J-85-GE-5A Turbojet - Thrust Available vs. Altitude · PDF fileHOMEWORK 5 SOLUTION – SAM...
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HOMEWORK 5 SOLUTION – SAM RODKEY – OCTOBER 23 RD , 2005 avail SL SL T T ρ ρ ⎛ ⎞ = ⎜ ⎟ ⎝ ⎠ for Turbojet Engines (Brandt, pg 180, Equation 5.11) SL T = 1770 for Normal Power, 1935 for Military Power (no afterburner) J-85-GE-5A Turbojet - Thrust Available vs. Altitude 0.00 500.00 1000.00 1500.00 2000.00 2500.00 0 5000 10000 15000 20000 25000 30000 35000 39000 44000 49000 54000 59000 Altitude [feet] Thrust Available [lbf].. Normal Power Military Power
Transcript of J-85-GE-5A Turbojet - Thrust Available vs. Altitude · PDF fileHOMEWORK 5 SOLUTION – SAM...
HOMEWORK 5 SOLUTION – SAM RODKEY – OCTOBER 23RD, 2005
avail SLSL
T T ρρ
⎛ ⎞= ⎜ ⎟
⎝ ⎠ for Turbojet Engines (Brandt, pg 180, Equation 5.11)
SLT = 1770 for Normal Power, 1935 for Military Power (no afterburner)
J-85-GE-5A Turbojet - Thrust Available vs. Altitude
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st A
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.
Normal PowerMilitary Power
,t t SLSL
ac ca
⎛ ⎞= ⎜ ⎟
⎝ ⎠ for all turbine driven engines (Brandt, page 186, Equation 5.16)
,t SLc = 1.09 lb/lb-hr for Normal Power, 1.14 lb/lb-hr for Military Power J-85-GE-5A Turbojet - TSFC vs. Altitude
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0.1avail SL
SL
T TM
ρρ ∞
⎛ ⎞⎛ ⎞= ⎜ ⎟⎜ ⎟
⎝ ⎠⎝ ⎠ for Turbofan Engines (Brandt, pg 184, Equation 5.13)
SLT = 58,000 lbf For all values of M∞ < 0.1, use M∞ = 0.1 in this equation. IF NOT YOUR THRUST WILL BE REDICULOUSLY HIGH WHEN M∞ IS LOW!
CF6-80C2B1F Turbofan - Thrust Available vs. Altitude
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M = 0.1M = 0.5
,t t SLSL
ac ca
⎛ ⎞= ⎜ ⎟
⎝ ⎠ for all turbine driven engines (Brandt, page 186, Equation 5.16)
,t SLc = .337 lb/lb-hr for all M∞ since this is not a function of Mach Number
CF6-80C2B1F - TSFC vs. Altitude
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0.1avail SL
SL
T TM
ρρ ∞
⎛ ⎞⎛ ⎞= ⎜ ⎟⎜ ⎟
⎝ ⎠⎝ ⎠ for Turbofan Engines (Brandt, pg 184, Equation 5.13)
SL
ρρ
⎛ ⎞⎜ ⎟⎝ ⎠
= 0.3748422 at 30,000 ft
CF6-80C2B1F - Thrust Available vs. Velocity @ 30,000 ft
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IF YOU MISSED THIS PROBLEM YOU MOST LIKELY DID NOT HAVE CONSISTENT UNITS! ALWAYS CHECK UNITS! p
avail SLSL
T ESHPVηρ
ρ ∞
⎛ ⎞⎛ ⎞= ⎜ ⎟⎜ ⎟
⎝ ⎠⎝ ⎠ for Turboprop Engines (Brandt, pg 184, Equation 5.14)
exhaustSL SL
TESHP SHPk
= + where k is 2.5 lbf/hp or 8 N/kW (Brandt, Page 184)
SLSHP = 6150 hp
AE1107C Turboprop - Thrust Available vs. Altitude
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Altitude [feet]
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V_inf = 150 ft/sV_inf = 250 ft/sV_inf = 500 ft/s
AE1107C Turboprop - Thrust Available vs. Velocity @ 30,000 ft
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st A
vaila
ble
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