NASA Technical Paper, Issue 2457 |
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Page 113 - Contract or Grant No. 12. Sponsoring Agency Name and Address National Aeronautics and Space Administration Washington, DC 20546-0001 13. Type of Report and Period Covered Technical Paper 14.
Page 19 - Braslow, Albert L.; and Knox, Eugene C.: Simplified Method for Determination of Critical Height of Distributed Roughness Particles for Boundary -Layer Transition at Mach Numbers From 0 to 5.
Page 19 - Blackwell, James A., Jr.: Preliminary Study of Effects of Reynolds Number and Boundary-Layer Transition Location on Shock-Induced Separation.
Page 19 - Shapiro, Ascher H.: The Dynamics and Thermodynamics of Compressible Fluid Flow. Volume II.
Page 19 - Nose Inlets at High-Subsonic Mach Numbers and at Mach 1.2. NACA RM L9L23a, 1950. See also NASA TM X-2917, 1974. 186. RE, RJ, An Investigation of Several NACA 1-Series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29. NASA TM X-2917, Mar. 1974. 187. BECKER, JV, and BAALS, DD, The Aerodynamic Effects of Heat and Compressibility in Internal Flow Systems, and High-Speed Tests of a Ram-Jet System. NACA Rept. 773, 1943. (Supersedes NACA ACR of Sept. 1942). 188. BREVOORT, MJ, et al., The Effect of Altitude...
Page 113 - Installation effects of long-duct pylon-mounted nacelles on a twin-jet transport model with swept supercritical wing...
Page 19 - Results of Design Studies and Wind Tunnel Tests of High-Aspect-Ratio Supercritical Wings for an Energy Efficient Transport.
Page 19 - Henne, Preston A.; Dahlin, John A.; Peavey, Charles C.; and Gerren, Donna S.: Configuration Design Studies and Wind Tunnel Tests of an Energy Efficient Transport With a High-Aspect-Ratio Supercritical Wing. NASA CR-3524, 1982.