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The measurement of performance, stability and control characteristics of a high subsonic jet aircraft in non-steady flight conditions employing high accuracy instrumentation techniques

Published online by Cambridge University Press:  04 July 2016

J. A. Mulder
J. A. Mulder*
Affiliation:
Department of Aerospace Engineering, Delft University of Technology
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Extract

Aircraft lift and drag characteristics can be measured in flight by subtracting the components of engine net thrust along and perpendicular to airspeed from the corresponding components of the total aerodynamic force R.

In steady straight flight the flight path angle can easily be measured and consequently the components of R when aircraft weight is known. Measurements in steady-straight conditions, however, are time consuming and furthermore the resulting accuracies are limited due to unavoidable deviations from the nominal straight flight condition.

Type
Research Article
Information
The Aeronautical Journal , Volume 81 , Issue 798 , June 1977 , pp. 247 - 258
Copyright
Copyright © Royal Aeronautical Society 1977 

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References

1. AGARD, Flight Test Manual, Vol 1, Performance 1959.Google Scholar
2. Definitions of the thrust of a jet engine and of the internal drag of a ducted body. The Journal of the Royal Aeronautical Society, Vol 59, No 536. August 1955.Google Scholar
3. Ascough, J. C. Procedures for the measurement of engine thrust in flight. AGARD Flight Mech. Symp. on Flight Test Techniques, Cologne. October 1976.Google Scholar
4. Beeler, D. E., Bellman, D. R. and Sultzman, E. J. Flight techniques for determining airplane drag at high Mach numbers. AGARD Rep. 84. August 1956.Google Scholar
5. Davidson, T. W. Measurement of net thrust in flight. Journal of Aircraft, Vol 1, No 3. May-June 1964.Google Scholar
6. Draper, N. R. and Smith, H. Applied Regression Analysis. John Wiley & Sons, Inc. March 1968.Google Scholar
7. Gerlach, O. H. Determination of performance and stability parameters from non-steady flight test manoeuvres. SA1 Paper No 700236. March 1970.Google Scholar
8. Hoerner, S. F. Fluid-dynamic drag. 1958.Google Scholar
9. Hosman, R. J. A. W. Advanced flight test instrumentation: design and calibration. AGARD Conf. Proc. No 172 on Methods for Aircraft State and Parameter Identification. November 1974.Google Scholar
10. Jonkers, H. L. Application of the Kalman filter to flight path reconstruction from flight test data including estimation of instrumental bias errors. Rep. VTH-162, Department of Aerospace Engineering, Delft Univ. of Techn. February 1976.Google Scholar
11. Kleingeld, H. W. Design and evaluation of a symmetric flight test manoeuvre for the estimation of performance, stability and control characteristics. AGARD Conf. Proc. No 172 on Methods for Aircraft State and Parameter Identification. November 1974.Google Scholar
12. Mulder, J. A. Estimation of the aircraft state in non-steady flight. AGARD Conf. Proc. No 172 on Methods for Aircraft State and Parameter Identification. November 1974.Google Scholar
13. Rooney, E. C. Development of techniques to measure in-flight drag of a US Navy fighter airplane and correlation of flight measured drag with wind tunnel data. AGARD Conf. Proc. No 124 on Aerodynamic Drag. April 1973.Google Scholar
14. Stephenson, J., Shields, R. T. and Bottle, D. W. An investigation into the pilot rate method of measuring turbo jet engine thrust in flight. ARC Techn. Rep. CP No 143 (15, 509). 1954.Google Scholar
15. Wingrove, R. C. Applications of a technique for estimating aircraft states from recorded flight test data. AIAA Paper 72-965. 1972.Google Scholar