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Analytical Techniques for the Analysis of Stall/Spin Flight Test Data
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Abstract
Analytical techniques for the analysis of stall/spin flight test data are reviewed by discussing (1) certain special flight instrumentation issues, (2) the mathematical modeling techniques, and (3) the analysis of post stall and spinning flight of general aviation airplanes. The angles of attack, sideslip, roll, pitch, and yaw are derived from measurements of angular velocity and linear acceleration. The key to the success of this approach is to simultaneously estimate both the biases in the instrumentation and the initial conditions. Techniques for determining stability derivatives from flight data are applied to angles of attack too high for stabilized flight. This practice greatly expands the range over which aerodynamic characteristics can be determined from flight test. Nonlinear terms in certain aerodynamic functions are shown to be valid by comparing them with the trends of results at different angles of attack A very old technique of studying spins is extended and applied to some modern light airplanes. Airplanes for which the wing provides the dominant moments during spins, offer the possibility of linking spin characteristics to longitudinal data.
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Citation
Taylor, L. and Klein, V., "Analytical Techniques for the Analysis of Stall/Spin Flight Test Data," SAE Technical Paper 810599, 1981, https://doi.org/10.4271/810599.Also In
References
- Anon “Report on Accidents to Certain Aeroplanes With Special Reference to Spinning.” Accidents Sub-Committee. R & M 592 Dec. 1918
- Gates S. B. Bryant L. W. “The Spinning of Aeroplanes.” R & M 1001 Oct. 1926
- Burk Sanger M. Bowman James S. Jr. White William L. “Spin-Tunnel Investigation of the Spinning Characteristics of Typical Single-Engine General Aviation Airplane Design.” II - Low Wing Model A, Tail Parachute Diameter and Canopy Distance for Emergency Spin Recovery. NASA TP-1076 1977
- Bihrle William Jr. Hultberg Randy S. Mulcay William “Rotary Balance Data for a Typical Single-Engine Low-Wing General Aviation Design for an Angle-of-Attack Range of 30° to 90°.” NASA CR-2972 1978
- Patton James M. Jr. Stough H. Paul III DiCarlo Daniel J. “Spin Flight Research Summary,” Paper, Soc. Automot, Eng. 790565 1979
- Moul Thomas M. Taylor Lawrence W. Jr. “Determination of an Angle of Attack Sensor Correction for a General Aviation Airplane at Large Angles of Attack as Determined From Wind Tunnel and Flight Tests.” AIAA Aircraft Systems and Technology Meeting Aug. 1980 AIAA Paper 80-1845
- Klein Vladislav Schiess James R. “Compatibility Check of Measured Aircraft Responses Using Kinematic Equations and Extended Kalman Filter.” NASA TN D-8514 Aug. 1977
- Keskar D. A Klein V. “Determination of Instrumentation Errors From Measured Data Using Maximum Likelihood Method.” A Collection of Technical Papers - AIAA Atmospheric Flight Mechanics Conference Aug. 1980 392 396
- Taylor Lawrence W. Jr. Iliff Kenneth W. “System Identification Using a Modified Newton-Raphson Method - A Fortran Program.” NASA TN D-6734 1972
- Draper N. R. Smith H. “Applied Regression Analysis.” John Wiley & Sons, Inc. 1966
- Bihrle William Jr. Hultberg Randy S. “Rotary Balance Data for a Typical Single-Engine General Aviation Design for an Angle-of-Attack Range of 8° to 90°.” I - High-Wing Model B. NASA CR-3097 Sept. 1979
- Mulcay William Jr. Rose Robert A. “Rotary Balance Data for a Typical Single-Engine General Aviation Design for an Angle-of-Attack Range of 8° to 90°.” I - Low-Wing Model C. NASA CR-3200 Oct. 1980
- Bihrle William Jr. Barnhart Billy Pantaaon Paul “Static Aerodynamic Characteristics of a Typical Single-Engine Low-Wing General Aviation Design for an Angle-of-Attack Range of −8° to 90°.” NASA CR-2971 July 1978