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The Static Stability of a Cone-Cylinder Flare and Two Cone-Cylinder Fin-Flare Combinations at Supersonic Speed

Published online by Cambridge University Press:  04 July 2016

M. C. Mathur
M. C. Mathur*
Affiliation:
Formerly with Rocket Engineering Division, Bristol Aerospace Limited, Canada now with Space-Science and Technology Centre, Trivandrum, India
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Extract

The Black Brant IV shown in Fig. 1, is a two-stage sounding rocket with a 15KS-25 000 booster motor stabilised with three fins and a 9KS-11 000 motor, a 5·3 fineness ratio conical noise and an 11·5° conical flare forming the second stage. Basically, the second stage is the single stage Black Brant III rocket, but uses a conical flare instead of three fins at the aft end for aerodynamic stability. This paper reviews the static stability of a Black Brant IV second stage with a flare and two fin-flare combinations.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 73 , Issue 702 , June 1969 , pp. 520 - 524
Copyright
Copyright © Royal Aeronautical Society 1969 

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References

1. Elinwood, J. W., Parsons, W. D. and Nakagama, T. T. Effectiveness of Flared Afterbodies in Lift: Data Survey and Application to the Exos Third Stage, Space General Report 106-R2, May 1962. (Confidential.)Google Scholar
2. Dixon, R. C. Black Brant IV Second Stage Stability Model, NAE, High Speed Aerodynamics Section, Wind Tunnel Data Report 5X5/0002, June-July 1963.Google Scholar
3. Dixon, R. C. and Galway, R. D. Addendum to 5X5/0001 and 5X5/0002, NAE, High Speed Aerdoynamics Section, Wind Tunnel Data Report 5X5/0004, March-April 1964.Google Scholar
4. Sevier, H. G. Flight Trials Report and Data Analysis of Black Brant IVA Vehicles-01 and -02, Canadian Bristol Aerojet, Technical Memorandum No 149, August 1964.Google Scholar
5. Dixon, R. C. Stability of Black Brant IV Second Stage with Flare-Mounted Fins, NAE, High Speed Aerodynamics Section, Wind Tunnel Data Report 5X5/0006, September-October 1964.Google Scholar
6. USAF Stability and Control DATCOM, Flight Control Division, Air Force Flight Dynamics Laboratory, Wright Patterson AFB, Ohio, Revised Edition, July 1963.Google Scholar
7. Mathur, M. C. An Aerodynamic Stability Study of the Black Brant IV Second Stage with a Conical Flare and Two Fin-Flare Combinations Using the NAE Supersonic Wind Tunnel, Canadian Bristol Aerojet, Engineering Report No 4157, April 1965.Google Scholar
8. Sevier, H. G. and Mathur, M. C. An Analysis of NAE Wind Tunnel Data and Comparison with Theoretical Rigid Vehicle and Aeroelastic Static Stability Calculations (Black Brant III), Canadian Bristol Aerojet, Technical Memorandum No 105, Issue B, October 1964.Google Scholar
9. Gowans, B. A Comparison of Methods Available for Predicting Cone-Cylinder Aerodynamic Forces along with Some Experimental Data, Canadian Bristol Aerojet, Technical Memorandum No 204, March 1965.Google Scholar
10. Van Dyke, M. D., The Combined Supersonic Hypersonic Similarity Rule, Reader's Forum, Journal of Aeronautical Sciences, July 1951.Google Scholar
11. Kirk, D. B. and Chapman, G. T. The Stabilizing Effectiveness of Conical Flares on Bodies with Conical Noses, NASA TM X-30, September 1959.Google Scholar
12. Ohman, L. The Square Flare, AIAA Journal (to be published).Google Scholar
13. Spring, D. J. The Static Stability Characteristics of Several Cone-Cylinder-Flare-Cylinder Configurations at Mach Numbers 0.4 to 4.5, US Army Missile Command, Redstone Arsenal Alabama, Report No RF-TR-63-14, 1963.Google Scholar
14. Hayes, C. and Fournier, R. H. Effects of Fin-Flare Combinations on the Aerodynamic Characteristics of a Body with Mach Numbers 1.61 and 2.20, NASA TN D-2623, February 1965.Google Scholar