Helicopter Performance, Stability, and Control |
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Page 395
... Pressure Distributions on Four NACA 64A - Series Airfoil Sections at Angles of Attack as High as 28 ° , NACA TN 3162 , 1954 . compression waves , as shown in Figure 6.16 . The initial expansion wave is generated by the high nose peak on ...
... Pressure Distributions on Four NACA 64A - Series Airfoil Sections at Angles of Attack as High as 28 ° , NACA TN 3162 , 1954 . compression waves , as shown in Figure 6.16 . The initial expansion wave is generated by the high nose peak on ...
Page 489
... pressure ratio q / q , and the downwash angles induced by the main rotor and fuselage , EMH and EFH These terms must ... Pressure Ratio The dynamic pressure at the horizontal stabilizer , q , is usually less than the free- stream value ...
... pressure ratio q / q , and the downwash angles induced by the main rotor and fuselage , EMH and EFH These terms must ... Pressure Ratio The dynamic pressure at the horizontal stabilizer , q , is usually less than the free- stream value ...
Page 491
... pressure ratio , making the distribution unsymmetrical and producing some values above unity , especially behind the advancing side of the rotor disc . The effect of the rotor can be even more dramatic for those speed conditions where ...
... pressure ratio , making the distribution unsymmetrical and producing some values above unity , especially behind the advancing side of the rotor disc . The effect of the rotor can be even more dramatic for those speed conditions where ...
Contents
AERODYNAMICS OF HOVERING FLIGHT | 1 |
AERODYNAMICS OF VERTICAL FLIGHT | 93 |
AERODYNAMICS OF FORWARD FLIGHT | 119 |
Copyright | |
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a₁ aerodynamic aircraft airfoil analysis angle of attack autorotation B₁ blade element calculated Chapter characteristics charts chord climb collective pitch Colo CT/O curve cyclic pitch damping derivatives disc loading drag coefficient engine equation example helicopter Figure of Merit flight conditions forward flight forward speed ft/sec ft² function fuselage gross weight ground effect H-force Helicopter Rotor hinge offset horizontal stabilizer ideal twist increase induced velocity knots lb/ft/sec level flight lift coefficient Mach number main rotor maneuver maximum lift coefficient method Mtip NACA nondimensional oscillation parameters pilot pitching moment power required radius rate of descent reported in reference Reynolds number rotation rotor thrust shaft shown in Figure sideslip stall tail rotor takeoff tilt tip path plane tip speed ratio torque trim conditions V₁ vortex wake wind tunnel wind tunnel tests wing zero ΟΥ ΩΡ дв ді дм др ду дх