3 pages matching forebody in this book
Results 1-3 of 3
What people are saying - Write a review
We haven't found any reviews in the usual places.
airfoil sections airfoil with 0.20-chord airplane angle of attack angle of dead angle of yaw approximately COMMITTEE FOR AERONAUTICS CONFIDENTIAL Figure CONFIDENTIAL x Upper critical Mach number critical speed dead rise depth of step dive drag coefficient drag curve drag increase effect of compressibility equal torque Figure 39 Fineness ratio flap deflection flight flow forebody front and rear front hub fuselage given in figure high-speed tunnel increasing Mach number indicated indicated airspeed Langley Field Langley Memorial Aeronautical length-beam ratio lift coefficient load coefficients Lower surface Memorial Aeronautical Laboratory modified NACA NACA airfoils NACA ARR Nacelle NATIONAL ADVISORY COMMITTEE normal-force coefficient number of blades obtained peak efficiency Percent chord pitot-static tube presented in figure Pressure distribution rear blade angle rear propeller rotational speed Schlieren static pressure supercritical surface O Lower terminal Mach number terminal velocity test section total-pressure tube Upper surface windshields wing X X X X X X