A Semiempirical Method For Predicting Aerodynamics Of Trailing Edge Flaps
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A Semiempirical Method for Predicting Aerodynamics of Trailing Edge Flaps
An improved semiempirical method has been developed to estimate the static aerodynamics of configurations that use a trailing edge flap for control. The method is based on deflecting the full aft-located lifting surface an amount that allows the normal force coefficient to be equal to that generated by the deflected flap. A transfer in pitching moments and a modified axial force coefficient is arrived to complete the set of static aerodynamics . The method to give satisfactory results over the practical range that trailing edge flaps are contemplated for use. However, additional wind tunnel data is needed to refine and expand the applicability of the method. This is particularly true for transonic Mach numbers and for supersonic Mach numbers where the angle of attack and control deflection are of the same.
A Semiempirical Method for Predicting Aerodynamics of Trailing Edge Flaps
An improved semiempirical method has been developed to estimate the static aerodynamics of configurations that use a trailing edge flap for control. The method is based on deflecting the full aft-located lifting surface an amount that allows the normal force coefficient to be equal to that generated by the deflected flap. A transfer in pitching moments and a modified axial force coefficient is arrived to complete the set of static aerodynamics . The method to give satisfactory results over the practical range that trailing edge flaps are contemplated for use. However, additional wind tunnel data is needed to refine and expand the applicability of the method. This is particularly true for transonic Mach numbers and for supersonic Mach numbers where the angle of attack and control deflection are of the same.
The 2002 Version of the Aeroprediction Code
A new version of the aeroprediction code (APC), the AP02, has been developed to address the requirements arising from advanced weapon concepts. The AP02 was formed by adding significant new technology and several productivity improvements to the previous version of the APC, the AP98. New technology added included 6 and 8 fin aerodynamics, improved nonlinear aerodynamics, improved pitch damping predictions, improved power-on base drag estimates, base-bleed effect on base drag estimation, improved axial force of nonaxisymmetric bodies and trailing-edge flap capability. Other improvements and productivity enhancements include an aerodynamic smoother, ballistic and three degree-of-freedom simulation modules as well as refinements for the pre- and post-processor for inputs and outputs of the AP02. Comparison of the predicted aerodynamics of the AP02 to AP98 and experimental data showed the AP02 to be slightly better than the AP98 in most cases that both codes would handle. However, due to the additional new technology incorporated into the AP02, many new options are available in the AP02 that are not available in the AP98. Therefore, the AP02 is more robust and, on average, is slightly more accurate than the AP98 in predicting aerodynamics of weapons.