task 1.2b miniature trailing edge effectors for rotorcraft applications principal investigators...
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TASK 1.2b
MINIATURE TRAILING EDGE EFFECTORS FOR ROTORCRAFT APPLICATIONS
PRINCIPAL INVESTIGATORS
GEORGE LESIEUTREMARK MAUGHMER
MICHAEL KINZEL
MICHAEL THIEL
GRADUATE RESEARCH ASSISTANTS
GARY KOOPMANN
EARL DUQUE
BACKGROUND:
“REAL” GURNEY FLAPS
Gurney flap
Wing trailing-edge
BACKGROUND
• MINIATURE TRAILING-EDGE EFFECTORS (MiTEs)- MOVABLE TABS, PARTIAL SPAN- CONSIDERED BY VanDam, Eaton, others
• MiTEs HAVE POTENTIAL TO IMPROVE- ROTOR PERFORMANCE
• INCREASE MAX LIFT TO REDUCE RETREATING-BLADE STALL• REDUCE COMPRESSIBILITY EFFECTS ON ADVANCING SIDE
- VIBRATION CONTROL• SPANWISE & AZIMUTHAL LIFT DISTRIBUTIONS
TECHNICAL BARRIERS• ACTUATION (4/REV => 20 Hz FREQ.)• DYNAMIC PERFORMANCE NOT UNDERSTOOD• ROTOR PERFORMANCE EFFECTS
Active MiTE
Wing trailing-edge
Dist. from TE
Var
iabl
e H
eigh
t
OBJECTIVES
EXPLORE UTILITY OF ACTIVE GURNEY FLAPS
APPROACHES:
• AERODYNAMIC UNDERSTANDING:• EXPERIMENTAL: 2D STATIC / DYNAMIC• NUMERICAL: 2D STATIC / DYNAMIC
• POTENTIAL FOR ROTORCRAFT:• FLIGHT PERFORMANCE – IMPROVED PREDICTION METHODS
• IMPLEMENTATION: • ACTUATION
EXPECTED RESEARCH RESULTS:
• AERODYNAMIC EFFECTS OF SIZE AND LOCATION
• BETTER UNDERSTANDING OF GURNEY FLAP PHYSICS
• DETERMINE EFFECTS ON ROTOR PERFORMANCE
• DEVELOP VIABLE ACTUATION METHODS
• OBTAIN DYNAMIC WIND-TUNNEL DATA
EXPERIMENT: TRANSITION FIXED AT 5%c
EXPERIMENT: GURNEY LOCATION AND SIZE
GF HEIGHT0.005c0.01c0.02c
NUMERICAL INVESTIGATION: CFD STREAKLINES
NUMERICAL INVESTIGATION: CFD STREAKLINES
AERODYNAMIC MODELING OF MiTES:
, , c ( , ) = c ( ')l GF l GFM
' Stall
Stall Stall
• MACH NUMBER AERO. EFFECTS FOR A GURNEY FLAP
• CONSISTENT WHEN CONSIDERING ’
AERODYNAMIC MODELING OF MiTES:
INDICIAL RESPONSE AND HARIHARAN-LEISHMAN UNSTEADY FLAPPED AIRFOIL MODEL
• AVERAGED INDICIAL RESPONSE IS SIMILAR TO PLAIN FLAP
• ALLOW THE INVESTIGATION OF UNSTEADY PLAIN-FLAPPED AIRFOIL THEORIES
AERODYNAMIC MODELING OF MiTES:
UNSTEADY FLAPPED AIRFOIL MODEL APPLIED TO MiTES
k=0.14, M=0.1, =0deg k=0.5, M=0.6, =0deg
AERODYNAMIC MODELING OF MiTES:
UNSTEADY FLAPPED AIRFOIL - DYNAMIC STALL MODEL
DYNAMIC STALL MODELUNSTEADY FLAPPED AIRFOIL MODEL
CFD – OVERFLOW2
EFFECT OF MiTE POSITION:
(a) xMiTE=1.0c
(b) xMiTE=0.9c
• VORTEX STREET FORMS CREATES HIGH FREQ. OSCILLATIONS
• TRAILING EDGE PLACEMENT AGREES WELL WITH THEODORSEN CIRCULATORY THEORY
• UPSTREAM PLACEMENT HAS LARGE DYNAMIC LOADS AND INCREASED LAGS
(a)
(b)
PERFORMANCE ANALYSIS: OPTIMAL DEPLOYMENT STRATEGY
REASONABLE FOR STEADY ASSUMPTIONS, BUT NOT WHEN UNSTEADY AERO. AND DYN. STALL ARE CONSIDERED
PERFORMANCE ANALYSIS: FORWARD FLIGHT
PERFORMANCE ANALYSIS: MiTE DEPLOYMENT
PERFORMANCE ANALYSIS: FORWARD FLIGHT WITH VARIATIONS IN AIRFOIL TRANSITION RADIUS
NOTE: DEPLOYMENT IS SCHEDULED TO
MINIMIZE PITCHING MOMENT
PERFORMANCE ANALYSIS: EFFECT OF MiTE DRAG TO PERFORMANCE ENHANCEMENT
ACTUATOR DESIGN
• DESIGN FOR AERODYNAMIC BENEFITS– OPERATING FREQUENCIES OF 4 – 5 Hz
• APPLY TO A VR-12 AIRFOIL– HEIGHT: 0.01c
– LOCATION: 0.9c
Fig. from Johnson, W., Helicopter Theory
AERODYNAMIC FORCE ON THE FLAP
• Re = 4x106
• M = 0.45• HEIGHT: 0.02c• PER UNIT SPAN• ONLY DRAG
ACCURATELY MODELED
ACTUATOR ISSUES
• DESIGN CONSIDERATIONS• SIZE CONSTRAINTS• TOTAL WEIGHT• FREQUENCY REQUIREMENTS• CENTRIFUGAL FORCES
• ACTUATION METHODS UNDER CONSIDERATION• LINEAR DC ACTUATORS (VOICE COILS)• PIEZOELECTRIC• ROTARY/STEPPER MOTORS
VR-12 AIRFOIL
~14” CHORD
FLAP ACTUATION: AMPLIFIED PIEZO BENDER
Fp
Mh
Piezoelectric BenderCoupler
• TAPERED PIEZO BENDER• LEVER AMPLIFIER
• REQUIREMENTS• QUASISTATIC DISP. > 0.36”
• RESONANT FREQ
• > 20 Hz (4/rev)
• MODELS• PIEZO BEAM FOR DISP.
• R-R FOR RESONANCE FREQ.
LINEAR DC ACTUATORS
• MOVING COIL (NCC)
– MORE FORCE
– HEAVIER
Motion
Motion
• MOVING MAGNET (NCM)
– LESS FORCE
– LIGHTER
TESTING OF NCC ACTUATOR
- LASER VELOCIMETER USED
- BROADER FREQUENCY RANGE NEEDED
CURRENT CONCEPT
• CURRENT CONCEPT FOR NCC ACTUATOR
• LOCATE AS FAR AFT AS POSSIBLE
• SIMILAR DESIGN FOR THE NCM ACTUATOR
• OPTIMAL DIMENSIONS NEEDED
• REFINE SIMULATION MODEL
• BUILD PROTOTYPE OF NCC ACTUATOR
• TEST NCM ACTUATOR
• DEVELOP DESIGNS FOR OTHER ACTUATOR TYPES (i.e. PIEZO)
• DETERMINE COMPARISON CRITERIA
• DETERMINE OPTIMAL INPUT SIGNAL
• DEVELOP METHODS TO TEST UNDER CF LOADS
ACTUATION DESIGN - IMMEDIATE FUTURE
ACCOMPLISHMENTS
• WIND-TUNNEL MEASUREMENTS OF GURNEY FLAPS (2002)• CFD PREDICTION OF GURNEY FLAP PERFORMANCE (2003)• ACTUATION CONCEPTS EXPLORED (2002)• DYNAMIC CFD CALCULATIONS (2003-2004)• ROTOR PERFORMANCE ANALYSIS (2003-2004)
– INCLUDE DYNAMIC STALL MODEL– CONSIDER UNSTEADY MiTE MODEL
• INVESTIGATE MODELING UNSTEADY AERO. OF MiTES (2004)• MORE EXTENSIVE ACTUATION METHODS EXPLORED (2004-2005)
– LINEAR DC ACTUATORS– PIEZOELECTRIC
• BUILD MODELS OF ACTUATION SYSTEMS
• WIND-TUNNEL VERIFICATION OF ACTUATION METHODS
• EXTEND ACTUATION DESIGN TO FULL-SCALE ROTOR BLADE
2005-2006 PLANS
PUBLICATIONS• Maughmer, M., Lesieutre, G., Thepvongs, S., Anderson, W, Kinzel, M.,
“Miniature Trailing-Edge Effectors for Rotorcraft Applications”, AHS 59th Forum, Phoenix, AZ, May 2003.
• Kinzel, M., “Miniature Trailing-Edge Effectors for Rotorcraft Applications,” Mindbend 2004 Student Conference, University Park, PA, April 2004.
• Kinzel, M.P., “Miniature Trailing-Edge Effectors for Rotorcraft Applications,” M.S. Thesis, Dept. of Aerospace Eng., Penn State University, University Park, PA, 2004.
• Kinzel, M.P, Maughmer, M.D, Lesieutre, G.L, Duque, E.P.N, "Numerical Investigation of Miniature Trailing-Edge Effectors on Static and Oscillating Airfoils," AIAA Paper No. 2005-1039, 2005.
• Thiel, M., “Actuation of an Active Gurney Flap for Rotorcraft Applications,” Mindbend 2005 Student Conference, University Park, PA, April 2005.
• Maughmer, M., Lesieutre, G., Kinzel, M., “Miniature Trailing-Edge Effectors for Rotorcraft Performance Enhancement”, AHS 61th Forum, Grapevine, TX, June 2005.
FUTURE RESEARCH NEEDS• DEVELOPMENT OF UNSTEADY AERO. MODELS FOR THE UPSTREAM
PLACEMENT OF MITES• DYNAMIC WIND-TUNNEL DATA • COMPREHENSIVE ROTOR PERFORMANCE / APPLICATION ANALYSES• HIGH-FREQUENCY ACTUATION DESIGN• MITE SPECIFIC AIRFOIL DESIGN• OTHER POTENTIAL BENEFITS OF MITES FOR ROTORCRAFT
MiTE SCHEDULETASKS 2001 2002 2004 2005
STAGE ONE
WT TEST WITH FIXED GURNEY FLAP
CFD SOLUTIONS (FLUENT)
MODEL ACTUATOR DESIGN
STAGE TWO
TRANSONIC CFD SOLUTIONS
ROTOR PERFORMANCE
SPECAILIZED CFD (OVERFLOW)
STAGE THREEDEVELOP FULL SCALE ACTUATORS
DYNAMIC WT TESTING
SHORT TERMLONG TERMCOMPLETE
2003 2006
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