Aeronautic Propeller Tester

8/17/2019 Aeronautic Propeller Tester

1/1097

TESTER FOR EVALUATING AERONAUTICAL PR

NOTE: ENTER DATA ONLY IN YELLOW FRAMES

Altitude of igt !"o#l$ %&&&

No"i'(l )o*e+ of ,o"-u#tio' e'gi'e !.P$ %/0

S)eed of +ot(tio' fo+ e'gi'e1# "(2 )o*e+ !+) %3&&&

A ,u-i, ,oef4 -l(de #()e !5$ &/60073

8 ,u-i, ,oef4 -l(de #()e !5$ 59/0%7%

C ,u-i, ,oef4 -l(de #()e !5$ %/7%76

D ,u-i, ,oef4 -l(de #()e !5$ 5&/&770

8l(de *idt f(,to+ !5$ %

S)eed i'du,tio' f(,to+ !5$ &/;7

Co++e,tio' f(,to+ fo+ Cl !5$ %

Co++e,tio' f(,to+ fo+ Cd !5$ %/98l(de ti) lo## ,o++e,tio' f(,to+ !5$ &/7

P+o)elle+ di("ete+ !""$ %7&

#$ &/&

8l(de t*i#t !?$ @(+i(-le )it,B &/&

A(il(-le e'gi'e )o*e+ !.P$ %/0&

P+o)elle+ )o*e+ ,o"#u")tio' !.P$ &/9=T+ottle !$ %3/0

P+o)elle+ )o*e+ ,o"#u")tio' !W$ %;7

T+u#t lo##e# (t % )l(de ti) !g$ &/&%6;

S',+o'ou# #)eed of te )+o)elle+ !">#$ 93/00

Fligt #)eed !">$ &/&

Ee,tie t+u#t !g$ &/7

T+u#t de'#it o' )+o)elle+ +oto+ di#, !g>"9$ 0%/=39

Ee,tie t+u#t )o*e+ !.P$ &/&&&

T+u#t e,ie', !$ &/&

T+u#t ee,tiit !$ 60/=Ee,tie (e+(ge ('gle of (tt(, !?$ 3/7;

T+u#t to )o*e+ #)e'di'g +(tio !g+>W$ 0/%3

8l(de ti) #)eed !">$ =3&/=9

8l(de ti) #)eed !">#$ %00/=7

8l(de ti) M(, !5$ &/=&

Solidit of te +oto+ di#, !$ 3/9

Ae+(ge Re'old o' te -l(de !5$ 764%;%


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R R/Rmax

[mm] [-]

15.00 0.20

16.50 0.22

18.00 0.24

19.50 0.26

21.00 0.28

22.50 0.30

24.00 0.32

25.50 0.34

27.00 0.36

28.50 0.38

30.00 0.40

31.50 0.42

33.00 0.44

34.50 0.46

36.00 0.48

37.50 0.50

39.00 0.52

40.50 0.54

42.00 0.56

43.50 0.58

45.00 0.60

46.50 0.62

48.00 0.64

49.50 0.66

51.00 0.68


100/1097

52.50 0.70

54.00 0.72

55.50 0.74

57.00 0.76

58.50 0.78

60.00 0.80

61.50 0.8263.00 0.84

64.50 0.86

66.00 0.88

67.50 0.90

69.00 0.92

70.50 0.94

72.00 0.96

73.50 0.98

75.00 1.00


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PELLERS

Important, as the altitude varies the performance of the prop

Only necessary to meet engine power availability data, only c

Only necessary to meet engine power availability data, only c

1 for Master Airscrew propellers. 0,5 for normal A! propelle

Appro#imate diameter bloc$ed by the spinner or the cowling

%or non helical blades, aerobatic helicopter style, enter &ero

Airplane )ight speed or ascent or descent speed of multiroto

Only in the case of variable pitch propellers. %or #ed pitch e

If the value e#ceeds 100-, it means to lower rpm, because en

daniel_gonzalez_lagos@yaoo.!l

/escriptive coecient of the blade geometry. ecommended





0.10 0.20 0.30 0.40 0.50 0.60 0.70

"#$s% along %e 'lade

mailto:[email protected]:[email protected]


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0.177 0.129

(/Rmax )aso geom *ng$lo (+#on%/Rmax d ,$

[-] [mm] %o#sin !$e#da [] [-] +#on% ala [-]

0.15 100.00 46.451 0.105 0.000

0.17 100.00 43.967 0.119 0.002

0.18 100.00 41.483 0.133 0.003

0.19 100.00 39.220 0.146 0.003

0.20 100.00 37.158 0.158 0.003

0.21 100.00 35.274 0.168 0.003

0.21 100.00 33.550 0.178 0.004

0.22 100.00 31.970 0.186 0.004

0.22 100.00 30.518 0.193 0.004

0.23 100.00 29.181 0.199 0.004

0.23 100.00 27.947 0.203 0.004

0.23 100.00 26.805 0.207 0.004

0.23 100.00 25.747 0.210 0.004

0.23 100.00 24.765 0.211 0.004

0.23 100.00 23.850 0.212 0.004

0.23 100.00 22.997 0.212 0.004

0.23 100.00 22.200 0.211 0.004

0.22 100.00 21.453 0.209 0.004

0.22 100.00 20.754 0.207 0.004

0.22 100.00 20.096 0.204 0.004

0.21 100.00 19.477 0.200 0.004

0.21 100.00 18.894 0.196 0.004

0.20 100.00 18.344 0.191 0.004

0.19 100.00 17.824 0.185 0.004

0.19 100.00 17.331 0.180 0.004


200/1097

0.18 100.00 16.865 0.173 0.003

0.17 100.00 16.422 0.167 0.003

0.17 100.00 16.001 0.160 0.003

0.16 100.00 15.601 0.153 0.003

0.15 100.00 15.219 0.146 0.003

0.14 100.00 14.856 0.138 0.003

0.14 100.00 14.509 0.131 0.0030.13 100.00 14.178 0.123 0.002

0.12 100.00 13.861 0.116 0.002

0.11 100.00 13.558 0.108 0.002

0.10 100.00 13.267 0.101 0.002

0.10 100.00 12.989 0.094 0.002

0.09 100.00 12.721 0.087 0.002

0.08 100.00 12.465 0.080 0.002

0.07 100.00 12.218 0.073 0.001

0.07 100.00 11.981 0.067 0.001


201/1097

ller

mbustion engines

mbustion engines

s. 0,"5 for A! propellers with particularly pointed tips.

f the plane

nd change '(lade twist'

or helicopter *negative value for descent+, to evaluate.

ter &ero value. ositive blade twist 'increases pitch'

gines capacity is e#ceeded

ot to change2

ot to change2

ot to change2

ot to change2

ot to change2

0.80 0.90 1.00


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($e#da ,olidez +#on% elo!idad el %ang *n$la!in

ala [mm] #o%o# [-] gi#o [#m] [m/s] em$e ,i/o

11.4 0.167 17000.0 26.69 ,i

12.4 0.173 17000.0 29.36 ,i

13.3 0.177 17000.0 32.03 ,i

14.1 0.179 17000.0 34.70 ,i

14.8 0.179 17000.0 37.37 o

15.5 0.179 17000.0 40.04 o

16.0 0.177 17000.0 42.70 o

16.4 0.174 17000.0 45.37 o

16.8 0.170 17000.0 48.04 o

17.1 0.166 17000.0 50.71 o

17.3 0.162 17000.0 53.38 o

17.4 0.157 17000.0 56.05 o

17.5 0.152 17000.0 58.72 o

17.5 0.146 17000.0 61.39 o

17.4 0.141 17000.0 64.06 o

17.3 0.135 17000.0 66.73 o

17.1 0.129 17000.0 69.39 o

16.9 0.123 17000.0 72.06 o

16.6 0.118 17000.0 74.73 o

16.3 0.112 17000.0 77.40 o

15.9 0.106 17000.0 80.07 o

15.5 0.100 17000.0 82.74 o

15.1 0.095 17000.0 85.41 o

14.6 0.089 17000.0 88.08 o

14.1 0.084 17000.0 90.75 o


300/1097

13.6 0.079 17000.0 93.42 o

13.1 0.074 17000.0 96.08 o

12.5 0.069 17000.0 98.75 o

11.9 0.064 17000.0 101.42 o

11.3 0.060 17000.0 104.09 o

10.7 0.055 17000.0 106.76 o

10.1 0.051 17000.0 109.43 o9.5 0.047 17000.0 112.10 o

9.0 0.043 17000.0 114.77 o

8.4 0.039 17000.0 117.44 o

7.8 0.036 17000.0 120.11 o

7.2 0.032 17000.0 122.77 o

6.7 0.029 17000.0 125.44 o

6.1 0.026 17000.0 128.11 o

5.6 0.024 17000.0 130.78 o

5.1 0.021 17000.0 133.45 o


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el aan!e el #ela%ia *ng$lo el #ela%ia *ng$lo

[m/s] [m/s] a%a$e [] #eal [m/s] a%a$e amo#% []

0.00 26.69 43.55 26.69 43.55

0.00 29.36 43.97 29.36 43.97

0.00 32.03 41.48 32.03 41.48

0.00 34.70 39.22 34.70 39.22

0.00 40.73 13.69 40.73 13.69

0.00 43.71 11.60 43.71 11.60

0.00 46.55 10.09 46.55 10.09

0.00 49.30 8.93 49.30 8.93

0.00 52.01 7.99 52.01 7.99

0.00 54.67 7.23 54.67 7.23

0.00 57.31 6.59 57.31 6.59

0.00 59.94 6.04 59.94 6.04

0.00 62.55 5.59 62.55 5.59

0.00 65.14 5.21 65.14 5.21

0.00 67.73 4.88 67.73 4.88

0.00 70.32 4.58 70.32 4.58

0.00 72.91 4.33 72.91 4.33

0.00 75.49 4.11 75.49 4.11

0.00 78.07 3.92 78.07 3.92

0.00 80.66 3.76 80.66 3.76

0.00 83.23 3.62 83.23 3.62

0.00 85.81 3.50 85.81 3.50

0.00 88.39 3.41 88.39 3.41

0.00 90.97 3.34 90.97 3.34

0.00 93.54 3.28 93.54 3.28


400/1097

0.00 96.11 3.25 96.11 3.25

0.00 98.69 3.23 98.69 3.23

0.00 101.26 3.22 101.26 3.22

0.00 103.83 3.24 103.83 3.24

0.00 106.40 3.26 106.40 3.26

0.00 108.97 3.30 108.97 3.30

0.00 111.53 3.36 111.53 3.360.00 114.10 3.42 114.10 3.42

0.00 116.67 3.50 116.67 3.50

0.00 119.23 3.60 119.23 3.60

0.00 121.80 3.70 121.80 3.70

0.00 124.36 3.82 124.36 3.82

0.00 126.93 3.94 126.93 3.94

0.00 129.50 4.07 129.50 4.07

0.00 132.07 4.21 132.07 4.21

0.00 134.64 4.35 134.64 4.35


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)aso lo!/,$ma( !ien!ia o# *l%i%$d ensidad Viscosidad

geom [-] in%e#+e#en!ia [:] [msnm] ai#e [;g/m3] [kg/ms]

4.37 98.7: 1000 1.108 1.70-05

4.02 98.2: 1000 1.108 1.70-05

3.75 97.6: 1000 1.108 1.70-05

3.54 97.1: 1000 1.108 1.70-05

3.37 96.6: 1000 1.108 1.70-05

3.24 96.1: 1000 1.108 1.70-05

3.13 95.6: 1000 1.108 1.70-05

3.05 95.2: 1000 1.108 1.70-05

2.98 94.9: 1000 1.108 1.70-05

2.93 94.7: 1000 1.108 1.70-05

2.90 94.5: 1000 1.108 1.70-05

2.88 94.4: 1000 1.108 1.70-05

2.86 94.3: 1000 1.108 1.70-05

2.86 94.3: 1000 1.108 1.70-05

2.88 94.4: 1000 1.108 1.70-05

2.90 94.5: 1000 1.108 1.70-05

2.93 94.6: 1000 1.108 1.70-05

2.96 94.8: 1000 1.108 1.70-05

3.01 95.1: 1000 1.108 1.70-05

3.07 95.4: 1000 1.108 1.70-05

3.14 95.7: 1000 1.108 1.70-05

3.22 96.0: 1000 1.108 1.70-05

3.32 96.4: 1000 1.108 1.70-05

3.42 96.7: 1000 1.108 1.70-05

3.54 97.1: 1000 1.108 1.70-05


500/1097

3.68 97.5: 1000 1.108 1.70-05

3.83 97.8: 1000 1.108 1.70-05

4.00 98.2: 1000 1.108 1.70-05

4.19 98.5: 1000 1.108 1.70-05

4.41 98.8: 1000 1.108 1.70-05

4.65 99.0: 1000 1.108 1.70-05

4.93 99.3: 1000 1.108 1.70-055.24 99.5: 1000 1.108 1.70-05

5.58 99.6: 1000 1.108 1.70-05

5.98 99.7: 1000 1.108 1.70-05

6.42 99.8: 1000 1.108 1.70-05

6.93 99.9: 1000 1.108 1.70-05

7.51 99.9: 1000 1.108 1.70-05

8.16 100.0: 1000 1.108 1.70-05

8.90 100.0: 1000 1.108 1.70-05

9.75 100.0: 1000 1.108 1.70-05


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- - - -

Re Cla Clb Clc

[-] [-] [-] [-]

17


600/1097

76


601/1097


602/1097


603/1097


604/1097


605/1097


606/1097


607/1097


608/1097


609/1097


610/1097


611/1097


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623/1097


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626/1097


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628/1097


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630/1097


631/1097


632/1097


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662/1097


663/1097


664/1097


665/1097


666/1097


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669/1097


670/1097


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698/1097


699/1097

- - - - - -

Cda Cdb Cdc Cl Cd L/D

[-] [-] [-] [-] [-] [-]

0.035 -0.745 0.120 0.888 0.8264 1.075

0.026 -0.541 0.107 0.882 0.8328 1.059

0.020 -0.389 0.095 0.931 0.7945 1.172

0.015 -0.277 0.085 0.977 0.7584 1.288

0.009 -0.151 0.069 1.479 0.0012 1232.240

0.006 -0.103 0.061 1.473 0.0012 1227.892

0.005 -0.072 0.055 1.434 0.0012 1194.740

0.003 -0.050 0.049 1.383 0.0012 1152.780

0.003 -0.036 0.045 1.332 0.0012 1109.584

0.002 -0.026 0.041 1.282 0.0012 1068.332

0.002 -0.019 0.037 1.236 0.0012 1030.340

0.001 -0.014 0.035 1.195 0.0012 996.065

0.001 -0.011 0.032 1.159 0.0037 310.404

0.001 -0.009 0.031 1.128 0.0110 102.360

0.001 -0.007 0.029 1.101 0.0157 70.132

0.001 -0.006 0.028 1.077 0.0187 57.669

0.001 -0.005 0.027 1.056 0.0206 51.397

0.001 -0.004 0.026 1.039 0.0217 47.827

0.001 -0.004 0.025 1.024 0.0224 45.660

0.000 -0.003 0.025 1.012 0.0228 44.303

0.000 -0.003 0.024 1.002 0.0231 43.456

0.000 -0.003 0.024 0.995 0.0232 42.955

0.000 -0.003 0.024 0.989 0.0232 42.715

0.000 -0.003 0.024 0.986 0.0231 42.704

0.000 -0.003 0.024 0.985 0.0229 42.929


700/1097

0.000 -0.003 0.025 0.985 0.0227 43.443

0.001 -0.004 0.025 0.987 0.0222 44.355

0.001 -0.004 0.026 0.990 0.0216 45.874

0.001 -0.005 0.027 0.994 0.0206 48.386

0.001 -0.006 0.028 1.000 0.0190 52.678

0.001 -0.007 0.029 1.007 0.0166 60.583

0.001 -0.009 0.031 1.015 0.0131 77.5790.001 -0.011 0.033 1.024 0.0078 130.857

0.001 -0.014 0.035 1.034 0.0012 861.748

0.002 -0.018 0.037 1.045 0.0012 871.231

0.002 -0.024 0.040 1.058 0.0012 881.401

0.002 -0.031 0.043 1.071 0.0012 892.188

0.003 -0.041 0.047 1.084 0.0012 903.513

0.004 -0.055 0.051 1.098 0.0012 915.278

0.005 -0.072 0.055 1.113 0.0012 927.360

0.006 -0.095 0.060 1.128 0.0012 939.602


701/1097


702/1097


703/1097


704/1097


705/1097


706/1097


707/1097


708/1097


709/1097


710/1097


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713/1097


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715/1097


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723/1097


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728/1097


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731/1097


732/1097


733/1097


734/1097


735/1097


736/1097


737/1097


738/1097


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740/1097


741/1097


742/1097


743/1097


744/1097


745/1097


746/1097


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748/1097


749/1097


750/1097


751/1097


752/1097


753/1097


754/1097


755/1097


756/1097


757/1097


758/1097


759/1097


760/1097


761/1097


762/1097


763/1097


764/1097


765/1097


766/1097


767/1097


768/1097


769/1097


770/1097


771/1097


772/1097


773/1097


774/1097


775/1097


776/1097


777/1097


778/1097


779/1097


780/1097


781/1097


782/1097


783/1097


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785/1097


786/1097


787/1097


788/1097


789/1097


790/1097


791/1097


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793/1097


794/1097


795/1097


796/1097


797/1097


798/1097


799/1097

&/%799 9/6%3

Cz Ct Z/T dZ dMf Suma dZ

[-] [-] [-] pala [] pala [m] pala []

0.000 1.213 0.000 0.000 0.0000 0

0.000 1.212 0.000 0.000 0.0000 0.000

0.000 1.212 0.000 0.000 0.0000 0.000

0.000 1.205 0.000 0.000 0.0000 0.000

1.178 0.894 1.318 0.024 0.0005 0.024

1.203 0.852 1.412 0.030 0.0007 0.054

1.194 0.793 1.506 0.034 0.0008 0.088

1.173 0.733 1.600 0.039 0.0010 0.127

1.147 0.677 1.694 0.043 0.0012 0.170

1.119 0.626 1.788 0.047 0.0014 0.218

1.092 0.580 1.882 0.051 0.0015 0.269

1.066 0.540 1.975 0.055 0.0017 0.324

1.043 0.507 2.058 0.059 0.0020 0.384

1.020 0.482 2.114 0.063 0.0022 0.446

1.001 0.459 2.179 0.066 0.0024 0.513

0.984 0.438 2.248 0.070 0.0026 0.583

0.970 0.418 2.322 0.073 0.0029 0.656

0.959 0.400 2.398 0.077 0.0031 0.733

0.950 0.384 2.475 0.080 0.0034 0.812

0.942 0.369 2.554 0.083 0.0036 0.895

0.937 0.356 2.634 0.086 0.0039 0.981

0.934 0.344 2.715 0.089 0.0041 1.070

0.932 0.333 2.797 0.091 0.0044 1.161

0.932 0.324 2.879 0.094 0.0046 1.255

0.933 0.315 2.962 0.096 0.0049 1.350


800/1097

0.936 0.307 3.046 0.098 0.0051 1.448

0.940 0.300 3.132 0.099 0.0054 1.547

0.945 0.293 3.222 0.101 0.0056 1.648

0.952 0.287 3.317 0.102 0.0058 1.750

0.960 0.281 3.420 0.102 0.0060 1.852

0.969 0.274 3.535 0.103 0.0062 1.955

0.980 0.267 3.670 0.103 0.0063 2.0580.991 0.258 3.837 0.102 0.0065 2.160

1.004 0.249 4.035 0.102 0.0066 2.262

1.016 0.246 4.128 0.100 0.0066 2.362

1.029 0.244 4.222 0.099 0.0067 2.461

1.043 0.242 4.316 0.097 0.0067 2.558

1.057 0.240 4.409 0.094 0.0067 2.652

1.072 0.238 4.503 0.092 0.0066 2.744

1.087 0.237 4.597 0.089 0.0065 2.832

1.103 0.235 4.690 0.085 0.0064 2.918


801/1097


802/1097


803/1097


804/1097


805/1097


806/1097


807/1097


808/1097


809/1097


810/1097


811/1097


812/1097


813/1097


814/1097


815/1097


816/1097


817/1097


818/1097


819/1097


820/1097


821/1097


822/1097


823/1097


824/1097


825/1097


826/1097


827/1097


828/1097


829/1097


830/1097


831/1097


832/1097


833/1097


834/1097


835/1097


836/1097


837/1097


838/1097


839/1097


840/1097


841/1097


842/1097


843/1097


844/1097


845/1097


846/1097


847/1097


848/1097


849/1097


850/1097


851/1097


852/1097


853/1097


854/1097


855/1097


856/1097


857/1097


858/1097


859/1097


860/1097


861/1097


862/1097


863/1097


864/1097


865/1097


866/1097


867/1097


868/1097


869/1097


870/1097


871/1097


872/1097


873/1097


874/1097


875/1097


876/1097


877/1097


878/1097


879/1097


880/1097


881/1097


882/1097


883/1097


884/1097


885/1097


886/1097


887/1097


888/1097


889/1097


890/1097


891/1097


892/1097


893/1097


894/1097


895/1097


896/1097


897/1097


898/1097


899/1097

&/&=6%7

dT dMt pala Re!dim el ind$!ida

pala [] [m] secto" [g"/#] [m/s]

0.0000 0.0000 0 0.00

0.0108 0.0002 0.00 0.00

0.0138 0.0002 0.00 0.00

0.0170 0.0003 0.00 0.00

0.0183 0.0004 9.06 16.22

0.0209 0.0005 9.32 17.54

0.0228 0.0005 9.62 18.52

0.0243 0.0006 9.95 19.29

0.0255 0.0007 10.30 19.91

0.0265 0.0008 10.70 20.43

0.0273 0.0008 11.13 20.87

0.0280 0.0009 11.59 21.24

0.0288 0.0009 12.03 21.54

0.0297 0.0010 12.36 21.79

0.0305 0.0011 12.78 22.01

0.0311 0.0012 13.29 22.20

0.0316 0.0012 13.86 22.36

0.0320 0.0013 14.51 22.49

0.0323 0.0014 15.23 22.60

0.0325 0.0014 16.02 22.68

0.0326 0.0015 16.90 22.73

0.0326 0.0015 17.87 22.76

0.0326 0.0016 18.94 22.77

0.0325 0.0016 20.11 22.74

0.0323 0.0016 21.42 22.69


900/1097


901/1097


902/1097


903/1097


904/1097


905/1097


906/1097


907/1097


908/1097


909/1097


910/1097


911/1097


912/1097


913/1097


914/1097


915/1097


916/1097


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920/1097


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923/1097


924/1097


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937/1097


938/1097


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940/1097


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949/1097


950/1097


951/1097


952/1097


953/1097


954/1097


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958/1097


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960/1097


961/1097


962/1097


963/1097


964/1097


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966/1097


967/1097


968/1097


969/1097


970/1097


971/1097


972/1097


973/1097


974/1097

8/17/2019 A

Documents

Aeronautic Propeller Tester