Effect of camber on the aerodynamics of adaptive-wing micro air vehicles

Research output: Contribution to journalArticle

36 Citations (Scopus)

Abstract

Four microair vehicle wind-tunnel models were built with 3, 6, 9, and 12% camber, all based upon the S5010-TOP24C-REF thin, cambered-plate airfoil. These models were tested in the Low Speed Wind Tunnel at angles of attack ranging from 0 to 35 deg and velocities of 5, 7.5, and 10 m/s, corresponding to mean aerodynamic chord Reynolds numbers of 5 × 104, 7.5 × 104, and 1 × 105, respectively. Aerodynamic coefficients CL, CD, CM and lift-to-drag ratio (L/D) were obtained and plotted vs angle of attack for all of the cambers at each velocity. Large positive, nose-up pitching moment coefficients were found with all cambers at the lowest Reynolds number. These results have been verified with flight tests of micro air vehicles utilizing these airfoils. The 3% camber wing gives the best lift-to-drag ratio of the four cambers and theoretically would be the optimal choice for high-speed, efficient flight. It is theorized that the 6 and 9% camber wings will give the best low-speed performance because of their high lift-to-drag ratios and mild pitching moments near their stall angles of attack.

Original languageEnglish (US)
Pages (from-to)1537-1542
Number of pages6
JournalJournal of Aircraft
Volume42
Issue number6
DOIs
StatePublished - Nov 2005

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Micro air vehicle (MAV)
Cambers
Aerodynamics
Angle of attack
Drag
Airfoils
Wind tunnels
Reynolds number

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Effect of camber on the aerodynamics of adaptive-wing micro air vehicles. / Null, W.; Shkarayev, Sergey V.

In: Journal of Aircraft, Vol. 42, No. 6, 11.2005, p. 1537-1542.

Research output: Contribution to journalArticle

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abstract = "Four microair vehicle wind-tunnel models were built with 3, 6, 9, and 12{\%} camber, all based upon the S5010-TOP24C-REF thin, cambered-plate airfoil. These models were tested in the Low Speed Wind Tunnel at angles of attack ranging from 0 to 35 deg and velocities of 5, 7.5, and 10 m/s, corresponding to mean aerodynamic chord Reynolds numbers of 5 × 104, 7.5 × 104, and 1 × 105, respectively. Aerodynamic coefficients CL, CD, CM and lift-to-drag ratio (L/D) were obtained and plotted vs angle of attack for all of the cambers at each velocity. Large positive, nose-up pitching moment coefficients were found with all cambers at the lowest Reynolds number. These results have been verified with flight tests of micro air vehicles utilizing these airfoils. The 3{\%} camber wing gives the best lift-to-drag ratio of the four cambers and theoretically would be the optimal choice for high-speed, efficient flight. It is theorized that the 6 and 9{\%} camber wings will give the best low-speed performance because of their high lift-to-drag ratios and mild pitching moments near their stall angles of attack.",
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