A higher order panel method for linearized supersonic flow-Reference-Cited by-同舟云学术

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A higher order panel method for linearized supersonic flow

Published:1976-07-14 Issue: Volume: Page:
ISSN:
Container-title:9th Fluid and PlasmaDynamics Conference
language:
Short-container-title:

Author:

EHLERS F.¹,JOHNSON F.¹,RUBBERT P.¹

Affiliation:

1. Boeing Co., Seattle, Wash.

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1976-381

Reference18 articles.

1. 10-15-58L computed by source panel

2. attack andyaw. Figure 23. Wing pressure distribution for wing-body combination of NASA Memo 10-15-581. computed by source panel method a t span location y/s = 0.3376.SOURCEPANEL METHOD 1 EXPERIMENT.NASAMEMO

3. 10-15-581 computed by source panel

4. 10-15-58L computed by source panel

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