AE 413 SP'24 HW#1

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Embry-Riddle Aeronautical University *

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413

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Mechanical Engineering

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Apr 3, 2024

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AE413 SP’24 HW #1 (due 18-Jan) 10-Jan’24 Prpf. Greiner Appendix A & B ERAU Section: Print name: This sheet is page 1 of your homework submittal. Followed by clean engineering paper showing needed calculations with documentation included using a yellow highlighter and red pen with straight edge to define values. You will also need an engineering scale for this course. 1) A NACA 6-series airfoil 64 2 -215 is being investigated. a) Per the airfoil’s NACA designation: i) Design lift coefficient, ࠵? ! !"#$%& = ii) Minimum drag C l range (drag bucket): from C l = to C l = iii) What does 15 represent? b) Per Abbot and Von Doenhoff’s NACA TR-824 tables and figures for this NACA 64 2 -215 airfoil w/o flaps: i) Maximum thickness is located at % c ii) Zero lift angle of attack (AoA), ࠵? " ’ = degrees iii) Lift coefficient at zero AoA, ࠵? ! ( = iv) Lift curve slope, ࠵? ! ) = ࠵? " = per degree or per radian v) Maximum lift coefficient, ࠵? ! *+, = at AoA = degrees vi) Pitching moment coefficient about its aerodynamic center, ࠵? # +- = vii) Aerodynamic center (a.c. or ac) location at % c c) Create a table comparing your Abbott and Von Doenhoff’s eye-ball values with that from Perkins and Hage’s airfoil table (A.26) and another column with that from Datcom’s airfoil table (A.27 to A.30). d) Now, if the NACA airfoil trailing edge cusp is removed, linearized from 80% to TE, its designation would change to NACA 64 2 A215. Add this airfoil information from Datcom’s airfoil table (A.27 to A.30) to your table for comparison. Any significant differences? 2) If the NACA 64 2 A415 airfoil is to incorporate a 20% trailing edge slotted flap deflected 40º utilizing Perkins and Hage’s section lift/moment figures on page A.37 (using t/c = 0.12) determine the following: a) Change in lift coefficient due to flap deflection, ∆࠵? ! . = b) Change in moment coefficient due to flap deflection, ∆࠵? # +- . = c) If we assume the change of lift/moment due to flap deflection is linear (an approximation), write a general equation to describe these: ࠵? ! = ࠵? ! ( + ࠵? ! ∝ ∝ +࠵? ! 0 1. ࠵? $% i.e. numerically define ࠵? ! ( , ࠵? ! ∝ , ࠵? ! 0 1. ࠵? # = ࠵? # ( + ࠵? # ∝ ∝ +࠵? # 0 1. ࠵? $% i.e. numerically define ࠵? # ( , ࠵? # ∝ , ࠵? # 0 1.

AE413 SP’24 HW #1 (due 18-Jan) 10-Jan’24 Prpf. Greiner Appendix A & B ERAU d) Estimate the airfoil’s total lift coefficient (C l ) and total pitching moment coefficient (C m ) with flap deflected 30º at alpha star, a *, which is where the lift curve slope ceases to be linear. 3) Some web sites containing airfoil information needed for this course are: a) UIUC Airfoil Data Site > The Incomplete Guide to Airfoil Usage: https://m-selig.ae.illinois.edu/ads/aircraft.html Visit the UIUC web site to define the Navion’s wing root and tip 4-digit NACA airfoil designation: wing root NACA , wing tip NACA b) Airfoil Tools: http://airfoiltools.com/search/index?m%5Bgrp%5D=naca6&m%5Bsort%5D=1 Use the Airfoil Tools web site to plot these airfoils shapes. Average the root and tip NACA designations to plot out a “single” airfoil designation. c) FAA’s Dynamic Regulatory System (DRS) > Design and Production Approvals > Type Certificate Data Sheet (TCDS) https://drs.faa.gov/browse/TCDSMODEL/doctypeDetails Download the Navion’s TCDS from FAA’s DRS web site. Print the TCDS sheets applicable to document your answers below. d) NASA’s Technical Report Server (NTRS) https://ntrs.nasa.gov/search Visit NTRS to download the Navion’s Technical Note (TN), NASA-TN-D-5857. 4) Define the following parameters for the original Navion (Army L-17A) per the TCDS: a) How many different models of the Navion have been certified? b) Maximum weight lbs c) Airspeed limits: circle the type : Indicated Calibrated Equivalent True i) Never Exceed knots = fps (clean configuration) ii) Flaps/gear extended knots = fps d) Optional engine its Bhp @ rpm e) The diameter of the propeller, D p = inches = ft (max) D p = inches = ft (min) f) Propeller pitch angle (low) to (high) measured/located at %R p g) Control surface deflection: i) Elevator: down (+ d e ) to up (- d e ) ii) Elevator tab: down (+ d e,tab ) to up (- d e,tab ) iii) Rudder: left (+ d r ) to right (- d r ) iv) Aileron (left): down (+ d a ) up (- d a )

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