answers are provided at the bottom Maximum available shaft power should be assumed to decrease in proportion to relative dens 1 Use the data in Table 1 to calculate the following: (a) Vmd,Vmp and Pmin (b) Shaft power output required to achieve (i) Straight-and-level flight at 160ms1, (ii) Best rate of climb of 10ms1. (iii) C

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answers are provided at the bottom
Maximum available shaft power should be assumed to decrease in proportion to relative dens
1 Use the data in Table 1 to calcu

Maximum available shaft power should be assumed to decrease in proportion to relative dens 1 Use the data in Table 1 to calculate the following: (a)

V_{m d}, V_{m p}

and

P_{m i n}

(b) Shaft power output required to achieve (i) Straight-and-level flight at

160 m s^{- 1}

, (ii) Best rate of climb of

10 m s^{- 1}

. (iii) Correctly banked turn, normal load factor 2.5 , at a speed of

100 m s^{- 1}

. In each case, give the associated values of

C_{L}

and

C_{D}

. (c) Ambient density at absolute ceiling altitude, based on an installed power (quoted at ISA sea level) of 8MW. (d) Gross still-air range and endurance at constant altitude of 25,000ft (

ρ / ρ st = 0.45)

and constant true air speed of

120 m / s

. The initial mass is

35000 kg

of which

10000 kg

is cruise fuel. Q1 (a)

Vm d = 81.3 m / s Vm p = 61.8 m / s P min = 1385.1 kW

(a)

(C L m d = 0.71 C L m p = 1.22)

(b)(i) Straight \& Level fight V=160.00m/s: Pshaft=7555.4kW (CL=0.182

C D = 0.021)

(b)(ii) For

10.00 m / s

best rate of climb: Pshaft=5668.9kW (b)(iii)

n = 2.5

Tum @

V = 100.0 m / s :

Pshaft

= 6446.9 kW

(c) relative density at celling altitude

= 0.346, Vmp = 105.0 m / s

(d) Gross Stir-Air Range

R = 5074.3 km @ V = 120.0 m / s

, sigma=0.45 Duration

= 11.75

hours

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