NASA technical note

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Page 44 - NASA Langley Research Center Hampton, VA 23665 11. Contract or Grant No. 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Technical Note National Aeronautics and Space Administration Washington, DC 20546 14.
Page 26 - The Dynamics and Thermodynamics of Compressible Fluid Flow. Vol. 1. The Ronald Press Co., 1953.
Page 65 - Chatterjee, A.; Tobias, CA; and Lyman, JT 1976: Nuclear Fragmentation in Therapeutic and Diagnostic Studies With Heavy Ions. Spoliation Nuclear Reactions and Their Applications, BSP Shen and M. Merker, eds., D. Reidel Publ. Co., pp. 169-191. Cleghorn, TF; Freier, PS; and Waddington, CJ 1968: The Energy Dependence of the Fragmentation Parameters and Mean Free Paths of Cosmic-Ray Nuclei With Z > 10. Canadian J. Phys., vol. 46, no. 10, pp. S572-S577.
Page 65 - Radiat. Res., vol. 115, pp. 347 360. Thomson, John F.; and Grahn, Douglas 1989: Life Shortening in Mice Exposed to Fission Neutrons and 7 Rays. VIII. Exposures to Continuous 7 Radiation. Radiat. Res., vol. 118, pp. 151-160. Todd, Paul; and Tobias, Cornelius A. 1974: Cellular Radiation Biology. Space Radiation Biology and Related Topics, Cornelius A. Tobias and Paul Todd, eds., Academic Press, Inc., pp. 141-196. Townsend, Lawrence W.; Wilson, John W.; Norbury, John W.; and Bidasaria, Hari B. 1984:...
Page 77 - ... one-third octave band and KQ is the measured takeoff noise path. The second correction term accounts for the effects of atmospheric sound absorption on the...
Page 60 - No. 11. Contract or Grant No. 12. Sponsoring Agency Name and Address National Aeronautics and Space Administration Washington, DC 20546-0001 13.
Page 53 - LOW SUBSONIC FLIGHT AND FORCE INVESTIGATION OF A SUPERSONIC TRANSPORT MODEL WITH A VARIABLE-SWEEP WING Delma C.
Page 16 - INCIDENCE, a, deq 20 (a) STATIC STALL ANGLE EXCEEDED (b) FIRST APPEARANCE OF FLOW REVERSAL ON SURFACE (c) LARGE EDDIES APPEAR IN BOUNDARY LAYER (d) FLOW REVERSAL SPREADS OVER MUCH OF AIRFOIL CHORD (e) VORTEX FORMS NEAR LEADING EDGE !f) LIFT SLOPE INCREASES (g) MOMENT STALL OCCURS (h) LIFT STALL BEGINS ( i ) MAXIMUM NEGATIVE MOMENT ( j ) FULL STALL k) BOUNDARY LAYER REATTACHES FRONT TO REAR ( I ) RETURN TO UNSTALLED VALUES Figure 27.- Dynamic stall events on NACA 0012 airfoil.

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