Estimation Of Longitudinal Moment Derivatives Of Missile Configuration Using Semi Free Flying Technique

A Semi-Free Dynamic Flying Test Technique Has Been Used To Estimate The Pitching Moment Derivatives Of A Missile Model. Wind Tunnel Tests Were Carried Out On A 1 :8 Scale Model Of PJ08 Missile Configuration. The Pitching Moment Derivatives Were Estimated From The Angular Motion Responses Of The Model To Doublet Input Using MLE Method. The Results Of Tests On Configuration 1 For Three CG Positions Are Detailed

Dynamic Wind Tunnel Testing Of A Flexible Delta Wing

Dynamic Wind Tunnel Testing Of A Flexible Delta Wing Model W3.Carried Out To Generate Experimental Data 3To Be Used By ; The Aero-Servo-Elastic Analysis Group Of ADA . This Report Details Model Eoastruztion, Instrumentation, And Wind Tunnel Testing As Well As The Analysis Carried Out To Obtain Transfer Function As From Wind Tunnel Test Data

Stability and control derivatives of Light Canard Research Aircraft (LCRA)

From the geometric data of NAL's Light Canard Research Aircraft (Rutan Long-Ez), its stability and control derivatives were estimated for various flight conditions using analytical/ empirical procedures . These estimated values would serve as basic data and would be used for designing optimal control inputs for generating flight test data for parameter estimation . This basic data would be compared with the flight test results to ascertain the accuracy of the analytical estimation procedures for this type of configurations

A Novel Method of Estimating leutral Point Using Dynamic Wind Tunnel Simulation

This report presents a novel method of estimating neutral point of an aircraft using Dynamic wind tunnel simulation. The method uses pitch motion and lift force responses13; of dynamically scaled aircraft model flown in the wind tunnel for estimating Pitching moment and lift derivatives from which neutral point is deduced. The advantage of this method is the simplicity of model instrumentation and testing. The method is demonstrated using a generic delta winged aircraft model flown with pitch DOF in dynamic wind tunnel. Comparison of estimated neutral point location with that obtained from static tests on similar configuration show good agreement

DO 28D1 aircraft parameter identification

Analysis of flight test data obtained for the identification of DO 28D1 research aircraft of TU Braunschweig is detailed in this report. The data analysis was done to understand aspects related to the aircraft parameter identification from flight test data, particularly in the context of this aircraft's instrumentation and data acquisition and for planning future flight tests for obtaining flight data for13; identification purposes

NALLA 1 Longitudinal stick-free stability

The estimation of elevator hinge moment derivatives and the stick-free neutral point of NAL Light Aircraft Conf. 1 (NALLA-1) is detailed in this report. These have been estimated using ESDU data sheets. Horn balance effects and suitable horn balance for minimising the neutral point shift are also estimated

Generation of Comprehensive Aerodynamic Data Using Dynamic Wind Tunnel Simulation

This report presents a novel method of generating13; comprehensive aerodynamic data of aircraft using Dynamic13; wind tunnel simulation. The method combines measurement13; of motion and force responses of aircraft model to control13; inputs. The aerodynamic data generated includes trimmed13; Lift characteristics, Longitudinal stability derivatives, Neutral point, and large amplitude Lift and pitching moment responses to arbitrary control surface inputs.13; The advantage of the method is the simple instrumentation and wind tunnel tests.13; The method is demonstrated using a generic delta winged aircraft model with pitch DOF flown in a low speed dynamic wind tunnel. The model pitch attitude and Lift responses to elevon inputs are measured and used to deduce longitudinal aerodynamic data. Comparison of these13; results with Datcom estimates and static test data of a similar configuration show good agreement, thus validating the method

Dynamic wind tunnel testing of a flexible wing model 13; 13;

The current state-of-art in the design of modern combat aircraft is to use CCV concepts to obtain high performance at lower weight. This demands an unstable aerodynamic configuration with the stability provided artificially by the control system. This needs longitudinal servo-actuators of high bandwidth. With lower structural frequencies there is scope for interaction and aeroservoelastic problems could occur. This document details a simple experimental study13; of servoelastically exciting a wing to yield transfer function data. The aim of these experiments is to provide a vehicle for generating experimental data for validating aeroservoelastic codes and to obtain insight of flutter I aeroservoelastic phenomena through scaled models.13

Estimation Of Roll Derivatives Of A 1/15 Scale LCA Model By Dynamic Wind Tunnel Simulation Technique

The Dynamic Wind Tunnel Simulation Conept Has Been Used To Estimate The Roll Damping Derivatives Of A 1/15 Scale Wind Tunnel Model Of LCA . The Experimental Results Are Compared With Existing Analytical/ Static Wind Tunnel Data For The Same Configuration

Identification of the dynamics of a flexible delta wing model

This paper details the identification of the dynamics of a flexible delta wing model. The wing model was tested in the low speed dynamic wind tunnel of NAL at three dynamic pressure conditions. The model was aerodynamically excited by driving its trailing edge control surface with sinesweep signals. Time domain time series identification technique was used to identify the flexible wing dynamics from its responses. Lower order models were deduced from the identified higher order models using balanced reduction technique. The identified dynamics showed that the frequency and damping of the dominant mode varied appreciably for the tested dynamic pressure range