Linearized theory is applied to determine lift coefficient and efficiency of heat addition and to optimize wing profile, angle of attack, and heat addition; comparison with conventional ramjet and wing shows ramjet to be superior on range basis up to Mach number of about 8. (Derivation of Effect of Supersonic Underwing Heat Addition from Potential-Flow Equations)
Analysis and evaluation of supersonic underwing heat addition
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 3-17-59E
1959
55 pages
Appendix C
Report
English
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Underwing Compression Vortex-Attenuation Device
NTRS | 1994
|Underwing Compression Vortex-Attenuation Device
Online Contents | 1994