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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:

  1. Boost Accelerometer
  2. Drag Accelerometer
  3. Transverse Accelerometer
  4. Normal Accelerometer
  5. Pitch Angular Accelerometer
  6. Separation Indicator
  7. Yaw Angular
  8. Roll Rate
  9. Angle of Attack (d)
  10. Angle of Sideslip (B)
  11. Pitot Pressure
  12. Static Pressure
  13. Separation
  14. Static "Buzz"
  15. Base Pressure
  16. 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:

  1. Boost Accelerometer
  2. Drag Accelerometer
  3. Transverse Accelerometer
  4. Normal Accelerometer
  5. Pitch Angular Accelerometer
  6. Separation Indicator
  7. Yaw Angular
  8. Roll Rate
  9. Angle of Attack (d)
  10. Angle of Sideslip (B)
  11. Pitot Pressure
  12. Static Pressure (from probe on d-B vane)
  13. Separation
  14. Static "Buzz"
  15. Base Pressure
  16. Pitot "Rake" at Duct Exit
  17. Separation Signal
  18. Roll Rate
  19. Full "Rake" Pressure
  20. Instrument Bay Temperature
  21. 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:

  1. Boost Accelerometer
  2. Drag Accelerometer
  3. Transverse Accelerometer
  4. Normal Accelerometer
  5. Pitch Angular Accelerometer
  6. Separation Indicator
  7. Yaw Angular
  8. Roll Rate
  9. Angle of Attack (d)
  10. Angle of Sideslip (B)
  11. Pitot Pressure
  12. Static Pressure (from probe on dB vane)
  13. Separation
  14. Static "Buzz"
  15. Base Pressure
  16. Pitot "Rake" at Duct Exit
  17. Separation Signal
  18. Roll Rate
  19. Full "Rake" Pressure
  20. Instrument Bay Temperature
  21. 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.

AVIATION TOP 100 - www.avitop.com Avitop.com

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