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FFM-Technical Results
Drag
and Stability
These
test results were compiled from Avro Technical Report
P/F.F.M./47, a 75 page summary of free flight model tests.
DRAG:
FFM-5
Point
Petre Range 14 May. 1955
ACCURATE
SCALE MODEL
-wings
had plain leading edge, 8% notch, .75% negative
camber
-radar
nose 50 deg conical shape
-J-67
intakes and ducts
-intermediate
J-75 rear fuselage
-fixed
control surfaces
INSTRUMENTATION:
Boost
Accelerometer
Drag
Accelerometer
Transverse
Accelerometer
Normal
Accelerometer
Pitch
Angular Accelerometer
Separation
Indicator
Yaw
Angular
Roll
Rate
Angle
of Attack (d)
Angle
of Sideslip (B)
Pitot
Pressure
Static
Pressure
Separation
Static "Buzz"
Base
Pressure
Pitot "Rake" at
Duct Exit
RESULTS:
-the
main purpose of this test was to determine from
data the supersonic drag coefficient of the CF-105
-also
2 subcarrier channels each commuted to give data
from 12 pressure points around and in the ducts
totaling 24 readings
-at
this time AVRO decided that a reevaluation of the
Picton range was necessary
-it
was noted that kine and radar tracking was erratic
and it was decided that the next two models to
Wallops Island for testing.
-this
was done to give CARDE time to repair their problems
at Pt. Petre and to give NACA an opportunity to
test it's new DOPPLER radar.
Wallops
Island is a rocket test range, N.A.C.A. at Langley
Air Force Base, near Hampton Virginia (became N.A.S.A.). 
 Delay
due to radar tracking problems. Testing moved to
United States to use the new "DOPPLER" radar
system which was  invented in New Mexico.
AVRO radar technicians were trained to use
this system.                         
FFM-6
Wallops
Island Virginia 9 May. 1956
ACCURATE
SCALE MODEL
-drooped
leading edge with 5% notch and 10% extension outboard
of notch
-30
deg conical radar nose shape
-J-75
intakes, ducts and rear fuselage
-pressure
rakes in ducts
-partial
area ruling of fuselage
INSTRUMENTATION:
Boost
Accelerometer
Drag
Accelerometer
Transverse
Accelerometer
Normal
Accelerometer
Pitch
Angular Accelerometer
Separation
Indicator
Yaw
Angular
Roll
Rate
Angle
of Attack (d)
Angle
of Sideslip (B)
Pitot
Pressure
Static
Pressure (from probe on d-B vane)
Separation
Static "Buzz"
Base
Pressure
Pitot "Rake" at
Duct Exit
Separation
Signal
Roll
Rate
Full "Rake" Pressure
Instrument
Bay Temperature
Commutated
Duct Pressures
RESULTS:
-on
pre-firing one commuted duct pressure sensor was
found to be inoperative
-during
boost the cover plate for the booster igniter came
off, but caused no damage
-because
of firing out to sea, no kine theodilites were
available to track the model
-radar
tracking was in automatic mode, except on model
separation, when an experienced radar technician
took control and manually tracked the model
-tracking
corrections normally supplied by 2 boresight cameras
were not available
"On
this model the d-B vane mounted on the sting was
modified to include a probe to measure the static
pressure. The assembly was balanced to within .1
ins. ozs. However, trouble was experienced in recording
d, although B seemed good. While transverse acceleration
and B correlated fairly well, normal acceleration
and d showed marked disagreement.
Later tests showed that the d trace error was entirely due to modifications
to the dB vane, but this was not immediately apparent.
Because of erroneous dB vane and the unstable oscillations the
test results were unsuitable for stability analysis but adequate
for drag calculations."
-high
rate of roll associated with the unstable oscillations
in the yaw plane
FFM-7
Wallops
Island Virginia 15 May.1956
ACCURATE
SCALE MODEL
-drooped
leading edge with 5% notch and 10% extension outboard
of notch
-30
deg conical radar nose shape
-J-75
intakes, ducts and rear fuselage
-pressure
rakes in ducts
-special
area ruling of fuselage (more complete, forward
upper part of fuselage)
INSTRUMENTATION:
Boost
Accelerometer
Drag
Accelerometer
Transverse
Accelerometer
Normal
Accelerometer
Pitch
Angular Accelerometer
Separation
Indicator
Yaw
Angular
Roll
Rate
Angle
of Attack (d)
Angle
of Sideslip (B)
Pitot
Pressure
Static
Pressure (from probe on dB vane)
Separation
Static "Buzz"
Base
Pressure
Pitot "Rake" at
Duct Exit
Separation
Signal
Roll
Rate
Full "Rake" Pressure
Instrument
Bay Temperature
Commutated
Duct Pressures
 
RESULTS:
-base
pressure did not function
-buzz
pressure was a poor trace
-roll
rate was more violent
-static
pressure from the dB vane was calibrated with a
radiosonde ballon over the range of mach no.
-with
the principal axis tilted down, models 5,6,and
7 were effected by inertia coupling
dB
vane malfunctioned in d
-due
to inertia coupling these results were unsuitable
for stability analysis, but suitable for drag
-tracking
radar performance was better and boresight cameras
were used.
STABILITY:
FFM-8
Point
Petre Range September. 1956
Lateral
Stability Model
No data available
at this time.
FFM-9
Point
Petre Range October. 1956
Lateral
Stability Model
No data available
at this time.
 
 
FFM-10
  Point
Petre Range December. 1956
Longitudinal
Stability Model
No data available
at this time.
 
 
FFM-11
Point
Petre Range January. 1957
Longitudinal
Stability Model
No data available
at this time.
 
 
Related
pages
[DAVID EWART COLLECTION] [PICTON
RANGE] [C.A.R.D.E.] [VIDEO]
Report
Courtesy A.V.Roe
Heritage Museum.
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