NASA-CR-114399-1971 Advanced general aviation propeller study《先进的通用航空螺旋桨的研究》.pdf

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1、CONTRACT REPORTNASACR 114399ADVANCED GENERAL AVIATIONPROPELLER STUDY(I_sA-CN 11ttqql,)tlD _DvANCE_ GEt_I_L AVIfiTON. , ,_tal !pROPELLF,_ Bt_nd4rd )R“ ;_orobel_(Hamilton 21 Dec. 1971 5L_ p _-G3/02 Ut,claS184560,/“ ,_CSCL 01C -_HCU_a 3_OK tl: B ROSE WOR OBEL _ _:_; ,_“-0_:_ ., , _;7/_,-7) ,_,DECEMBER

2、21,1971 ,:., ,“_“d f “h_ _._ “.“PREPARED UNDER CONTRAC.T NO. NAS2-6477 BYHAM ILTON STANDARDDIVISION OF UNITED AIRCRAFT CORPORATION;, WINDSOR LOCKS ,CONNECTICUTFORi _ ADVANCED CONCEPTS AND MISSIONS DIVISION OFFICE OF ADVANCED RESEARCH AND TECHNOLOGYNATIONAL AERONAUTICS AND SPACE ADMINISTRATION“ -_“f_

3、 “-“-_:;“_ “_ . -_ 1972010354Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_CONTRACT REPORTNASA CR 114399ADVANCED GENERAL AVIATION PROPELLER STUDYByRose WorobelMiUard G. MayoDecember 21, 1971_“ Prepared Under Contract No. NAS2-6477 By:._ HAMILTON S

4、TANDARD Division of United Aircraft CorporationWindsor Locks, Connecticut i“forADVANCED CONCEPTS AND MISSIONS DIVISIONOFFICE OF ADVANCED RESEARCH AND TECHNOLOGYNATIONAL AERONAUTICS AND SPACE ADMINISTRATIONqProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-

5、,-,- rJ,l f_ f, I A(,I, ,lH,A_,q( NOT i |I_Mr,DABSTRACTUnder a previous NASA contract and reported in CR-114289 methods for pre-dicting the performance, noise, weight, and cost of propellers for advanced generaaviation aircraft of the 1980 time period were developed and computerized. Underthe presen

6、t contract this baste program was refined to incorporate a method of includ-ing the blade shape parameter, integrated design lift eoefficl_:nt, This method arLdareverse thrust computational procedure were included in the computer program. Thewetg_ equation was refined and also incorporated in the co

7、mputer program. A UsertsManual which includes a complete listing of this computer program with detailedinstructions on tt_ use has been written and will be published as a NASA low numberContractor RoporLIll/iv“ 1972010354-TSA04Provided by IHSNot for ResaleNo reproduction or networking permitted with

8、out license from IHS-,-,-CONTENTS, SUMMARY 1INTRODUCTION 3SYMBOLS 5TECHNOLOGY DEVELOPMENT 7Method for Varying Integ:ated Design Lift Coefficient, 7Integrated Design Lift Coefficient Adjustment Factor, 9Compressibility Factor 10Method for Computing Reverse Thrust 11Computational Procedure 13Refinemen

9、t of Weight Generalization 16Input/Output Additions to the Computer Program 17USERtS MANUAL 19._ CONC LUDING REMARKS 21REFERENCES 23,;._ TABLES_: I Weight Summary of Propellers Studies for 1980 25II General Aviation - Generalized Propeller Weight Equation 26!_:_._i III Typical 1970 Propeller Weights

10、 27:.“ IV O.E.M. Single Unit Cost Summary of Representativei.i_ii,i Propellers for 1980 29.: FIGURES1 Blade Camber Distribution 302 Number of Blades Correction for Power Coefficient 313 Camber Factor Adjustment for Advance Ratio 324 Integrated Design Lift Coefficient Adjustment to PowerCoefficient f

11、or 4-Bladed Propellers 335 Number of Blades Correction for Thrust Coefficient 34 6 Integrated Design Lift Coefficient Adjustment to ThrustCoefficient for 4-Bladed Propellers 38.: 7 Critical Mach Number for Advance Ratios Greater than Zero 36V1972010354-TSA05Provided by IHSNot for ResaleNo reproducti

12、on or networking permitted without license from IHS-,-,-iCONTENTS (Continued)FIGURES (Continued)8 C ritical Mash Number for Advance Ratios Equal to Zero 379 Compres_ibility Adjustment 3810 E_cample Reverse Thrust Variation w_th Landing Speed and Power Setting 3911 Activity Factor Adjustment to Torqu

13、e Coefficient 4012 Integrsted Design Lift Coefficient Adjustment to Torque ,.C o_Jffleient 4113 Variation of Percentage of Integrated Design Lift CoefficientCorrection Required for Thrust and Torque 4214 Basic Performance Curve - Variation of Effective TorqueCoefficient with Advance Ratio and Blade

14、Angle 4315 Integrated Design lift Coefficient Adjustment to TorqueCoefficient 4416 Basic Performance Cur_e - Variation of Effective ThrustCoefficient with Advance Ratio and Blade Anglo 4517 Activity Factor Adjustment to Thrust Coefficient 4G18 Integrated Design Lift Coefficient Adjustment to ThrustC

15、oeffieient 47 !19 Sample Case I of Computer Program Output 4820 Sample Case II of Computer Program Output 49Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SUMMARYA major outcome of the study sponsored by the Advanced Concept and mission. Division, A

16、. C.M.D. of NASA under Contract No. NAS2_5885 dated 30 January 1970and reported in CR 114289 has been the developnmnt of a computer program for evalu-ating propeller performance, noise, weight and cost for general aviation aircraft pro-pollers as a function of the primo geometric and aerodynamic var

17、iables. This programprovides for changes in the activity factor per blade and number of blades, but it waslimited to a single value of integrated design lift coefficient. This study, Contract No.NAS2-6477 dated fl May 1971 and also sponsored by the A. C. M. D., extends this com-puter program to inco

18、rporate the integrated deMgn lift coefficient as a propeller bladeshape variable. Additional extensions to the computer program which are documentedin this report are the eapabiliW of calculating propeller reverse thrust and the refine-meat of the propeller weight equation. A final requirement of Co

19、ntract No. NAS2-6477was to describe the complete computer program. This manuM is reported in a sep-arate low number NASA Contractor Report.In this report the technology is developed for including the capability of varyingintegrated design lift coefficient. An existing reverse thrust method has been

20、adaptedfor the general aviation aircraft application. The weights for 36 additional propellersover those used in the original study have been defined analytically and used in refiningthe weight equation. These technology additions and revisions are incorporated into the: computer program.1/2TSA07 19

21、72010354-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-INTRODUCTIONAviation forecasts for the next ten to fifteen year time period, indicate the eon- iftinned steady growth of general aviation. Furthermore, it is apparent that most of these aircraf

22、t, even into the 1980 time period will be propeller driven utilizing prima- Irily reeiproeating engines with turbine engines coming on as their economies improve.The attainment of this forecasted growth is dependent upon the eontl 1ned improvement 1in the safety, utility, performance and cost of gen

23、eral aviation sire“ ,fit. I|In view of this, a study was undertaken under NASA sponsorship to derive and 1computeriz_ appropriate propeller performance, noise, weight and cost criteria topermit sensitivity studies of these factors to be made for adwmee propeller configura-tions designe_ for general

24、aviation aircraft of the 1980 time period. The results ofthis study wer,_ presented in Contractor Report NASA Cfl 114289, “Advanced GeneralAviation Stud: ,t April 1971 (rof. 1). At NA_AIs request a contract study was under-“ taken to provide a Userts Manned which includes a complete listing of this

25、compt_erprogram with detailed instructions on its use. Furthermore the scope of the computerprogram has been extended to incorporate the following:1. Method for varying integrated design lift coefficient (the only primeblade shape variable not included in the original program)_. 2. Method for comput

26、ing reverse thrust: 3. Refinement of the weight equationThus a reliable computer program has been developed for predicting propeller perfor-mance (static, flight and reverse), noise, weight and cost for the complete general:i_ aviation aircraft range.i ._ A detailed discussion of the technology deve

27、lopments and incorporation into the.:_ computational procedures of the above extensions to the computer program are discussedin the following text. The Userts Manual which includes FORTRAN IV listings andInput/output Instructions wtll be published under separate cover as a NASA low numberContractor

28、Report.3/41972010354-TSA08Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SYMBOLS AND ABBREVIATIONSi.0O.15b blade aaetion width, ftB ntmlber of bladeflCLD blade B_ctlon design lift coefficient1.0ELI propeller blnde integrated destine Ill% coefficient

29、 4 f CLD x3 d,_0.18SHP(Po/P) I0IICp power coefficient,2N3D 5CQ torque coefficient for J_ 1.0, SHP (_._Po/P).101147r N3D 51.514x 106T(Po/p)CT thrust coefficient,N2D 4D propeller diameter, fth maximum blade section thickness101.4 VkJ advance ratio, NDM free stream Mach numberN propeller speed, rpmPNL

30、perceived noise level, PNdB5, ,.;.,_“_“=_ .“_ “ 1972010354-T 9Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Qc torque coefficient for J;. 1.0, SHP(Po/P) 1011 I4_r N3D 5 j2iR blade radius at propeller tip, ftr radius at blade element, ftSHP _haft ho

31、rsepowerT propeller thrust, pound_TC thrust coefficient for J_ 1.0, 1._14 x 106 T(Po/p ) X 1N2D4 j2VK freostrc_un velocity, lmotsx fraction of propeller tip r_lius, r/R_3/4 propeller blade angle at 3/4 radiusP density, lb sec2/ft 4Pc density at sea level standard day, 0.002378 lb. scc2/ft 4_,:. %lp

32、01_0 ratio of absolute temperature to absolute _emperature at sea level,_ T/To?. i _ ratio of static pressure to static pressure at sea level, P/Po:/i:_!i.= 6 - . “ _“ _ _ - 1972010354-TSA10Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECliNOLOGY

33、DEVELOPMENTMethod for Varying Integrated Design Lift CaeffiaientIn the original report (ref. 1), a perfornianee method generalization was devel_.oped far predicting static and forward flight performance for general aviation aircraftpropellers. The horsepower, thrust, propeller rotational spe_d, velo

34、city and dia_motor are included In the non-dimensional farm of power coefficient, Cp, thrustaocffieiont, CT, and advance ratio, J defined as fallows:fdliP ( Po/P ) 10JCp _ 2N3D 81.514.x i06T (Oo/p)(T _-_ N2Dd101.4 VKJ = NDwhere:SlIP - shaft horsepowerPo/P - ratio of density at sea level standard day

35、 to density for a specific operating condition_, N - propeller speed, rpm, D - propeller diameter_ftT - propeUer thrust, poundsVK - forward speed velocity, knotsBase curves were defined in this non-dimensional form presenting the perfor-mance of 2, 4, 6 and 8 bladed propellers referenced to an activ

36、ity factor of 150 and0.5 integrated design lift coefficient. In order to minimize the number of curves and consequently the size and complex-ity of the computer program, the terms effective power coefficient, CPE, and effective: thrust coefficient, CTE were introduced. The effective power coefficien

37、t and thrust7. 1972010354_TSA11Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CTE _ CTxTAFxTCLIwhere=Cp .- pawar aoeffietentPAF - nativity factor luiJustmt_nt to power eoofflalont (rof. 1, fig 3A)PCL l - integrated design lift coefficient, eLl ralJt

38、mtmont fimtor to l)oweraoeffiatont (do_ot_llmd in subt_oquoat text)(2T - thru._t aooffiektntTAF - activity fatJtor adjustment factor to thrust t,)offtcl_a_ (rift. 1,fig. 3A)TCL l - integrated design lift coefficient,eL i adjustment factor to thrust.i coefficient (described in subsequent text)IIn the

39、 original report, the base performance curves and the activity factori ,_ adjustment factors, PAF and TAF were developed and included in the computer pro-, gram. Furthermore, a limited anmunt of work was done to establish the feasibility ofgener_izing the integrated design li.ft coefficient effect.

40、Under the present studycontract, the integrated design lift coefficient adjustment factor was developed for a. _ range of 0.3 _ CLt _ 0.8. Blade camber distributions for this range of CL! are shown: _i: in figure 1. Thus, the base curves while referenced to a basic activity factbr and.:, integrated

41、design lift coefficient, are applicable to the complete range of 2 to 8 blades,80-200 activity factor and O. 3 to O. 8 integrated design lift coefficient.Since it has been projected tha_ general aviation aircraft will be operating atsignificantly ,higher speeds by the 1980 _tme period, a compressibi

42、lity factor, Ft forthe base curves of 0.5 integrated design lift coefficient was derived for use with thebase plots presented in reference 1. The thrust is multiplied by the Ft to correct forcompressibility losses. Under the present contract, the Ft correction was expandedto apply to the complete ra

43、nge of integrated design lift coefficient of 0. -_to 0.8.The development of the integrated design lift coefficient adjustment factors,: PCLt and TCL t and the compressibility correction, Ft, as well as their incorporation“ L/., 8Provided by IHSNot for ResaleNo reproduction or networking permitted wi

44、thout license from IHS-,-,-into the computational procedures are described in the following textIntegrated design lift coefficient adiustmen_ factors - Using the propeller compu-tational procedure based on the work of Goldstein _ defined in reference 1, calcula-tions were made for integrated design

45、lift coefficient between 0.3 and 0.8, number ofblades ranging from 2 to 8, and activity factor from 80 to 200. These calculationswere utilized in deriving the adjustment factors, PCLz and TCL l for the power ,_Aldthrust coefficients respectfully. These adjustment factors are dependent on advancerati

46、o, number of blades, activity factor :rod integrated design lift coefficient. Thedetailed step-by-step procedure incorp_,rated in the computer program is presentedbelow for the ease where thrust is calculated for a known shaft horsepower.1. CPE 1 - ealetflate = Cp x PAF (PAF- ref. 1,fig. 3A)2. PBL -

47、 read _om figure 2 for the CPE 1 of item I above an,! theproper number of blades3. PFCLi - read from fig_tre 3 for the appropriate J (revision offig. 12A in ref 1)4. CPE2 - calculate = CPE 1 x PBL x PFCLI5. PCLI - read from figure 4 for the CPE 2 of item 4 and the CLi(expansion of fig. 13A in ref. 1

48、)6. CPE - calculate = CPE 1 x PCLiNow, the corresponding blade angle, _3/4 and thrust coefficient, C T are obtainedas foUows:,i_; j 7. _3/4 - read for CPE , J and appropriate number oi blades (ref. 1,_:?_ fig. 4A, 6A, 8A, 10A),1_:_ J 8. - read for J and fl3/4 for the proper number of blades_ _ (ref. 1, fig. 5A_ 7A, 9A, llA)_, CTEThe following iteration is required to define the thrust coefficient since, C T = CTE/(TAF x TCLi) and TCLi is a function of