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| 086 | 0 | ⊔ | ‡aD 301.45/46-2:66-230 |
| 088 | ⊔ | ⊔ | ‡aAF 33(615)-2902 |
| 088 | ⊔ | ⊔ | ‡aAD 0656492 |
| 088 | ⊔ | ⊔ | ‡aAFFDL TR 66-230 |
| 100 | 1 | ⊔ | ‡aMoore, Dave R., ‡eauthor. |
| 245 | 1 | 0 | ‡aInvestigation of ablation effects on hypersonic dynamic stability of a 10 cone / ‡cDave R. Moore, Charles J. Stalmach, Jr., Thomas C. Pope. |
| 264 | ⊔ | 1 | ‡aWright-Patterson Air Force Base, Ohio : ‡bAir Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, ‡c1967. |
| 300 | ⊔ | ⊔ | ‡axii, 74 pages : ‡billustrations, figures, tables ; ‡c28 cm. |
| 336 | ⊔ | ⊔ | ‡atext ‡btxt ‡2rdacontent |
| 337 | ⊔ | ⊔ | ‡aunmediated ‡bn ‡2rdamedia |
| 338 | ⊔ | ⊔ | ‡avolume ‡bnc ‡2rdacarrier |
| 490 | 0 | ⊔ | ‡aAir Force Flight Dynamics Laboratory (U.S.). Technical report ; ‡vAFFDL-TR-66-230 |
| 500 | ⊔ | ⊔ | ‡a"The work was performed under USAF Contract No. AF 33(615)-2902, Project No. 8219, Stability and Control Investigations, Task 821902, Aerodynamic Stability and Control." |
| 500 | ⊔ | ⊔ | ‡a"Vought Aeronautics Division. LTV Aerospace Corporation." |
| 500 | ⊔ | ⊔ | ‡a"January 1967." |
| 520 | ⊔ | ⊔ | ‡aAn experimental program has been conducted in the LTV Hypervelocity Wind Tunnel at M = 17 to investigate the effects of ablation product characteristics and thermal lags on re-entry vehicle dynamic stability. The free oscillation method of dynamic stability measurement was used and the ablation processes were simulated by the controlled mass injection through four sections of the porous model skin. The flow rates through the top and bottom quadrants were oscillated at the same frequency and at an amplitude proportional to the model motion. The thermal lag effect was investigated with nitrogen injection into nitrogen tunnel flow at several different mass flow rates and phase angles between the oscillating mass flow and the body motion. The ablation product study was conducted by injecting gases other than nitrogen with specific heat ratio and molecular weight being the test parameters in addition to mass flow rate. The results obtained from these tests indicate significant effect on dynamic stability with both injection phase angle and some characteristics of the injected gas. The effects of model frequency, Reynolds number and mass injection distribution were also investigated and some static pressure measurements were made near the aft of the model. Appendices to the report contain tabulations of the pertinent data and discussions of supporting analytical studies and data analysis. |
| 538 | ⊔ | ⊔ | ‡aMode of access: Internet. |
| 583 | 1 | ⊔ | ‡awill digitize ‡c20200915 ‡zQueued for digitization ‡cSeptember 15, 2020 ‡5miu ‡2pda |
| 650 | ⊔ | 0 | ‡aAerodynamics, Hypersonic. |
| 650 | ⊔ | 0 | ‡aWind tunnels. |
| 650 | ⊔ | 0 | ‡aStability of rockets. |
| 650 | ⊔ | 0 | ‡aSpace vehicles ‡xAtmospheric entry. |
| 650 | ⊔ | 0 | ‡aAblation (Aerothermodynamics) |
| 700 | 1 | ⊔ | ‡aPope, Thomas C., ‡eauthor. |
| 700 | 1 | ⊔ | ‡aStalmach, Charles J., ‡cJr., ‡eauthor. |
| 710 | 2 | ⊔ | ‡aAir Force Flight Dynamics Laboratory (U.S.), ‡eissuing agency. |
| 710 | 2 | ⊔ | ‡aLTV Aerospace Corporation, ‡esponsor. |
| 730 | 0 | ⊔ | ‡aTechnical Report Archive & Image Library (TRAIL) |
| 776 | 0 | 8 | ‡iOnline version: ‡aMoore, Dave R. ‡tInvestigation of ablation effects on hypersonic dynamic stability of a 10° cone. ‡d[Wright-Patterson Air Force Base, Ohio, Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1967] ‡w(OCoLC)741881910 |
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