In order to balance this pitching moment the horizontal stabilizer must be somewhat larger than it would otherwise be, so that it can produce enough force to balance the negative pitching moment created by the trailing edge flaps.
32.
In order to balance this pitching moment the horizontal stabilizer must be somewhat larger than it would otherwise be, so that it can produce enough force to balance the negative pitching moment created by the trailing edge flaps.
33.
When the lift coefficient is zero an airfoil is generating no lift but a conventionally cambered airfoil generates a nose-down pitching moment, so the location of the center of pressure is an infinite distance behind the airfoil.
34.
One of the practical problems with the use of SERNs is the fact that they produce a pitching moment depending on the throttling of the engine, thereby requiring more control authority of the elevators and more complex control systems etc.
35.
With a lifting-canard type, the main wing must be located further aft of the center of gravity than a conventional wing, and this increases the downward pitching moment caused by the deflection of trailing-edge flaps.
36.
Thermal protection shield ( TPS ) heating in the vehicle's afterbody is usually not very high, but the geometry and unsteadiness of the vehicle's wake can significantly influence aerodynamics ( pitching moment ) and particularly dynamic stability.
37.
When the lift coefficient is zero an airfoil is generating no lift but a reflex-cambered airfoil generates a nose-up pitching moment, so the location of the center of pressure is an infinite distance ahead of the airfoil.
38.
21 . " New Methods for Predicting Nonlinear Lift, Center of Pressure, and Pitching Moment on Missile Configurations ", NSWCDD / TR-92 / 217, Jul1992 ( written with T . Hymer and L . Devan ).
39.
Since these wings are swept, as the shock cone moves inward, the lift vector moves forward as the outer, rearward portions of the wing are generating less lift . This results in powerful pitching moments and their associated required trim changes.
40.
The D-19's wing area was only slightly higher, with the result that the cambered G�ttingen 535, so decreasing the pitching moment; over the outer panels the thickness / chord ratio reduced continuously from 15 % to 8.
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