UH-60Q 直升机技术手册 直升机操作手册 2(39)

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The altitude determined for optimum range may also be used for optimum endurance. Enter the chart at a current cruise or takeoff temperature condition and move along the temperature guide lines to the anticipated gross weight for cruise and obtain the optimum pressure altitude. Turn to the cruise chart closest to the altitude and temperature predicted by the optimum range chart for speci.c cruise information. The use of this chart is shown by the example.

OPTIMUM RANGE
CLEAN CONFIGURATION 100% RPM R
HIRSS (BAFFLES INSTALLED)

EXAMPLE

WANTED:
CRUISE ALTITUDE FOR OPTIMUM RANGE AND CORRESPONDING CRUISE CHART FOR FLIGHT CONDITIONS
KNOWN:
REFERENCE CONDITIONS OF: PRESSURE ALTITUDE = 1,500 FT FAT = 24 OC GROSS WEIGHT = 16,500 LB

METHOD:
ENTER CHART AT FAT (24 OC), MOVE RIGHT TO REFERENCE / OPTIMUM PRESSURE ALTITUDE (1,500 FT). MOVE PARALLEL WITH THE TEMPERATURE TREND LINES TO AIRCRAFT GROSS WEIGHT (16,500 LB). MOVE LEFT OR RIGHT PARALLELING THE TEMPERATURE TREND LINE TO NEAREST EVEN THOUSAND REFERENCE / OPTIMUM PRESSURE ALTITUDE LINE (12,000). MOVE LEFT TO FREE AIR TEMPERATURE LINE (2.5 OC), MOVE UP OR DOWN TO NEAREST TEN VALUE ON THE FREE AIR TEMPERATURE SCALE (0 OC).
SELECT CRUISE CHART WITH ALTITUDE AND
TEMPERATURE DATA AT THE NEAREST REFERENCE / OPTIMUM PRESSURE ALTITUDE (12,000 FT) AND THE NEAREST TEN DEGREE FREE AIR TEMPERATURE (0 OC).

AA0683_1B

OPTIMUM PRESSURE ALTITUDE ~ 1000 FT SA
DATA BASIS: FLIGHT TEST
OPTIMUM RANGE
HIGH DRAG CONFIGURATION 100% RPM R
HIRSS (BAFFLES INSTALLED)

 

0  2  4  6 8 10 12 14 16 OPTIMUM PRESSURE ALTITUDE ~ 1000 FT  18  20  22 
DATA BASIS: FLIGHT TEST  SA AA0683_2B 

Section VI DRAG
7.21 EXTERNAL LOAD DRAG CHART.  7.22 AIRCRAFT CONFIGURATION DRAG CHANGES FOR USE WITH CLEAN CRUISE
The general shapes of typical external loads are shown CHARTS. on Figure 7-30 as a function of the load frontal area. The frontal area is combined with the typical drag coefficient of When external equipment or con.guration differs from the general shapes to obtain a drag multiplying factor for the baseline clean con.guration as de.ned in Section I, a
use with the 10 sq. ft. drag scale on each cruise chart. The  drag correction should be made similarly to the external TRQ .% value obtained from the cruise chart is multi-drag load method. Typical con.guration changes that have

plied by the drag multiplying factor and added to indicated drag areas established from .ight test or analysis along with torque to obtain total torque required at any airspeed. their drag multiplying factor are shown on Table 7-1.
Table 7-1. Con.guration Drag Change
DRAG CHANGES FOR USE WITH CLEAN CRUISE CHARTS
Item Change in Flat Plate Drag Drag Multiplying Factor Area-
F Sq. Ft.
a.
Both cargo doors open  6.0 0.60

b.
Cargo doors removed  4.0 0.40

c.
Cargo mirror installed  0.3 0.03

d.
IR Countermeasure Transmitter (ALQ-144) installed 0.8  0.08

e.
Chaff Dispenser Installed  0.3 0.03

f.
HIRSS not installed  -2.2 -0.22

g.
Blade Erosion Kit  2.0 0.20

h.
UH-60Q con.guration  5.3 0.53

7.23 AIRCRAFT CONFIGURATION DRAG drag load method. Typical high drag con.guration changes CHANGES FOR USE WITH HIGH DRAG CRUISE that have been established from .ight test or analysis along CHARTS.
with the drag multiplying factors are shown.
When external equipment differs from the baseline high drag con.guration as de.ned in this Section, a drag correc-tion should be made using Table 7-2 similar to the external
Table 7-2. Con.guration Drag Change
DRAG CHANGES FOR USE WITH HIGH DRAG CRUISE CHARTS
Item Change in Flat Plate Drag Drag Multiplying Factor Area-
　
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