b.
ESSS Four pylons -no stores -1.7 -0.17
c.
Skis installed 3.0
-0.40
0.30
d. Both cargo doors open 6.0
0.60
EXTERNAL DRAG LOAD
METHOD:
EXAMPLE
KNOWN: ENTER CHART AT SYMBOL
LOAD
DRAG
0 2 4 6 8 10 12 14 16 18 20 22 24
DATA BASIS: ESTIMATED DRAG MULTIPLYING FACTOR SA AA0684A
Figure 7-30. External Load Drag
Table 7-2. Con.guration Drag Change (Cont)
DRAG CHANGES FOR USE WITH HIGH DRAG CRUISE CHARTS
Item Change in Flat Plate Drag Drag Multiplying Factor
Area- F Sq. Ft.
e. Both cargo doors removed 4.0 0.40
f. Cargo mirror installed 0.3 0.03
g. IR Countermeasure transmitter (AN/ALQ-144) removed -0.8 -0.08
h. Chaff dispenser removed -0.3 -0.03
Table 7-2. Con.guration Drag Change (Cont)
DRAG CHANGES FOR USE WITH HIGH DRAG CRUISE CHARTS
Item Change in Flat Plate Drag Drag Multiplying Factor
Area- F Sq. Ft.
i. UH-60Q con.guration 5.3 0.53
Section VII CLIMB -DESCENT
7.24 CLIMB/DESCENT CHART.
The CLIMB/DESCENT chart (Figures 7-31 and 7-32) presents the rate of climb or descent resulting from an in-crease or decrease of engine torque from the value required for level .ight above 40 KIAS. The data are presented at 100% RPM R for various gross weights. The charts may also be used in reverse to obtain the torque increase or reduction required to achieve a desired steady rate of climb or descent. The maximum R/C may be determined by sub-tracting the cruise chart torque required from the maximum torque available at the desired .ight conditions. Then enter the difference on the torque increase scale of the climb chart, move up to the gross weight, and read the resulting maximum R/C.
CLIMB/DESCENT
CLEAN CONFIGURATION 100% RPM R
FOR IAS ABOVE 40 KIAS
EXAMPLE
WANTED:
INDICATED TORQUE CHANGE FOR DESIRED RATE.OF.CLIMB OR DESCENT.
KNOWN:
GROSS WEIGHT = 18,000 POUNDS DESIRED RATE = 550 FEET PER MINUTE
METHOD:
ENTER CHART AT 550 FEET PER MINUTE MOVE RIGHT TO INTERSECT GROSS WEIGHT LINE. MOVE DOWN TO READ 12% TRQ CHANGE.
0 1020304050607080
TORQUE INCREASE PER ENGINE ~ % TRQ
AA0687A
SA
DATA BASIS: FLIGHT TEST
CLIMB/DESCENT
100% RPM R
AIRSPEEDS ABOVE 40 KIAS
4000
3500
3000
2500
2000
1500
1000
500
0
GROSS WEIGHT ~ 1000 LB
RATE OF CLIMB ~ FT/MIN RATE OF DESCENT ~ FT/MIN
0 1020304050607080
TORQUE REDUCTION PER ENGINE ~ % TRQ
3500
3000
2500
2000
1500
1000
500
0
GROSS WEIGHT ~ 1000 LB
22
24
0 1020304050607080
TORQUE INCREASE PER ENGINE ~ % TRQ
AA0688A
SA
DATA BASIS: FLIGHT TEST
Section VIII FUEL FLOW
7.25 IDLE FUEL FLOW.
Dual-engine idle fuel .ow is presented as a function of altitude at 0°C FAT in Table 7-3. The data are based on operation at 62% to 69% Ng for idle and 85% to 89% for .at pitch (collective full down) at 100% RPM R. Fuel .ow for the auxiliary power unit (APU) is also presented for a nominal load of 80% maximum power as a function of altitude and 0°C FAT for general planning.
7.26 SINGLE-ENGINE FUEL FLOW.
a.
Engine fuel .ow is presented in Figure 7-33 for vari-
ous torque and pressure altitudes at a baseline FAT of 0°C with engine bleed air extraction off. When operating at other than 0°C FAT, engine fuel .ow is increased 1% for each 20°C above the baseline temperature and, decreased 1% for each 20°C below the baseline temperature.
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