By NAVY AEROBALLISTICS ADVISORY COMMITTEE
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Extra info for Proceedings of the Navy Symposium on Aeroballistics (10th)
Sample text
In a design code. For example, Figure 5 is a computer-generated plot of aerodynamic data which has been processed for use by a 6 degreeof-freedom trajectory code in order to avoid use of inefficient tabular storage. The utility of conterm porary interpolation methods can be illustrated by considering a simple but widely used rapid design technique for predicting invi&cid aerodynamic loads at supersonic and hypersonic speeds. Using a combination of tangent wedge or tangent cone and modified Newtonian methods, the pressure on the windward surface of 12 1lh Nay Symposium on Aeroballistics Vol.
CONSERVATIVE IN NATURE OFTEN MISUSED IN TERMS OF APPLICATION OUTSIDE RANGE OF VALIDITY ACCURACY OF DATA CAN BE COMPROMISED BY FACILITY FLOW QUALITY, INSTRU. , SUCCESSFUL) FOR ALL VEHICLE GEOMETRIES AND SPEED REGIMES CANNOT BE CONFIDENTLY EXTRAPOLATED TO YIELD NONLINEAR TRENDS IN AERODYNAMIC DATA GROUND TEST FACILITIES DO NOT PROVIDE FULL-SCALE REYNOLD'S NUMBER SIMULATION FOR ALL TACTICAL AND STRATEGIC FLIGHT ENVIRONMENTS! Figure 1. Sources of Aerodynamic Design Datae will be limited to solutions of the inviscid governing equations.
A few of the results obtained by the method are presented The first case considered flow through a nozzle as reported by Boldman et al. (Ref. 21). The nozzle configuration consists of a 300 conical convergent section, a circular arc throat section and a 150 conical divergent section. , and the stagnation pressure and temperature were 300 psia and 9700R, respectively. I The predicted heat-transfer coefficient using the present method of solution is compared with the experimental data and the solutions obtained using the Elliott, Bartz and Silver (Ref.