NASA MemorandumNational Aeronautics and Space Administration, 1958 - Aeronautics |
From inside the book
Results 1-5 of 5
Page 13
... Mach numbers up to the maximum speed of the tunnel ( approximate Mach number , 1.2 ) . The spray bar was similar in design to the one used in the 4- by 8 - inch open jet just men- tioned previously . In figure 6 ( a ) the spray is shown ...
... Mach numbers up to the maximum speed of the tunnel ( approximate Mach number , 1.2 ) . The spray bar was similar in design to the one used in the 4- by 8 - inch open jet just men- tioned previously . In figure 6 ( a ) the spray is shown ...
Page 27
L - 58-148a Figure 2.- Concluded . Mach number , 2.36 Air flow Mach number , 2.87. ( b ) Bodies added to wing . Approximate Mach number , 0.65 Approximate Mach number , 0.70. 27.
L - 58-148a Figure 2.- Concluded . Mach number , 2.36 Air flow Mach number , 2.87. ( b ) Bodies added to wing . Approximate Mach number , 0.65 Approximate Mach number , 0.70. 27.
Page 33
... fixed at 10 - percent - chord line ; fluorescent - oil film pattern on sur- face of wing after model was sprayed and spray bar retracted . Figure 6.- Conclude L - 58-157a Approximate Mach number , 0.80 Approximate Mach number , 0.85. 33.
... fixed at 10 - percent - chord line ; fluorescent - oil film pattern on sur- face of wing after model was sprayed and spray bar retracted . Figure 6.- Conclude L - 58-157a Approximate Mach number , 0.80 Approximate Mach number , 0.85. 33.
Page 34
... 450 swept back - wing model in a 4- by 8 - inch open jet . Angle of attack , 20 ; transition natural . L - 58-153a ( b ) Approximate Mach number ,. Approximate Mach number , 0.65 Approximate Mach number , 0.70 Approximate Mach number , 0.75.
... 450 swept back - wing model in a 4- by 8 - inch open jet . Angle of attack , 20 ; transition natural . L - 58-153a ( b ) Approximate Mach number ,. Approximate Mach number , 0.65 Approximate Mach number , 0.70 Approximate Mach number , 0.75.
Page 35
L - 58-153a ( b ) Approximate Mach number , 0.80 . Interval between successive frames ( beginning at top left photograph and reading down ) , 0.5 second . Figure 7.- Concluded . L - 58-154a Figure 8.- Temperature - sensitive fluorescent ...
L - 58-153a ( b ) Approximate Mach number , 0.80 . Interval between successive frames ( beginning at top left photograph and reading down ) , 0.5 second . Figure 7.- Concluded . L - 58-154a Figure 8.- Temperature - sensitive fluorescent ...
Other editions - View all
Common terms and phrases
3-17-59L National Aeronautics 30-percent-chord line 8-inch open jet Aerodynamic 9.2.2 Angle of attack Approximate Mach number Boundary-Layer Char BOUNDARY-LAYER FLOW VISUALIZATION characteristics china clay Clair Avenue desired test conditions Donald Donald L Dow Corning E-H4 lamp unit flow patterns flow-visualization fluorescein fluorescent additive Fluorescent Green C.H. fluorescent-oil film method Fluorescent-oil film pattern gear oil Navy high-powered wind tunnels hydrofoil indicated Katzoff kerosene Kodak Tri-X film laminar Langley 8-foot transonic Langley Field Langley Research Center Langley Unitary Plan leading edge lubricating oil method is especially NACA NACA RM NASA MEMO number of 0.90 observed oil Navy Symbol pattern on surface Plan wind tunnel radiometer reach desired test region require less experience silicone fluid single test speed spray bar spraying technique surface of cambered TECHNIQUES FOR BOUNDARY-LAYER Tests in Langley transition fixed transition natural transonic tunnel tunnels that require turbulent areas Type K-24 camera ultraviolet light Unitary Plan wind viscosity wing model Wratten Filter
Popular passages
Page 20 - Chemical solids as diffusible coating films for visual indication of boundary layer transition in air and water. R. & M.
Page 20 - The use of a luminescent lacquer for the visual indication of boundary-layer transition.
Page 20 - ... and Cruciform-Wing and Body Combinations. NACA Rep. 962, 1950. B-3. Heaslet, Max A.; Lomax, Harvard; and Spreiter, John R.: Linearized Compressible-Flow Theory for Sonic Flight Speeds. NACA Rep. 956, 1950. B-4. Jones, Robert T.: Estimated Lift-Drag Ratios at Supersonic Speed. NACATN 1350, 1947. B-5. Vincenti, Walter G.; Nielsen, Jack N.; and Matteson, Frederick H.: Investigation of Wing Characteristics at a Mach Number of 1.53. I— Triangular Wings of Aspect Ratio 2. NACA RM A7I10, 1947. B-6....
Page 20 - The Observation of Temperature Distributions and of Thermal Radiation by Means of Non-Linear Phosphors," /. Opt. Soc. Am., 39, no. 12, pp. 1011-1019 (December, 1949). 59. LC Bradley, "A Temperature-Sensitive Phosphor Used to Measure Surface Temperatures in Aerodynamics,
Page 8 - Boundary-layer flow patterns on a wing were observed and photographed in the Langley high-speed 7- by 10-foot tunnel for a Mach number range from 0.6 to 0.92, with the angle of attack fixed for each test.
Page 20 - Investigation at Transonic Speeds of Aerodynamic Characteristics of an Unswept Semielliptical Air Inlet in the Root of a U5° Sweptback Wing.
Page 4 - Where emphasis is on determining the direction of boundary -layer crossflows, it may help to apply the oil in small discrete dabs which then stretch out into lines that show the direction of the surface shear.