Wind tunnel tests of quad-rotor autogyro model

• Autorzy: Krzysiak A.

Identyfikatory

DOI

10.5604/01.3001.0010.2819

• Języki publikacji: EN

Abstrakty

EN

The wind tunnel investigation of basic aerodynamic characteristics as well as flow visualization tests of the innovative quad-rotor autogyro model is presented. The wind tunnel measurements of aerodynamic characteristics were carried out using 6-component internal strain-gauge balance. In the area of the main rotor and quad-rotors, the flow visualization tests were performed by PIV (Particle Image Velocimetry) System. The work was carried out in cooperation with the Lublin University of Technology, which provided a model of gyroplane manufactured according to their own concept. In the experimental study an influence of quad-rotors as well as pusher propeller on the autogyro model characteristics were determined by measurements aerodynamic forces and moments for a number of selected model configurations. The wind tunnel experimental tests were performed in the Institute of Aviation low speed wind tunnel T-1, characterized by 1.5 m diameter test section. The investigations were carried out for undisturbed flow velocity V∞ = 12.5 m/s, which corresponds to the Reynold’s number, Re = 0.82 * 106 referred to 1 m, The angles of attack used in the experiment were implemented in two ranges -40 ≤ α \ ≤ 20 and 00≤ α ≤ 130, with a sideslip angle β = 0. The tests showed that the flow induced by quad-rotors interfered with the flow induced by the main rotor changing the autogyro aerodynamic characteristics.

Słowa kluczowe

EN

transport; autogyro; quad-rotor; aerodynamic characteristics

PL

transport; charakterystyka aerodynamiczna

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2017
• Tom: Vol. 24, No. 1
• Strony: 231--238
• Opis fizyczny: Bibliogr. 8 poz., rys.

Twórcy

autor

Krzysiak A.

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.:[phone], fax: [phone]

Bibliografia

• [1] Leishman, J. G., Principles of Helicopter Aerodynamics, Cambridge University Press, 2000.
• [2] Wheatey, J. B., Hood, M. J., Full-Scale Wind-Tunnel Tests of Autogyro Rotor, NACA Report No. 515, 1935.
• [3] Charnov, B. H., From Autogyro to Gyroplane, Westport Conn, 2003.
• [4] Harrison, J. P., The Cierva Autodynamic Rotor, NASA Report No. TP-218714, 2015.
• [5] Jefflewis Net., Autogyro History and Theory, https://pl.scribd.com/document/254272804/Autogyro-History-and-Theory.
• [6] Dziubiński, A., Ulma, D., Żurawski, R., CFD Analysis of Tail Surface Modifications and Rudder Deflection Influence on I-28B Gyroplane at High Angle of Sideslip, Proceedings of AHS International's Annual Forum & Technology Display, Palm Beach, pp. 808-813, 2016.
• [7] Stalewski, W., Sznajder, J., Possibilities of Improvement of Directional Control Effectiveness of Light Gyroplane at High-Angle-of-Attack Flight Conditions, Transactions of Institute of Aviation, No. 218, pp. 77-85, 2011.
• [8] Stryczniewicz, W., Placek, R., Szczepaniak, R., PIV Measurements of Flow Separation over Laminar Airfoil at Transonic Speeds, Journal of KONES, 2016, Vol. 23, No. 1, pp. 329-335.

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017).