NASA Technical Note, Issues 8236-8244National Aeronautics and Space Administration., 1976 - Aeronautics |
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Common terms and phrases
analysis angle of attack angle of sideslip attack vane boundary Boundary Errors buckling calculated calibration CARD CD.B characteristics chondrite Classification Map clusters coefficient configuration corner crack cross-sectional curve data set Default deflection Density Slicing diffuser DODOO drag DUCT effects ELLTAB equation error flap Fowler flap fracture function Ground Truth Map INPUT DATA INPUT PARAMETER IPAGE ISEC EQ isogrid KEXP Linear Linear Classifier LINECT loading M/SEC Mach number Maximum Likelihood meteorite METERS NASA NCHECK nose boom NSECT OPT'N output percent performance pixel plotted RECT rectangular reference Reynolds number RNREF SECT SHAPE sideslip vane Similarity Matrix similarity measures specimens spectral spoiler spoiler effectiveness stiffening grid stress stress-intensity factor subroutine surface-crack Table techniques test section training samples transonic turning vanes U.S. Customary Units unsupervised V/STOL vector velocity vent lip wind tunnel x/dm
Popular passages
Page 160 - Use of Short Flat Vanes for Producing Efficient Wide-Angle Two-Dimensional Subsonic Diffusers.
Page 11 - 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 7 - NASA Langley Research Center Hampton, VA 23665 11. Contract or Grant No. 13. Type of Report and Period Covered 12.
Page 58 - The ratio of the area of a circle to the square of its diameter...
Page 11 - AERODYNAMIC DESIGN GUIDELINES AND COMPUTER PROGRAM FOR ESTIMATION OF SUBSONIC WIND TUNNEL PERFORMANCE This program was developed as an aid In the design and analysis of subsonic wind tunnels.
Page 160 - Reneau, LR, Johnston, JP, and Kline, SJ, "Performance and Design of Straight, Two-Dimensional Diffusers,
Page 17 - Reubush, David E.: Experimental Study of the Effectiveness of Cylindrical Plume Simulators for Predicting Jet-On Boattail Drag at Mach Numbers up to 1.30.
Page xi - Category 34 19. Security Qassif. (of this report) 20 Security Classif. (of this page) Unclassified Unclassified 21. No. of Pages 22.
Page 16 - Kilgore, Robert A.; Adcock, Jerry B.; and Ray, Edward J.: Simulation of Flight Test Conditions in the Langley Pilot Transonic Cryogenic Tunnel. NASA TN D-7811, 1974.
Page 19 - An investigation of anomalies observed in wind-tunnel tests of a blunt body at transonic and supersonic speeds was conducted at Mach numbers from 0.20 to 2.16.