Airplane Flight
Manual Cessna
F150L
Nr. 160
Converted with kit
NS402S with ROTAX 912 S3 and
Page:
5-1
HOFFMANN HO-V352F/170FQ+10
Revision 1
5
PERFORMANCE
INTRODUCTION
Performance data charts on the following pages are presented so that you may know what to
expect from the airplane under various conditions, and, to facilitate the planning of flights in
detail and with reasonable accuracy. The data in the charts has been computed from actual
flight tests with the airplane and engine in good condition and using average piloting
techniques.
It should be noted that the performance information in the range and endurance charts do not
include fuel reserves. Cruise fuel flow values are based on normal engine settings. Some
indeterminable variables such as engine mixture, fuel metering characteristics, engine and
propeller condition, and air turbulence may account for variations of 10% or more. Therefore, it
is important to utilize all available information to estimate the fuel required for the particular
flight.
USE OF PERFORMANCE CHARTS
Performance data is presented in tabular or graphical form to illustrate
the effect of different variables. Sufficiently detailed information is provided in the tables so that
conservative values can be selected and used to determine the performance figure with
reasonable accuracy.
SAMPLE PROBLEM
The following example uses values from various tables and charts in this section to define the
performance values for a typical flight.
AIRPLANE CONFIGURATION
•
Takeoff weight ................................................ 692kg
•
Usable fuel ..................................................... 85ltr. (22.5 US gal)
TAKEOFF CONDITIONS
•
Field pressure altitude .................................... 1500ft
•
Temperature ................................................... 28°C (16°C above STD)
•
Wind component along the RWY .................... 12 kts Headwind
•
Field length ..................................................... 1067m
Fig. 5 - 4 should be used to determine the takeoff distance. For example, in this
sample
problem, the take-off distance information presented for a pressure altitude of 4000 feet and a
temperature of ISA + 22°C should be used and results in the following:
Ground roll:
387m
Takeoff distance
770m
Содержание CESSNA 150
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