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Rotorcraft Performance Data for AEDT Methods of Using the NASA Design and Analysis of Rotorcraft Tool for Developing Data for AEDT’S Rotorcraft Performance Model

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Rotorcraft Performance Data for AEDT Methods of Using the NASA Design and Analysis of Rotorcraft Tool for Developing Data for AEDT’S Rotorcraft Performance Model Rotorcraft performance data for AEDT Methods of using the NASA Design and Analysis of Rotorcraft tool for developing data for AEDT’s Rotorcraft Performance Model David A. Senzig Sandy Liu Final Report — September 2016 DOT-VNTSC-FAA-16-22 DOT/FAA/AEE/2016-28 Prepared for: Office of Environment and Energy Federal Aviation Administration U.S. Department of Transportation Notice This document is disseminated under the sponsorship of the Department of Transportation in the interest of information exchange. The United States Government assumes no liability for the contents or use thereof. The United States Government does not endorse products or manufacturers. Trade or manufacturers’ names appear herein solely because they are considered essential to the objective of this report. REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188 Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188), Washington, DC 20503. 1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED September 2016 Final Report 4. TITLE AND SUBTITLE 5a. FUNDING NUMBERS Rotorcraft performance data for AEDT FA5JC6 PJ1C1 Methods of using the NASA Design and Analysis of Rotorcraft tool for developing data for AEDT’s Rotorcraft Performance Model 6. AUTHOR(S) 5b. CONTRACT NUMBER David A. Senzig, Sandy Liu 8. PERFORMING ORGANIZATION 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) REPORT NUMBER U.S. Department of Transportation John A Volpe National Transportation Systems Center 55 Broadway DOT-VNTSC-FAA-16-22 Cambridge, MA 02142-1093 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSORING/MONITORING US Department of Transportation AGENCY REPORT NUMBER Federal Aviation Administration Office of Environment and Energy DOT/FAA/AEE/2016-28 800 Independence Ave, SW Washington, DC 20591 11. SUPPLEMENTARY NOTES 12a. DISTRIBUTION/AVAILABILITY STATEMENT 12b. DISTRIBUTION CODE This document is available on the DOT’s National Transportation Library website at: http://ntlsearch.bts.gov/ 13. ABSTRACT (Maximum 200 words) This report documents use of the NASA Design and Analysis of Rotorcraft (NDARC) helicopter performance software tool in developing data for the FAA’s Aviation Environmental Design Tool (AEDT). These data support the Rotorcraft Performance Model (RPM) developed for AEDT. The methods are primarily intended to support helicopters which do not have sufficient information in their flight manuals to develop data using the methods documented in DOT-VNTSC-FAA-16-03. The process of developing performance data for RPM using NDARC is detailed for a piston engine training helicopter. 14. SUBJECT TERMS 15. NUMBER OF PAGES Helicopter, Rotorcraft, Helicopter Performance, Aviation Environmental Design Tool, AEDT, FAA 33 16. PRICE CODE 17. SECURITY CLASSIFICATION 18. SECURITY CLASSIFICATION 19. SECURITY CLASSIFICATION 20. LIMITATION OF ABSTRACT OF REPORT OF THIS PAGE OF ABSTRACT Unlimited Unclassified Unclassified Unclassified NSN 7540-01-280-5500 Standard Form 298 (Rev. 2-89) Prescribed by ANSI Std. 239-18 298-102 SI* (MODERN METRIC) CONVERSION FACTORS APPROXIMATE CONVERSIONS TO SI UNITS Symbol When You Know Multiply By To Find Symbol LENGTH in inches 25.4 millimeters mm ft feet 0.305 meters m yd yards 0.914 meters m mi miles 1.61 kilometers km AREA in2 square inches 645.2 square millimeters mm2 ft2 square feet 0.093 square meters m2 yd2 square yard 0.836 square meters m2 ac acres 0.405 hectares ha mi2 square miles 2.59 square kilometers km2 VOLUME fl oz fluid ounces 29.57 milliliters mL gal gallons 3.785 liters L ft3 cubic feet 0.028 cubic meters m3 yd3 cubic yards 0.765 cubic meters m3 NOTE: volumes greater than 1000 L shall be shown in m3 MASS oz ounces 28.35 grams g lb pounds 0.454 kilograms kg T short tons (2000 lb) 0.907 megagrams (or "metric ton") Mg (or "t") oz ounces 28.35 grams g TEMPERATURE (exact degrees) oF Fahrenheit 5 (F-32)/9 Celsius oC or (F-32)/1.8 ILLUMINATION fc foot-candles 10.76 lux lx fl foot-Lamberts 3.426 candela/m2 cd/m2 FORCE and PRESSURE or STRESS lbf poundforce 4.45 newtons N lbf/in2 poundforce per square inch 6.89 kilopascals kPa APPROXIMATE CONVERSIONS FROM SI UNITS Symbol When You Know Multiply By To Find Symbol LENGTH mm millimeters 0.039 inches in m meters 3.28 feet ft m meters 1.09 yards yd km kilometers 0.621 miles mi AREA mm2 square millimeters 0.0016 square inches in2 m2 square meters 10.764 square feet ft2 m2 square meters 1.195 square yards yd2 ha hectares 2.47 acres ac km2 square kilometers 0.386 square miles mi2 VOLUME mL milliliters 0.034 fluid ounces fl oz L liters 0.264 gallons gal m3 cubic meters 35.314 cubic feet ft3 m3 cubic meters 1.307 cubic yards yd3 mL milliliters 0.034 fluid ounces fl oz MASS g grams 0.035 ounces oz kg kilograms 2.202 pounds lb Mg (or "t") megagrams (or "metric ton") 1.103 short tons (2000 lb) T g grams 0.035 ounces oz TEMPERATURE (exact degrees) oC Celsius 1.8C+32 Fahrenheit oF ILLUMINATION lx lux 0.0929 foot-candles fc cd/m2 candela/m2 0.2919 foot-Lamberts fl FORCE and PRESSURE or STRESS N newtons 0.225 poundforce lbf kPa Kilopascals 0.145 poundforce per square inch lbf/in2 *SI is the symbol for the International System of Units. Appropriate rounding should be made to comply with Section 4 of ASTM E380. (Revised March 2003) Acknowledgments This work was funded by the FAA’s Office of Environment and Energy. We thank Becky Cointin for supporting and directing this work. We thank Lauren Jackson for assisting with the data development, and Robert Downs for his review of the document. The work would not have been possible without the assistance of Wayne Johnson, the author of the NASA Design and Analysis of Rotorcraft software tool. Contents List of Figures ........................................................................................................................ 3 List of Tables .......................................................................................................................... 4 List of Abbreviations .............................................................................................................. 5 Executive Summary ............................................................................................................... 6 1. Introduction ................................................................................................................... 7 2. Background .................................................................................................................... 8 3. NDARC Data ................................................................................................................... 9 3.1 Engine performance data ........................................................................................................... 9 3.1.1 Engine weight ............................................................................................................... 11 3.1.2 Engine reference parameters ...................................................................................... 11 3.1.3 Engine scaling parameters ........................................................................................... 12 3.1.4 Engine power available ................................................................................................ 13 3.1.5 Performance at the power required ............................................................................ 14 3.2 Main and tail rotor data ............................................................................................................ 15 3.2.1 Main rotor .................................................................................................................... 15 3.2.2 Tail rotor....................................................................................................................... 16 3.3 Control surface data.................................................................................................................. 16 3.4 Fuselage dimensional data........................................................................................................ 17 3.5 Fuel ............................................................................................................................................ 17 3.6 Performance cases .................................................................................................................... 17 3.7 NDARC outputs ......................................................................................................................... 18 4. RPM support tools ........................................................................................................ 19 4.1 CTCP program ........................................................................................................................... 19 4.1.1 CTCP inputs .................................................................................................................. 19 4.1.2 CTCP outputs ...............................................................................................................
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