global flyer

Naca 4412Alfa CL CD CL/CD Cm-18 #DIV/0! 0.095-17 #DIV/0! 0.095-16 -0.65 0.01 -65.0000 0.095-15 -0.7 0.015 -46.6667 0.095-14 -0.75 0.02 -37.5000 0.095-13 -0.78 0.022 -35.4545 0.095-12 -0.8 0.025 -32.0000 0.095-11 -0.75 0.02 -37.5000 0.095-10 -0.68 0.01 -68.0000 0.095-9 -0.55 0.0087 -63.2184 0.095-8 -0.45 0.008 -56.2500 0.095-7 -0.35 0.0075 -46.6667 0.095-6 -0.25 0.007 -35.7143 0.095-5 -0.15 0.0068 -22.0588 0.095-4 0 0.0065 0.0000 0.095-3 0.07 0.0064 10.9375 0.095-2 0.17 0.0063 26.9841 0.095-1 0.27 0.0062 43.5484 0.0950 0.4 0.0062 64.5161 0.0951 0.5 0.0062 80.6452 0.0952 0.6 0.0062 96.7742 0.0953 0.7 0.0062 112.9032 0.0954 0.8 0.0064 125.0000 0.0955 0.9 0.0067 134.3284 0.0956 1 0.0078 128.2051 0.0957 1.1 0.0088 125.0000 0.0958 1.22 0.0109 111.9266 0.0959 1.33 0.012 110.8333 0.095

10 1.4 0.0135 103.7037 0.09511 1.5 0.0162 92.5926 0.09512 1.55 0.0172 90.1163 0.09513 1.6 0.019 84.2105 0.09514 1.62 0.019 85.2632 0.09515 1.64 0.02 82.0000 0.09516 1.59 0.025 63.6000 0.09517 1.55 0.03 51.6667 0.09518 1.47 0.035 42.0000 0.095

Desempeños 1.64 0.0062 134.3284 0.09515° 1°-3° 5°

Distribucion Eliptica

Peso del Avión 5000 Kg 49050

Velocidad de Vuelo 65 m/s 234Altitud de Vuelo 3000 m 9842.51969

Densidad 0.90926 Kg/m^3

Viscocidad 1.48E-05 Kg/(m*s)Reynolds 4.18E+06

Cuerda de Raiz 1.4 mCuerda de Punta 0.7 m

Conicidad 0.500Envergadura 36 m

Superficie Alar 37.8 m^2

Alargamiento 34.286

Torcimiento A. -2Torcimiento G. -2 °

Estación Y(m)

0 -4 0.1 5 00.1 -4 0.1 4.7 1.80.2 -4 0.1 4.4 3.60.3 -4 0.1 4.1 5.40.4 -4 0.1 3.8 7.20.5 -4 0.1 3.5 90.6 -4 0.1 3.2 10.80.7 -4 0.1 2.9 12.60.8 -4 0.1 2.6 14.4

0.85 -4 0.1 2.45 15.30.9 -4 0.1 2.3 16.2

0.95 -4 0.1 2.15 17.10.975 -4 0.1 2.075 17.55

1 -4 0.1 2 18

Variación del ángulo de 0 levantamiento

Variación de la pendiente del Perfil

Variación del ángulo de ataque

DATOS DEL EMPENAJE HORIZONTAL

CR 0.5 mCP 0.5 m

CONICIDAD 1ENVERGADURA 11.44 m

SUPERFICIE ALAR 5.72 m^2ALARGAMIENTO 22.88ÁNGULO DE A. R -ÁNGULO DE A.C. -TORCIMENTO G. 0

Eficiencia E.H 80%

Torcimiento G. ESTACIÓN Y CY0 0 0 0.50 0.2 1.144 0.50 0.4 2.288 0.50 0.6 3.432 0.50 0.8 4.576 0.50 0.9 5.148 0.50 0.95 5.434 0.50 0.975 5.577 0.50 1 5.72 0.5

Torcimiento G. ESTACIÓN Y CY0 0 0 0.50 0.2 1.144 0.50 0.4 2.288 0.50 0.6 3.432 0.50 0.8 4.576 0.50 0.9 5.148 0.50 0.95 5.434 0.50 0.975 5.577 0.50 1 5.72 0.5

ESTACIÓN ClE.H CLE.H0 0.105937557847616 0.10652931

0.2 0.105937557847616 0.11162153

0.4 0.105937557847616 0.113994470.6 0.105937557847616 0.111971080.8 0.105937557847616 0.100412040.9 0.105937557847616 0.08225897

0.95 0.105937557847616 0.064444780.975 0.105937557847616 0.0478314

1 0 0

N CL del Avión Circulación 0

Km/Hr 0.6756 29.3525ft

Cl=0 Punta

0.1 -4

Cl=0 Raíz

0.1 -4

Ángulo Ataque Raíz Valor de TAO5 0.25

2

Cuerda (m) Ángulo Efectivo CL local

29.3525 1.4 1734.78887970166 4.99372809698924 0.899372809729.2054 1.33 1726.09314133542 4.69372809698924 0.869372809728.7595 1.26 1699.73902668941 4.39372809698924 0.839372809728.0005 1.19 1654.8831185296 4.09372809698924 0.809372809726.9020 1.12 1589.9602712001 3.79372809698924 0.779372809725.4200 1.05 1502.37124002438 3.49372809698924 0.749372809723.4820 0.98 1387.83110376133 3.19372809698924 0.719372809720.9619 0.91 1238.88706230214 2.89372809698924 0.689372809717.6115 0.84 1040.873327821 2.59372809698924 0.659372809715.4624 0.805 913.8567485418 2.44372809698924 0.644372809712.7945 0.77 756.176941499768 2.29372809698924 0.62937280979.1653 0.735 541.687654069034 2.14372809698924 0.61437280976.5223 0.7175 385.478520894636 2.06872809698924 0.60687280970.0000 0.7 0 1.99372809698924 0.5993728097

DATOS DEL PERFIL

Pendiente del Perfil Punta

Pendiente del Perfil Raíz

Ángulo de Ataque Punta

Variación de la Circulación

Levantamiento a lo largo de la

semienvergadura

PERFIL RAIZ NACA 0009 0.1125 1.05PREFIL PUNTA NACA 0009 0.1125 1.05

PENDIENTE PR

Eficiencia E.H 0.8 CLE.H 0.2790218389

Cl=Clb+CL*Cla

CL1

La Lb Cla Clb -1.07 -0.25 1.07 0 -

1.069 -0.176 1.069 0 -1.065 -0.02 1.065 0 -1.046 0.1 1.046 0 -0.962 0.16 0.962 0 -0.846 0.16 0.846 0 -0.73 0.13 0.73 0 -

0.615 0.091 0.615 0 -0 0 0 0 0

La Lb Cla Clb ClE.H1.07 0 1.07 0 0.279022

1.069 0 1.069 0 0.2790221.065 0 1.065 0 0.2790221.046 0 1.046 0 0.2790220.962 0 0.962 0 0.2790220.846 0 0.846 0 0.2790220.73 0 0.73 0 0.279022

0.615 0 0.615 0 0.2790220 0 0 0 0.000000

LE.H N/m390.6995369

375.58961006

PENDIENTE DE LEVANTAMIENTO

FACTOR DE CORRECCIÓN

349.07014662308.98258561246.69268313189.64500015143.69848792104.84439033

0

CDi

0.00627190301076 0.00423703

0.1

Pendiente de ala

0.09988408404169

Levantamiento Local CDi

2418.53620470029 0.007509593567282220.96900564028 0.007016960502582031.46921593026 0.006541038706911850.03683557025 0.006081828180261676.67186456023 0.005639328922631511.37430290022 0.005213540934031354.1441505902 0.00480446421446

1204.98140763019 0.004412098763911063.88607402017 0.00403644458238996.363685721417 0.0038548842175930.858149760159 0.00367750166988867.369466136403 0.00350429693951836.381443951086 0.0034192612558

0 0.0033352700264

DATOS DEL PERFIL

Ángulo inducido de Ataque

Pendiente Promedio

0.1071428571428570.107142857142857

0.107142857142857 DATOS DEL AVIÓN

W MAX 11023 LB 5048.534VEL. C 65 m/sDENSIDAD. C 0.90926 Kg/m^3Superficie 37.8 m^2

CL tot 0.68211514

Cl=Clb+CL*Cla

CL2 CL3 CL4 CL5 CL6 CL7

- -0.9 -1 -1.3 -1.1 -0.9- -0.963 -1.07 -1.391 -1.177 -0.963- -1.029447 -1.14383 -1.486979 -1.258213 -1.029447- -1.096361055 -1.21817895 -1.58363264 -1.33999685 -1.09636106- -1.14679366353 -1.27421518 -1.65647974 -1.4016367 -1.14679366- -1.1032155043159 -1.225795 -1.59353351 -1.34837451 -1.1032155- -0.9333203166512 -1.03702257 -1.34812935 -1.14072483 -0.93332032- -0.6813238311554 -0.75702648 -0.98413442 -0.83272913 -0.68132383- -0.4190141561606 -0.46557128 -0.60524267 -0.51212841 -0.419014160 0 0 0 0 0

CLE.H LE.H N/m0.298553367571584 215.0493060.298274345732732 214.8483260.297158258377324 214.0444030.291856843439137 210.2257700.268419008975574 193.3433950.236052475668748 170.0296380.203685942361922 146.7158820.171598430893948 123.603106

0 0.000000

PENDIENTE DE LEVANTAMIENTO

CORREGIDA

0 1 2 3 4 5 60.0

50.0

100.0

150.0

200.0

250.0

Distribucion de Levantamiento del Empenaje Horizontal

Y(m)

L (N

/m)

0 1 2 3 4 5 60.0

50.0

100.0

150.0

200.0

250.0


Y(m)

L (N

/m)

KG 49526.1185

Cl=Clb+CL*Cla

CL8 CL9 CL10 CL11 CL12 CL13 CL14 CL15

-0.65 -0.4 -0.2 0 0.2 0.4 0.65 0.9-0.6955 -0.428 -0.214 0 0.214 0.428 0.6955 0.963

-0.7434895 -0.457532 -0.228766 0 0.228766 0.457532 0.7434895 1.029447-0.79181632 -0.48727158 -0.24363579 0 0.24363579 0.48727158 0.79181632 1.096361055-0.82823987 -0.50968607 -0.25484304 0 0.25484304 0.50968607 0.82823987 1.146793664-0.79676675 -0.490318 -0.245159 0 0.245159 0.490318 0.79676675 1.103215504-0.67406467 -0.41480903 -0.20740451 0 0.20740451 0.41480903 0.67406467 0.933320317-0.49206721 -0.30281059 -0.1514053 0 0.1514053 0.30281059 0.49206721 0.681323831-0.30262134 -0.18622851 -0.09311426 0 0.09311426 0.18622851 0.30262134 0.419014156

0 0 0 0 0 0 0 0

0 1 2 3 4 5 60.0

50.0

100.0

150.0

200.0

250.0


Y(m)

L (N

/m)

0 0.2 0.4 0.6 0.8 1 1.20

0.2

0.4

0.6

0.8

1

1.2

1.4

CL MAX PERFIL0.91.040.65

0 1 2 3 4 5 60.0

50.0

100.0

150.0

200.0

250.0


Y(m)

L (N

/m)

Cl=Clb+CL*Cla

CL16 CL17 CL18 CL19 CL20

1.04 1.3 1.3 1.1 1.05 1.32 ESTACIÓN1.1128 1.391 1.391 1.177 1.1235 1.32 0

1.1895832 1.486979 1.486979 1.258213 1.2010215 1.32 0.21.26690611 1.58363264 1.58363264 1.33999685 1.2790879 1.32 0.41.32518379 1.65647974 1.65647974 1.4016367 1.33792594 1.32 0.61.2748268 1.59353351 1.59353351 1.34837451 1.28708476 1.32 0.8

1.07850348 1.34812935 1.34812935 1.14072483 1.0888737 1.32 0.90.78730754 0.98413442 0.98413442 0.83272913 0.7948778 1.32 0.950.48419414 0.60524267 0.60524267 0.51212841 0.48884985 1.32 0.975

0 0 0 0 0 1.32 1

CL MAX PERFIL

0 0.2 0.4 0.6 0.8 1 1.20

0.2

0.4

0.6

0.8

1

1.2

1.4

CL MAX PERFIL0.91.040.65

Cl=Clb+CL*Cla

CL10 CL11 CL12 CL13 CL14 CL15 CL16 CL17

-0.2 0.0 0.2 0.4 0.7 0.9 1.1 1.3-0.2011 0.0 0.2 0.4022 0.6536 0.9050 1.1061 1.3073-0.2119 0.0 0.2119 0.4238 0.6887 0.9536 1.1655 1.3774-0.2280 0.0 0.2280 0.4560 0.7411 1.0261 1.2541 1.4822-0.2410 0.0 0.2410 0.4820 0.7833 1.0845 1.3256 1.5666-0.2284 0.0 0.2284 0.4569 0.7424 1.0280 1.2564 1.4849-0.1774 0.0 0.1774 0.3548 0.5765 0.7982 0.9756 1.1530-0.1079 0.0 0.1079 0.2158 0.3507 0.4856 0.5935 0.7014-0.0487 0.0 0.0487 0.0974 0.1583 0.2192 0.2680 0.31670.0000 0.0 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000

Cl=Clb+CL*Cla

CL18 CL19 CL20

1.3 1.1 1.1 1.31.3073 1.1061 1.0559 1.31.3774 1.1655 1.1125 1.31.4822 1.2541 1.1971 1.31.5666 1.3256 1.2653 1.31.4849 1.2564 1.1993 1.31.1530 0.9756 0.9312 1.30.7014 0.5935 0.5665 1.30.3167 0.2680 0.2558 1.30.0000 0.0000 0.0000 1.3

CL MAX PERFIL

CRECE 0 PERFIL 0.4 CREUCE 0 DEL ALA 0.39953634CL MAX 1.65 CL MAXPENDIENTE PERFIL 0.1 PENDIENTE ALA 0.09988408ALFA CERO LEVANTAMIENTO -4 ALFA CERO LEVANTAMIENTO -4

PERFIL ALAALFA CL ALFA CL-18 -1.4000 -18 -1.39837718-17 -1.3000 -17 -1.29849309-16 -1.2000 -16 -1.19860901-15 -1.1000 -15 -1.09872492-14 -1.0000 -14 -0.99884084-13 -0.9000 -13 -0.89895676-12 -0.8000 -12 -0.79907267-11 -0.7000 -11 -0.69918859-10 -0.6000 -10 -0.5993045-9 -0.5000 -9 -0.49942042-8 -0.4000 -8 -0.39953634-7 -0.3000 -7 -0.29965225-6 -0.2000 -6 -0.19976817-5 -0.1000 -5 -0.09988408-4 0.0000 -4 0-3 0.1000 -3 0.09988408-2 0.2000 -2 0.19976817-1 0.3000 -1 0.299652250 0.4000 0 0.399536341 0.5000 1 0.499420422 0.6000 2 0.59930453 0.7000 3 0.699188594 0.8000 4 0.799072675 0.9000 5 0.898956766 1.0000 6 0.998840847 1.1000 7 1.098724928 1.2000 8 1.198609019 1.3000 9 1.29849309

10 1.4000 10 1.3983771811 1.5000 11 1.4982612612 1.6000 12 1.59814534

12.5 1.6500 13 1.5513 1.6500 14 1.514 1.6300 15.3 1.415 1.6000 16 1.316 1.5000 17 1.218 1.4000 18 1.1

-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6

1.8

CL ALA VS ALFA CL PERFIL VS ALFA

ALFA

CL

CREUCE 0 DEL ALA 0CL MAX 1.32 CL MAX 1.04PENDIENTE PERFIL 0.107142857 PENDIENTE ALA 0.09871ALFA CERO LEVANTAMIENTO 0 ALFA CERO LEVANTAMIENTO 0

PERFIL EMPENAJE HORIZONTALALFA CL ALFA CL-17 -1.8214 -17 -1.67807-16 -1.7143 -16 -1.57936-15 -1.6071 -15 -1.48065-14 -1.5000 -14 -1.38194-13 -1.3929 -13.5 -1.332585

-12.4 -1.3286 -13 -1.28323-12 -1.2857 -12 -1.18452-11 -1.1786 -11 -1.08581-10 -1.0714 -10 -0.9871-9 -0.9643 -9 -0.88839-8 -0.8571 -8 -0.78968-7 -0.7500 -7 -0.69097-6 -0.6429 -6 -0.59226-5 -0.5357 -5 -0.49355-4 -0.4286 -4 -0.39484-3 -0.3214 -3 -0.29613-2 -0.2143 -2 -0.19742-1 -0.1071 -1 -0.098710 0.0000 0 01 0.1071 1 0.098712 0.2143 2 0.197423 0.3214 3 0.296134 0.4286 4 0.394845 0.5357 5 0.493556 0.6429 6 0.592267 0.7500 7 0.690978 0.8571 8 0.789689 0.9643 9 0.88839

10 1.0714 10 0.987111 1.1786 10.6 1.046326

12.4 1.3286 11.6 1.0413 1.3929 12.6 1.24374614 1.5000 13.5 1.33258515 1.6071 14 1.3819416 1.7143 15 1.48065 -5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19

-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6

CL PERFIL EMPENAJE VS ALFA CL EMPENAJE HORIZANTAL VS ALFA

ALFA

CL

17 1.8214 16 1.5793618 1.9286 17 1.67807

-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6


ALFA

CL

CL ALA NECESARIO 0.66ÁNGULO NECESARIO 2.60765933

-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6

1.8


ALFA

CL

CL EH NECESARIO 0.085ÁNGULO NECESARIO 0.8611083

-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6


ALFA

CL

-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6


ALFA

CL

-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6

1.8


ALFA

CL

-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6


ALFA

CL

ALAPERFIL NACA 23012

ALFA CL CD CM C/4 CM C.A. FINEZA A.-20 - - - - --18 -0.9 0.011 -81.81818182-16 -0.9 0.011 -81.81818182-14 -1.2 - --12 -1.15 - --10 -0.95 0.011 -86.36363636-8 -0.7 0.0085 -82.35294118-6 -0.5 0.008 -62.5-4 -0.3 0.0075 -40-2 -0.1 0.0075 -13.333333330 0.1 0.006 16.6666666672 0.3 0.006 504 0.55 0.0065 84.6153846156 0.75 0.0069 108.695652178 1 0.0075 133.33333333

10 1.2 0.01 12012 1.4 0.014 10014 1.55 0.0185 83.78378378416 1.7 - - - -18 1.35 0.0135 10020 - - - - -

REYNOLDS 3000m REYNOLDS 6000mVELOCIDAD 90 VELOCIDAD 84.368DENSIDAD 0.9092 DENSIDAD 0.6596

VISCOCIDAD 1.73E-05 VISCOCIDAD 1.82E-05LONGITUD 1.72E+00 LONGITUD 1.72E+00

REYNOLDS 8.11E+06 REYNOLDS 5.23E+06

ALA EMPENAJE HORIZONTALPERFIL NACA 23018 PERFIL NACA 0009

ALFA CL CD CM C/4 CM C.A. FINEZA A. ALFA-20 - - - - - -20-18 -1.3 0.015 -86.66666667 -18-16 -1.4 - - - - -16-14 -1.3 0.015 -86.66666667 -14-12 -1.15 0.0125 -92 -12-10 -0.95 0.011 -86.36363636 -10-8 -0.75 0.0095 -78.94736842 -8-6 -0.5 0.009 -55.55555556 -6-4 -0.3 0.008 -37.5 -4-2 -0.1 0.007 -14.28571429 -20 0.1 0.007 14.285714286 02 0.3 0.007 42.857142857 24 0.5 0.0075 66.666666667 46 0.7 0.0075 93.333333333 68 0.91 0.0085 107.05882353 8

10 1.15 0.01 115 1012 1.3 0.013 100 1214 1.55 0.018 86.111111111 1416 1.6 - - - - 1618 1.05 0.0095 110.52631579 1820 1 0.009 111.11111111 20

EMPENAJE HORIZONTALPERFIL NACA 0009 PERFIL NACA 4412

CL CD CM C/4 CM C.A. FINEZA A. ALFA CL- - - - - -18- - - - - -17

-0.9 0.085 -10.5882353 -16 -0.65-1 0.01 -100 -15 -0.7

-1.3 - #VALUE! -14 -0.75-1.1 0.014 -78.5714286 -13 -0.78-0.9 0.0085 -105.882353 -12 -0.8

-0.65 0.0075 -86.6666667 -11 -0.75-0.4 0.0065 -61.5384615 -10 -0.68-0.2 0.006 -33.3333333 -9 -0.55

0 0.0055 0 -8 -0.450.2 0.0055 36.3636364 -7 -0.350.4 0.006 66.6666667 -6 -0.25

0.65 0.007 92.8571429 -5 -0.150.9 0.0085 105.882353 -4 01.1 0.0105 104.761905 -3 0.071.3 0.0135 96.2962963 -2 0.171.3 0.0135 96.2962963 -1 0.271.1 0.0105 104.761905 0 0.4

1.05 0.0095 110.526316 1 0.5- - - - - 2 0.6

3 0.74 0.85 0.96 17 1.18 1.229 1.33

10 1.411 1.512 1.5513 1.614 1.6215 1.6416 1.5917 1.5518 1.47

U ALAAR

PERFIL NACA 4412 PERFIL NACA 4412 PERFIL NACA 0009 ALACD ALFA CL CD ALFA CL CD ALFA

-18 -18 0 0 -18-17 -17 0 0 -17

0.01 -16 -0.65 0.01 -16 -0.9 0.0085 -160.015 -15 -0.7 0.015 -15 -0.9 0.0085 -150.02 -14 -0.75 0.02 -14 -1.3 0.017 -14

0.022 -13 -0.78 0.022 -13 -1.3 0.017 -130.025 -12 -0.8 0.025 -12 -1.25 0.015 -120.02 -11 -0.75 0.02 -11 -1.2 0.014 -110.01 -10 -0.68 0.01 -10 -1.1 0.011 -10

0.0087 -9 -0.55 0.0087 -9 -1 0.01 -90.008 -8 -0.45 0.008 -8 -0.9 0.0087 -8

0.0075 -7 -0.35 0.0075 -7 -0.8 0.008 -70.007 -6 -0.25 0.007 -6 -0.65 0.0075 -6

0.0068 -5 -0.15 0.0068 -5 -0.55 0.007 -50.0065 -4 0 0.0065 -4 -0.4 0.0065 -40.0064 -3 0.07 0.0064 -3 -0.3 0.006 -30.0063 -2 0.17 0.0063 -2 -0.2 0.006 -20.0062 -1 0.27 0.0062 -1 -0.1 0.0055 -10.0062 0 0.4 0.0062 0 0 0.005 00.0062 1 0.5 0.0062 1 0.1 0.005 10.0062 2 0.6 0.0062 2 0.2 0.005 20.0062 3 0.7 0.0062 3 0.3 0.006 30.0064 4 0.8 0.0064 4 0.4 0.006 40.0067 5 0.9 0.0067 5 0.55 0.0065 50.0078 6 1 0.0078 6 0.65 0.007 60.0088 7 1.1 0.0088 7 0.75 0.0075 70.0109 8 1.22 0.0109 8 0.85 0.008 80.012 9 1.33 0.012 9 1 0.0095 9

0.0135 10 1.4 0.0135 10 1.1 0.0115 100.0162 11 1.5 0.0162 11 1.2 0.012 110.0172 12 1.55 0.0172 12 1.3 0.0135 120.019 13 1.6 0.019 13 1.3 0.0135 130.019 14 1.62 0.019 14 1.25 0.014 140.02 15 1.64 0.02 15 1.2 0 15

0.025 16 1.59 0.025 16 1.15 0 160.03 17 1.55 0.03 17 1.05 0 17

0.035 18 1.47 0.035 18 1 0 18

1 U EH 134.2857 Conicidad 0.5000 AR 22.8800 Conicidad 1.0000

ALA EMPENAJE HORIZONTALCL ALA CD o ALA CD i ALA CD ALA ALFA CL EH CD o EH CD i EH-1.3984 0 0.0182 0.0182 -18 -1.6781 0.0392-1.2985 0 0.0157 0.0157 -17 -1.5794 0.0347-1.1986 0.01 0.0133 0.0233 -16 -1.4807 0.0085 0.0305-1.0987 0.015 0.0112 0.0262 -15 -1.3819 0.0085 0.0266-0.9988 0.02 0.0093 0.0293 -14 -1.3326 0.017 0.0247-0.8990 0.022 0.0075 0.0295 -13 -1.2832 0.017 0.0229-0.7991 0.025 0.0059 0.0309 -12 -1.1845 0.015 0.0195-0.6992 0.02 0.0045 0.0245 -11 -1.0858 0.014 0.0164-0.5993 0.01 0.0033 0.0133 -10 -0.9871 0.011 0.0136-0.4994 0.0087 0.0023 0.0110 -9 -0.8884 0.01 0.0110-0.3995 0.008 0.0015 0.0095 -8 -0.7897 0.0087 0.0087-0.2997 0.0075 0.0008 0.0083 -7 -0.6910 0.008 0.0066-0.1998 0.007 0.0004 0.0074 -6 -0.5923 0.0075 0.0049-0.0999 0.0068 0.0001 0.0069 -5 -0.4936 0.007 0.00340.0000 0.0065 0.0000 0.0065 -4 -0.3948 0.0065 0.00220.0999 0.0064 0.0001 0.0065 -3 -0.2961 0.006 0.00120.1998 0.0063 0.0004 0.0067 -2 -0.1974 0.006 0.00050.2997 0.0062 0.0008 0.0070 -1 -0.0987 0.0055 0.00010.3995 0.0062 0.0015 0.0077 0 0.0000 0.005 0.00000.4994 0.0062 0.0023 0.0085 1 0.0987 0.005 0.00010.5993 0.0062 0.0033 0.0095 2 0.1974 0.005 0.00050.6992 0.0062 0.0045 0.0107 3 0.2961 0.006 0.00120.7991 0.0064 0.0059 0.0123 4 0.3948 0.006 0.00220.8990 0.0067 0.0075 0.0142 5 0.4936 0.0065 0.00340.9988 0.0078 0.0093 0.0171 6 0.5923 0.007 0.00491.0987 0.0088 0.0112 0.0200 7 0.6910 0.0075 0.00661.1986 0.0109 0.0133 0.0242 8 0.7897 0.008 0.00871.2985 0.012 0.0157 0.0277 9 0.8884 0.0095 0.01101.3984 0.0135 0.0182 0.0317 10 0.9871 0.0115 0.01361.4983 0.0162 0.0208 0.0370 11 1.0463 0.012 0.01521.5981 0.0172 0.0237 0.0409 12 1.0400 0.0135 0.01501.5500 0.019 0.0223 0.0413 13 1.2437 0.0135 0.02151.5000 0.019 0.0209 0.0399 14 1.3326 0.014 0.02471.4000 0.02 0.0182 0.0382 15 1.3819 0.02 0.02661.3000 0.025 0.0157 0.0990 16 1.4807 0.03 0.03051.2000 0.03 0.0134 0.1050 17 1.5794 0.04 0.03471.1000 0.035 0.0112 0.1100 18 1.6781 0.06 0.0392

EMPENAJE HORIZONTALCD EH0.03920.03470.03900.03510.04170.03990.03450.03040.02460.02100.01740.01460.01240.01040.00870.00720.00650.00560.00500.00510.00550.00720.00820.00990.01190.01410.01670.02050.02510.02720.02850.03500.03870.04660.06050.07470.0992

0.000 0.005 0.010 0.015 0.020 0.025 0.030 0.035 0.040-1.0

-0.8

-0.6

-0.4

-0.2

0.0

0.2

0.4

0.6

0.8

1.0

1.2

1.4

1.6

1.8

G. Polar Ala CL vs CD

CD Ala

CL a

la

0.000 0.005 0.010 0.015 0.020 0.025 0.030 0.035 0.040-0.1

0.1

0.3

0.5

0.7

0.9

1.1

1.3

G. Polar EH CL VS CD

CD

CL

Tren de Aterrizaje

Superficie Alar 37.8

Elemento Observaciones

1 2 llanta 0.11849 0.6 0.00376158732 2 cilindro 0.0205 0.6 0.000650793653 2 cilindro 0.06798 0.6 0.002158095244 2 cilindro 0.029659 0.6 0.000941555565 2 C. Fuselado 0.13825 0.12 0.000877777786 1 llanta 0.0707 0.6 0.001122222227 1 Placa Plana 0.04045 2 0.002140211648 1 cilindro 0.0103 0.6 0.000163492069 1 cilindro 0.01316 0.6 0.00020888889

10 1 C. Fuselado 0.055296 0.12 0.00017554286

Total 0.0122001672

Numero de Elementos

Superficie m2

Cd del elemento (superficie Frontal)

Cd' Del elemento

Densidad 0.90926 q Fl 1920.81175Velociad Ala 65 Superficie Ala 37.8

Datos del Ala

Alfa 0 del ala 2.607659332 Alfa 0 del EH 0.861108297

CREUCE 0 DEL ALA 0.399536336 CRECE 0 PERFIL 0.4

CL MAX 1.4 CL MAX 1.65

PENDIENTE ALA 0.099884084 PENDIENTE PERFIL 0.1

-4 -4

K 20U ALA 1

AR 34.2857 Conicidad 0.5000L (dist. Centro Aero) 7.262

C. Aerodinamica 1.05

0 1 2 3 4 5

CD Fus0.07 -4.00 -1.39 0.2605 0.0065 0.00060.06 -3.00 -0.39 0.3603 0.0064 0.00120.06 -2.00 0.61 0.4602 0.0063 0.00200.05 -1.00 1.61 0.5601 0.0062 0.00290.05 0.00 2.61 0.6600 0.0062 0.00400.05 1.00 3.61 0.7599 0.0062 0.00540.06 2.00 4.61 0.8598 0.0062 0.00690.06 3.00 5.61 0.9597 0.0062 0.00850.07 4.00 6.61 1.0595 0.0064 0.01040.08 5.00 7.61 1.1594 0.0067 0.01250.08 6.00 8.61 1.2593 0.0078 0.01470.09 7.00 9.61 1.3592 0.0088 0.01720.11 8.00 10.61 1.4591 0.0109 0.01980.12 9.00 11.61 1.5590 0.012 0.02260.13 10.00 12.61 1.6588 0.0135 0.02550.15 11.00 13.61 1.4000 0.0162 0.01820.16 12.00 14.61 1.3800 0.0172 0.01770.17 13.00 15.61 1.3600 0.019 0.01720.19 14.00 16.61 1.3000 0.019 0.01570.20 15.00 17.61 1.2500 0.02 0.01450.21 16.00 18.61 1.2000 0.025 0.01340.23 17.00 19.61 1.1500 0.03 0.01230.24 18.00 20.61 1.1000 0.035 0.01120.25 19.00 21.61 1.0500 0.0400 0.0102

ALFA CERO LEVANTAMIENTO


aF aA CLA CDOA CDiA

0.27 20.00 22.61 1.0000 0.0450 0.0093

1 15 26 30aF CLTS/A CDTS/AyTA Fineza-4 0.220 0.024 9.1717-3 0.330 0.024 13.7705-2 0.441 0.024 18.0635-1 0.552 0.025 22.12910 0.662 0.026 25.77521 0.773 0.027 28.28242 0.884 0.029 30.34733 0.994 0.031 31.89164 1.105 0.034 32.83945 1.215 0.037 33.04436 1.326 0.041 32.63357 1.437 0.045 31.99918 1.547 0.051 30.29899 1.658 0.056 29.6189

10 1.768 0.062 28.639811 1.525 0.058 26.143112 1.517 0.060 25.202613 1.509 0.063 24.081114 1.462 0.062 23.391415 1.424 0.064 22.378716 1.387 0.069 20.133717 1.283 0.072 17.904218 1.231 0.076 16.108519 1.177 0.081 14.505320 1.121 0.086 13.0539

B max 33.0443

Densidad 0.90926 q EH 1080.456609375Velocidad EH 48.75 Superficie EH 5.72 Superficie EV

Datos del Empenaje Horizontal Datos del Empenaje Vertical

CREUCE 0 DEL ALA 0CD

CL MAX 1.32 CL MAX 1.04

PENDIENTE PERFIL 0.107142857 PENDIENTE ALA 0.09871

0 0

U EH 0.999AR 22.88 Conicidad 1

6 7 8 9 10 11

d0.0071 0.2647 -3.4036 -0.3360 -0.0407 0.00650.0076 0.3663 -2.5052 -0.2473 -0.0299 0.0060.0083 0.4678 -1.6067 -0.1586 -0.0192 0.0060.0091 0.5693 -0.7082 -0.0699 -0.0085 0.00550.0102 0.6708 0.1903 0.0188 0.0023 0.0050.0116 0.7724 1.0887 0.1075 0.0130 0.0050.0131 0.8739 1.9872 0.1962 0.0237 0.0050.0147 0.9754 2.8857 0.2848 0.0345 0.0060.0168 1.0769 3.7842 0.3735 0.0452 0.0060.0192 1.1785 4.6826 0.4622 0.0560 0.00650.0225 1.2800 5.5811 0.5509 0.0667 0.0070.0260 1.3815 6.4796 0.6396 0.0774 0.00750.0307 1.4830 7.3781 0.7283 0.0882 0.0080.0346 1.5846 8.2765 0.8170 0.0989 0.00950.0390 1.6861 9.1750 0.9057 0.1096 0.01150.0344 1.4230 10.4381 1.0303 0.1247 0.0120.0349 1.4027 11.4584 1.1311 0.1369 0.01350.0362 1.3823 12.4788 1.2318 0.1491 0.01350.0347 1.3214 13.5397 1.3365 0.1618 0.0140.0345 1.2705 14.5906 1.4402 0.1744 0.01450.0384 1.2197 15.6414 1.5440 0.1869 0.0150.0423 1.1689 16.6922 1.1000 0.1332 0.01550.0462 1.1181 17.7430 1.0800 0.1307 0.0160.0502 1.0673 18.7939 1.0500 0.1271 0.0165



CDA aEH CLEH CL’EH CDoEH

0.0543 1.0164 19.8447 1.0000 0.1211 0.0170

4.4975Datos del Empenaje Vertical CD BAR

0.011 0.6

SUPERFICIE BAR

0.3

12 13 14 15 16 17 18

0.0016 0.0081 0.0010 0.2198 0.0013 0.0095 0.00000.0009 0.0069 0.0008 0.3304 0.0013 0.0095 0.00000.0004 0.0064 0.0008 0.4410 0.0013 0.0095 0.00000.0001 0.0056 0.0007 0.5517 0.0013 0.0095 0.00000.0000 0.0050 0.0006 0.6623 0.0013 0.0095 0.00000.0002 0.0052 0.0006 0.7729 0.0013 0.0095 0.00000.0005 0.0055 0.0007 0.8835 0.0013 0.0095 0.00000.0011 0.0071 0.0009 0.9941 0.0013 0.0095 0.00000.0019 0.0079 0.0010 1.1048 0.0013 0.0095 0.00000.0030 0.0095 0.0011 1.2154 0.0013 0.0095 0.00000.0042 0.0112 0.0014 1.3260 0.0013 0.0095 0.00000.0057 0.0132 0.0016 1.4366 0.0013 0.0095 0.00000.0074 0.0154 0.0019 1.5472 0.0013 0.0095 0.00000.0093 0.0188 0.0023 1.6579 0.0013 0.0095 0.00000.0114 0.0229 0.0028 1.7685 0.0013 0.0095 0.00000.0148 0.0268 0.0032 1.5247 0.0013 0.0095 0.00000.0178 0.0313 0.0038 1.5169 0.0013 0.0095 0.00000.0211 0.0346 0.0042 1.5091 0.0013 0.0095 0.00000.0249 0.0389 0.0047 1.4618 0.0013 0.0095 0.00000.0289 0.0434 0.0053 1.4244 0.0013 0.0095 0.00000.0332 0.0482 0.0058 1.3869 0.0013 0.0095 0.00000.0169 0.0324 0.0039 1.2832 0.0013 0.0095 0.00000.0162 0.0322 0.0039 1.2307 0.0013 0.0095 0.00000.0154 0.0319 0.0039 1.1771 0.0013 0.0095 0.0000

CDiEH CDEH CD’EH CLTS/A CD’EV CD’BAR CD’M

0.0139 0.0309 0.0037 1.1211 0.0013 0.0095 0.0000

Cuerda AeroPendiente CD Boom 1.05

0.35 0.6 Cuerfa Flap0.453

SUPERFICIE FUS Superficie Boom Superficie Flap Grados

1.237 0.908 1.655 30

19 20 21 22 23 24

0.0122 0.0021 0.0016 0.0281 0.1313 0.00620.0122 0.0020 0.0014 0.0278 0.1313 0.00620.0122 0.0019 0.0014 0.0276 0.1313 0.00620.0122 0.0017 0.0013 0.0273 0.1313 0.00620.0122 0.0016 0.0012 0.0270 0.1313 0.00620.0122 0.0017 0.0013 0.0273 0.1313 0.00620.0122 0.0019 0.0014 0.0276 0.1313 0.00620.0122 0.0020 0.0014 0.0278 0.1313 0.00620.0122 0.0021 0.0016 0.0281 0.1313 0.00620.0122 0.0025 0.0018 0.0287 0.1313 0.00620.0122 0.0026 0.0019 0.0290 0.1313 0.00620.0122 0.0029 0.0022 0.0295 0.1313 0.00620.0122 0.0036 0.0026 0.0307 0.1313 0.00620.0122 0.0039 0.0029 0.0313 0.1313 0.00620.0122 0.0044 0.0032 0.0321 0.1313 0.00620.0122 0.0048 0.0035 0.0329 0.1313 0.00620.0122 0.0052 0.0038 0.0337 0.1313 0.00620.0122 0.0057 0.0042 0.0345 0.1313 0.00620.0122 0.0061 0.0045 0.0353 0.1313 0.00620.0122 0.0065 0.0048 0.0361 0.1313 0.00620.0122 0.0070 0.0051 0.0369 0.1313 0.00620.0122 0.0074 0.0054 0.0377 0.1313 0.00620.0122 0.0078 0.0058 0.0385 0.1313 0.00620.0122 0.0083 0.0061 0.0393 0.1313 0.0062

CD’TA CD’FUS CD’boom 1.05 CD’PAR DCL’ DCD’

0.0122 0.0087 0.0064 0.0401 0.1313 0.0062

Radianes

0.52359878

25 26 27 28 29

0.3511 0.0240 0.0423 0.0362 0.03010.4618 0.0240 0.0424 0.0362 0.03020.5724 0.0244 0.0428 0.0366 0.03060.6830 0.0249 0.0433 0.0371 0.03110.7936 0.0257 0.0441 0.0379 0.03190.9042 0.0273 0.0457 0.0395 0.03351.0149 0.0291 0.0475 0.0413 0.03531.1255 0.0312 0.0495 0.0434 0.03731.2361 0.0336 0.0520 0.0458 0.03981.3467 0.0368 0.0552 0.0490 0.04301.4573 0.0406 0.0590 0.0528 0.04681.5680 0.0449 0.0633 0.0571 0.05111.6786 0.0511 0.0694 0.0633 0.05721.7892 0.0560 0.0743 0.0682 0.06211.8998 0.0617 0.0801 0.0739 0.06791.6561 0.0583 0.0767 0.0705 0.06451.6483 0.0602 0.0786 0.0724 0.06641.6405 0.0627 0.0810 0.0749 0.06881.5931 0.0625 0.0809 0.0747 0.06871.5557 0.0636 0.0820 0.0758 0.06981.5183 0.0689 0.0873 0.0811 0.07511.4145 0.0717 0.0900 0.0839 0.07781.3621 0.0764 0.0948 0.0886 0.08261.3085 0.0812 0.0995 0.0934 0.0873

CLTC/A CDTS/AyTA CDTC/AyT CDTC/TA CDTC/A

1.2524 0.0859 0.1043 0.0981 0.0921

0.020 0.030 0.040 0.050 0.060 0.070 0.080 0.0900.0

0.2

0.4

0.6

0.8

1.0

1.2

1.4

1.6

1.8

2.0

Polar del Avión Limpio

CD

CL

global flyer

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