Supersonic wind tunnel tests of two rocket propelled projectile models
Two models of rocket propelled projectiles have been tested in the Galcit 2 1/2 inch supersonic wind tunnel at a Mach Number of 3.06, and angles of attack from 0° to 10°. Variations of lift, drag, pitching moment, and position of center pressure with angle of attack have been obtained for each model...
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ndltd-CALTECH-oai-thesis.library.caltech.edu-49102019-12-22T03:08:54Z Supersonic wind tunnel tests of two rocket propelled projectile models Fossier, Mike Walter Small, John Two models of rocket propelled projectiles have been tested in the Galcit 2 1/2 inch supersonic wind tunnel at a Mach Number of 3.06, and angles of attack from 0° to 10°. Variations of lift, drag, pitching moment, and position of center pressure with angle of attack have been obtained for each model. A strain gage balance system, which was designed to measure the forces acting on the models was found to be entirely satisfactory for this purpose. The results were found to agree very closely with the small perturbation theory for supersonic flow. 1947 Thesis NonPeerReviewed application/pdf https://thesis.library.caltech.edu/4910/1/Fossier_m_1947.pdf https://resolver.caltech.edu/CaltechETD:etd-12092008-082853 Fossier, Mike Walter and Small, John (1947) Supersonic wind tunnel tests of two rocket propelled projectile models. Engineer's thesis, California Institute of Technology. doi:10.7907/71EK-W641. https://resolver.caltech.edu/CaltechETD:etd-12092008-082853 <https://resolver.caltech.edu/CaltechETD:etd-12092008-082853> https://thesis.library.caltech.edu/4910/ |
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Two models of rocket propelled projectiles have been tested in the Galcit 2 1/2 inch supersonic wind tunnel at a Mach Number of 3.06, and angles of attack from 0° to 10°. Variations of lift, drag, pitching moment, and position of center pressure with angle of attack have been obtained for each model.
A strain gage balance system, which was designed to measure the forces acting on the models was found to be entirely satisfactory for this purpose.
The results were found to agree very closely with the small perturbation theory for supersonic flow.
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| author |
Fossier, Mike Walter Small, John |
| spellingShingle |
Fossier, Mike Walter Small, John Supersonic wind tunnel tests of two rocket propelled projectile models |
| author_facet |
Fossier, Mike Walter Small, John |
| author_sort |
Fossier, Mike Walter |
| title |
Supersonic wind tunnel tests of two rocket propelled projectile models |
| title_short |
Supersonic wind tunnel tests of two rocket propelled projectile models |
| title_full |
Supersonic wind tunnel tests of two rocket propelled projectile models |
| title_fullStr |
Supersonic wind tunnel tests of two rocket propelled projectile models |
| title_full_unstemmed |
Supersonic wind tunnel tests of two rocket propelled projectile models |
| title_sort |
supersonic wind tunnel tests of two rocket propelled projectile models |
| publishDate |
1947 |
| url |
https://thesis.library.caltech.edu/4910/1/Fossier_m_1947.pdf Fossier, Mike Walter and Small, John (1947) Supersonic wind tunnel tests of two rocket propelled projectile models. Engineer's thesis, California Institute of Technology. doi:10.7907/71EK-W641. https://resolver.caltech.edu/CaltechETD:etd-12092008-082853 <https://resolver.caltech.edu/CaltechETD:etd-12092008-082853> |
| work_keys_str_mv |
AT fossiermikewalter supersonicwindtunneltestsoftworocketpropelledprojectilemodels AT smalljohn supersonicwindtunneltestsoftworocketpropelledprojectilemodels |
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1719305153942650880 |