COMPUTER PROGRAM USER'S MANUAL FOR ... - CAFE Foundation

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TECHNOLOGY IDENTIFICATION ' General aviation aircraft covers a very broad spectrum of aircraft implied by the power plant size range of 100-1500 shaft horsepower. Thus, in order to provide a meaningful study within the scope intended by the Advanced Concepts and Missions Division, A. C. M. D. , as an initial step under the study in reference 1 the Contractor classified into five categories the general aviation aircraft envisioned by A. C. M. D. For convenience, the categories are repeated here in Table I. Analytical generalizations for predicting the performance (static , forward flight, and reverse) , noise, weight and cost of propellers for general aviation aircraft classified in Table I were established and computerized. With' the aircraft and propeller requirements thus defined and the computer program having been established, comprehensive sensitivity studies of the propeller geometric and performance parameters can be conducted. Such studies were presented in reference 1 for representative aircraft from each general category described in Table I. The details of the analytical procedures are defined in references 1 and 2. A brief description of each generalization is presented in the following text. Propeller Performance Generalization As a means of assessing propeller performance over the entire flight spectrum, performance generalizations were developed for predicting static and forward flight performance. Furthermore, for those aircraft incorporating propellers with the reverse thrust feature, a method of calculating reverse thrust has been included. These generalizations were made for a family of propellers spanning the prime propeller variables of 2 to 8 in number of blades, 80-200 in blade activity factor, AF, and 0.3 to 0.8 in integrated design lift coefficient, CL.. 1 A brief description of these generalizations is presented in the following test. Static and forward flight. - A performance generalization was developed for predicting static and forward flight performance for general aviation propellers. Using the proven propeller performance prediction methods discussed in references 1 and 2, performance calculations were made for a family of propellers selected on the basis of propeller shapes which prior study had shown to be the most favorable for minimum weight, low noise characteristics and good performance (ref. Afig. 1, 2, 3 and 4 and ref 2, fig. 1). These calculations were used in developing the performance generalizations. The horsepower, thrust, propeller rotational speed, velocity and diameter were included in the non-dimensional form of power coefficient, Cp, thrust coefficient, CT, and advance ratio, J defined as follows.
C P cT J where: - - SHP ( P o/P) x 10l1 3 5 2N D 6 1.514 x10 T( P,/P) N2 D4 101.4 V - k ND SHP - shaft horsepower p o/,, - ratio of density at sea-level standard day to density for a specific operating condition. D - propeller diameter, ft N - propeller speed, rpm T - propeller thrust, pounds 'k - forward speed velocity, knots Base curves were defined in this non-dimensional form for presenting the performance of 2, 4, 6 and 8 bladed propellers referenced to an activity factor of 150 and 0.5 integrated design lift coefficient. In order to minimize the number of curves and consequently the size and complexity of the computer program, the terms effective power coefficients, CpE and effective thrust coefficient, CTE were -introduced. The effective power and thrust coefficients are defined as follows: C pE C TE where: 'P 'AF - - 'P~'AF XPC Li - - ' T ~ ~ A F x TC Li - power coefficient - activity factor adjustment to power coefficient (ref. 1, fig. 3A) PC - integrated design lift coefficient adjustment factor to power co- Li efficient (ref. 2, fig. 4) 8
Page 1 and 2: k .” c - 1. -a “ ”- NASA *o *
Page 4 and 5: CONTENTS SUMMARY 1 INTRODUCTION SYM
Page 6: SUMMARY A major outcome of the stud
Page 10 and 11: AF b B C LD C Li cP C Q cT D h J M
Page 14 and 15: cT T~~ - thrust coefficient - activ
Page 16 and 17: &AF - activity factor adjustment fa
Page 18 and 19: Propeller Weight Generalization A w
Page 20 and 21: Propeller 1. Diameter range 2. Numb
Page 22 and 23: PARAMETRIC STUDY OPTIONS Having dev
Page 24 and 25: 1. 2. 3. 4. 5. 6. 7. a. 9. 10. Card
Page 26 and 27: 6. RPM for zero velocity, full thro
Page 28 and 29: For the option where tipspeed for 5
Page 30 and 31: CONCLUDING REMARKS 1. Generalizatio
Page 32 and 33: j Aircraft Class Seats I. Single En
Page 34 and 35: Y (I) 4 w EFFECTIVE POWER COEFFICIE
Page 36 and 37: I 3 BLADES/IOO AF/O.~ cLi BLADE ANG
Page 38 and 39: PROPELLER INPUT HORSEPOWER FIGURE 5
Page 40 and 41: ~ ja, m ~ MINIMUM CRUISE 370# THRUS
Page 42 and 43: I CATEGORY V I LANDING SPEEDS, KNOT
Page 44 and 45: w W JOB NO.: ACCT. NO: W.O. NO.: !
Page 46 and 47: HAMILTON STANQARD CflMPUTER DECK Nf
Page 48: 2FClPR7CATIVG F'IGI'JF 650. 547. 21
Page 51 and 52: DETERMINE TIPSPEED AT WHICH BLADE W
Page 53 and 54: . FORTRAN .CY G LEVEL 2011 HA1 N DA
Page 55 and 56: FORTRAN .I.V G LEVEL 2011 . . MA I
Page 57 and 58: FORTRAN I V G LEVEL 20.1 MA IN OATE
Page 59 and 60: FClQTR41 IV G LEVEL 70.1 INPUT DATE
Page 61 and 62: 0017 00 19 00 19 0020 0021 0022 56
Page 63 and 64:
FORTRAN I V G LEVEL 20.1 PERFM DATE
Page 65 and 66:
FORTRAN IV G LEVEL 20.1 PERFM DATE
Page 67 and 68:
. " . -. . . . IDRTRAN .IV..G LEVEL
Page 69 and 70:
FOPTRAU 1V C, LFVFL 23.1 ZNO I SF D
Page 71 and 72:
FORTRAN I V G LEVEL.. 20.1 . . " .
Page 73 and 74:
0035 0006 0007 001 0 FIGURE 3A. FOR
Page 75 and 76:
. .. F3RTpAN 1V.G LFVEL 20,l 0063 0
Page 77 and 78:
FI?RTP.AY IV G LEVEL 20.1 R IOUAD D
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