Free Flight Tests At Mach Numbers From 0 8 To 1 4 To Determine The Effect On Zero Lift Drag Of Increasing The Leading Edge Bluntness Of A 45 Degree Sweptback Wing Having An Naca 65a009 Airfoil
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Free Flight Tests At Mach Numbers From 0 8 To 1 4 To Determine The Effect On Zero Lift Drag Of Increasing The Leading Edge Bluntness Of A 45 Degree Sweptback Wing Having An Naca 65a009 Airfoil
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Author : William B. Pepper
language : en
Publisher:
Release Date : 1952
Free Flight Tests At Mach Numbers From 0 8 To 1 4 To Determine The Effect On Zero Lift Drag Of Increasing The Leading Edge Bluntness Of A 45 Degree Sweptback Wing Having An Naca 65a009 Airfoil written by William B. Pepper and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with categories.
Free Flight Measurements Of The Zero Lift Drag Of Several Wings At Mach Numbers From 1 4 To 3 8
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Author : H. Herbert Jackson
language : en
Publisher:
Release Date : 1960
Free Flight Measurements Of The Zero Lift Drag Of Several Wings At Mach Numbers From 1 4 To 3 8 written by H. Herbert Jackson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Mach number categories.
Free Flight Investigation At Mach Numbers From 0 8 To 1 5 Of The Effect Of A Fuselage Indentation On The Zero Lift Drag Of A 52 5 Degree Sweptback Wing Body Configuration With Symmetrically Mounted Stores On The Fuselage
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Author : Sherwood Hoffman
language : en
Publisher:
Release Date : 1958
Free Flight Investigation At Mach Numbers From 0 8 To 1 5 Of The Effect Of A Fuselage Indentation On The Zero Lift Drag Of A 52 5 Degree Sweptback Wing Body Configuration With Symmetrically Mounted Stores On The Fuselage written by Sherwood Hoffman and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1958 with categories.
Transonic Flight Tests To Determine The Effect Of Thickness Ratio And Plan Form Modification On The Zero Lift Drag Of A 45 Degrees Sweptback Wing
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Author : William B. Pepper
language : en
Publisher:
Release Date : 1952
Transonic Flight Tests To Determine The Effect Of Thickness Ratio And Plan Form Modification On The Zero Lift Drag Of A 45 Degrees Sweptback Wing written by William B. Pepper and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with categories.
Investigation At Mach Numbers Of 0 20 To 3 50 Of A Blended Diamond Wing And Body Combination Of Sonic Design But With Low Wave Drag Increase With Increasing Mach Number
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Author : George H. Holdaway
language : en
Publisher:
Release Date : 1959
Investigation At Mach Numbers Of 0 20 To 3 50 Of A Blended Diamond Wing And Body Combination Of Sonic Design But With Low Wave Drag Increase With Increasing Mach Number written by George H. Holdaway and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Airplanes categories.
Aerodynamic Characteristics At Mach Numbers From 0 20 To 4 63 Of A Canard Type Supersonic Commercial Air Transport Configuration
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Author :
language : en
Publisher:
Release Date : 1962
Aerodynamic Characteristics At Mach Numbers From 0 20 To 4 63 Of A Canard Type Supersonic Commercial Air Transport Configuration written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with categories.
Effects Of Mach Number Leading Edge Bluntness And Sweep On Boundary Layer Transition On A Flat Plate
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Author : DON W. JILLIE
language : en
Publisher:
Release Date : 1961
Effects Of Mach Number Leading Edge Bluntness And Sweep On Boundary Layer Transition On A Flat Plate written by DON W. JILLIE and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with categories.
The effects of leading-edge bluntness and sweep on boundary-layer transition on flat plate models were investigated at Mach numbers of 2.00, 2.50, 3.00, and 4.00. The effect of sweep on transition was also determined on a flat plate model equipped with an elliptical nose at a Mach number of 0.27. Models used for the supersonic investigation had leading-edge radii varying from 0.0005 to 0.040 inch. The free-stream unit Reynolds number was held constant at 15 million per foot for the supersonic tests and the angle of attack was 0 degrees. Surface flow conditions were determined by visual observation and recorded photographically. For the models with the blunter leading edges, the transition Reynolds number (based on free-stream flow conditions) was approximately doubled by an increase in Mach number from 2.50 to 4.00; and nearly the same result was predicted from shock-loss considerations. At all supersonic Mach numbers, increases in sweep reduced the transition Reynolds number and the amount of reduction increased with increases in bluntness. The shock-loss method considerably underestimated the sweep effects, with swept wings. (Author).
Flight Investigation At Mach Numbers From 0 8 To 1 5 To Determine The Effects Of Nose Bluntness On The Total Drag Of Two Fin Stabilized Bodies Of Revolution
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Author : Roger G. Hart
language : en
Publisher:
Release Date : 1950
Flight Investigation At Mach Numbers From 0 8 To 1 5 To Determine The Effects Of Nose Bluntness On The Total Drag Of Two Fin Stabilized Bodies Of Revolution written by Roger G. Hart and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1950 with Body of revolution categories.
Values of total-drag coefficient were measured for two fin-stabilized blunt-nose bodies of revolution in free flight at Mach numbers from 0.8 to 1.5. The blunt-nose configurations were designed by rounding off the sharp noses of two previously tested configurations, having nose fineness ratios of about 3.5, to radii equal to about 1/4 the maximum body radii.
Effects Of Mach Number Variation Between 0 07 And 0 34 And Reynolds Number Variation Between 0 97 X 10 Exp 6 And 8 1 X 10 Exp 6 On The Maximum Lift Coefficient Of A Wing Of Naca 64 210 Airfoil Sections
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Author :
language : en
Publisher:
Release Date : 1952
Effects Of Mach Number Variation Between 0 07 And 0 34 And Reynolds Number Variation Between 0 97 X 10 Exp 6 And 8 1 X 10 Exp 6 On The Maximum Lift Coefficient Of A Wing Of Naca 64 210 Airfoil Sections written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with categories.
The effects of Mach number and Reynolds number on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections are presented. The wing was tested through the speed range of the Langley 19-foot pressure tunnel at two values of air pressure. The ranges of Mach number obtained were from 0.07 to 0.34 at atmospheric pressure and from 0.08 to 0.26 at a pressure of 33 pounds per square inch absolute. The corresponding Reynolds number ranges were from 0.97 x 10(exp 6) to 4.44 x 10(exp 6) and from 2.20 x 10(exp 6) to 8.10 x 10(exp 6), respectively. The tests were made with and without partial-span and full-span split flaps deflected 60 deg. Pressure-distribution measurements were obtained for all configurations. The maximum lift coefficient was a function of the two independent variables, Mach number and Reynolds number, and both parameters had an important effect on the maximum lift coefficient in the ranges investigated. The stall-progression and, consequently, the shape of the lift-curve at the stall were influenced by variations in both Mach number and Reynolds number. Peak maximum lift coefficients were measured at Mach numbers between 0.12 and 0.20, depending on the Reynolds number range and flap configuration. There was very little influence of either Mach number or Reynolds number on the maximum lift of the wing with leading-edge roughness.
Flight Evaluation Of Splitter Plate Effectiveness In Reducing Base Drag At Mach Numbers From 0 65 To 0 90
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Author : Edwin J. Saltzman
language : en
Publisher:
Release Date : 1967
Flight Evaluation Of Splitter Plate Effectiveness In Reducing Base Drag At Mach Numbers From 0 65 To 0 90 written by Edwin J. Saltzman and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with categories.