 0.15 mach = Inc of 93 kts TAS/LSS
LSS= 93/0.15= 620 Kts
Q4 LSS is same as above question, 620 kts
LSS= 38.94 sq.root of absolute temperature
Put in the value of LSS and absolute temp= 254 Kelvin= -19 degree C
Temperature Deviation= OAT- ISA temp.
+9 = -19-ISA
ISA Temp.= -28 Deg. C
ISA Temp= 15 - (2 X Altitude)
-28= 15- 2 X Alt.
Altitude= 21.5 = 21500 Feet (close to FL220)
Q6 M.No= TAS/LSS
Put in values of M.no and TAS and find out LSS which comes out to be 594 Kts.
LSS= 38.94 sq.root of absolute temp.
OAT=233 Kelvin= -40.27 deg. C
ISA temp. Above 36090 ft is -56.5 deg. c
OAT- ISA= Temp. Deviation
-40.27- (-56.5)= +16.23 deg C (Close to +17)