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reorganize file structure

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This commit is contained in:
Anthony Correa
2010-04-17 12:00:00 -05:00
parent 0da2092d89
commit 5bacd30bad
515 changed files with 2257 additions and 37 deletions
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42
ronald-plus/Ronaldplus Outputs/FDR001.txt Executable file
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FDR001
Outputs--------------------------------------------------
Wingspan: 140.000000, AR: 4.816577, Planform Area: 4069.280000, Wetted Area: 8408.002654
----------Takeoff--------------------------------
alfa: 6.125000, Cd0: 0.009957, CL: 0.480000, CD: 0.028410, D: 10790.513767, CM: -0.582875, L/D: 15.932485
----------Cruise---------------------------------
alfa: 0.951405, Cd0: 0.005179, CL: 0.190279, CD: 0.007481, D: 6817.381579, CM: -0.256939, L/D: 25.434985
D_Wing:993.322998, D_fuselage:3770.664809
----------Loiter---------------------------------
alfa: 3.952095, Cd0: 0.005682, CL: 0.358317, CD: 0.013937, D: 5208.157173, CM: -0.445982, L/D: 25.709670
----------Landing--------------------------------
alfa: 4.714286, Cd0: 0.009735, CL: 0.401000, CD: 0.021135, D: 9997.294077, CM: -0.494000, L/D: 18.973583
Inputs--------------------------------------------------
laminarflow_to 0.4 laminarflow_cruise 0.4
laminarflow_cruise 0.4 laminarflow_loiter 0.4
laminarflow_loiter 0.4 laminarflow_landing 0.4
laminarflow_landing 0.4 M_cruise 0.8
M_cruise 0.8 M_to 0.2
M_to 0.2 M_loiter 0.3
M_loiter 0.3 M_landing 0.2
M_landing 0.2 cLalpha 0.056
cLalpha 0.056 cL0 0.137
cL0 0.137 cMalpha-0.063
cMalpha-0.063 cM0-0.197
cM0-0.197 efficiency_to 0.8
efficiency_to 0.8 efficiency_cruise 0.8
efficiency_cruise 0.8 efficiency_loiter 0.8
efficiency_loiter 0.8 efficiency_landing 0.8
efficiency_landing 0.8 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise160000
weight_cruise160000 weight_to160000
weight_to160000 weight_loiter130000
weight_loiter130000 weight_landing130000
weight_landing130000 cd_correction 0
cd_correction 0 c_f 0.003

42
ronald-plus/Ronaldplus Outputs/FDR002.txt Executable file
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FDR002
Outputs--------------------------------------------------
Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8638.340407
----------Takeoff--------------------------------
alfa: 5.894737, Cd0: 0.009897, CL: 0.480000, CD: 0.024414, D: 9527.785965, CM: -0.600053, L/D: 18.540333
----------Cruise---------------------------------
alfa: 0.722547, Cd0: 0.005203, CL: 0.185185, CD: 0.006919, D: 6478.628035, CM: -0.258688, L/D: 26.764926
D_Wing:1155.571422, D_fuselage:3770.664809
----------Loiter---------------------------------
alfa: 3.591678, Cd0: 0.005699, CL: 0.348726, CD: 0.011851, D: 4550.243775, CM: -0.448051, L/D: 29.426995
----------Landing--------------------------------
alfa: 4.508772, Cd0: 0.009677, CL: 0.401000, CD: 0.018645, D: 9062.166794, CM: -0.508579, L/D: 21.507190
Inputs--------------------------------------------------
laminarflow_to 0.4 laminarflow_cruise 0.4
laminarflow_cruise 0.4 laminarflow_loiter 0.4
laminarflow_loiter 0.4 laminarflow_landing 0.4
laminarflow_landing 0.4 M_cruise 0.8
M_cruise 0.8 M_to 0.2
M_to 0.2 M_loiter 0.3
M_loiter 0.3 M_landing 0.2
M_landing 0.2 cLalpha 0.057
cLalpha 0.057 cL0 0.144
cL0 0.144 cMalpha-0.066
cMalpha-0.066 cM0-0.211
cM0-0.211 efficiency_to 0.8
efficiency_to 0.8 efficiency_cruise 0.8
efficiency_cruise 0.8 efficiency_loiter 0.8
efficiency_loiter 0.8 efficiency_landing 0.8
efficiency_landing 0.8 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise160000
weight_cruise160000 weight_to160000
weight_to160000 weight_loiter130000
weight_loiter130000 weight_landing130000
weight_landing130000 cd_correction 0
cd_correction 0 c_f 0.003

42
ronald-plus/Ronaldplus Outputs/FDR003.txt Executable file
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FDR003
Outputs--------------------------------------------------
Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8646.272379
----------Takeoff--------------------------------
alfa: 5.894737, Cd0: 0.009903, CL: 0.480000, CD: 0.024420, D: 9530.278297, CM: -0.600053, L/D: 18.535485
----------Cruise---------------------------------
alfa: 0.722547, Cd0: 0.005208, CL: 0.185185, CD: 0.006924, D: 6483.328324, CM: -0.258688, L/D: 26.745522
D_Wing:1159.593905, D_fuselage:3771.626725
----------Loiter---------------------------------
alfa: 3.591678, Cd0: 0.005704, CL: 0.348726, CD: 0.011856, D: 4552.237898, CM: -0.448051, L/D: 29.414104
----------Landing--------------------------------
alfa: 4.508772, Cd0: 0.009684, CL: 0.401000, CD: 0.018651, D: 9065.211714, CM: -0.508579, L/D: 21.499965
Inputs--------------------------------------------------
laminarflow_to 0.4 laminarflow_cruise 0.4
laminarflow_cruise 0.4 laminarflow_loiter 0.4
laminarflow_loiter 0.4 laminarflow_landing 0.4
laminarflow_landing 0.4 M_cruise 0.8
M_cruise 0.8 M_to 0.2
M_to 0.2 M_loiter 0.3
M_loiter 0.3 M_landing 0.2
M_landing 0.2 cLalpha 0.057
cLalpha 0.057 cL0 0.144
cL0 0.144 cMalpha-0.066
cMalpha-0.066 cM0-0.211
cM0-0.211 efficiency_to 0.8
efficiency_to 0.8 efficiency_cruise 0.8
efficiency_cruise 0.8 efficiency_loiter 0.8
efficiency_loiter 0.8 efficiency_landing 0.8
efficiency_landing 0.8 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise160000
weight_cruise160000 weight_to160000
weight_to160000 weight_loiter130000
weight_loiter130000 weight_landing130000
weight_landing130000 cd_correction 0
cd_correction 0 c_f 0.003

42
ronald-plus/Ronaldplus Outputs/FDR004.txt Executable file
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FDR004
Outputs--------------------------------------------------
Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8638.340407
----------Takeoff--------------------------------
alfa: 6.035714, Cd0: 0.009897, CL: 0.480000, CD: 0.024414, D: 9527.785965, CM: -0.601321, L/D: 18.540333
----------Cruise---------------------------------
alfa: 0.771164, Cd0: 0.005203, CL: 0.185185, CD: 0.006919, D: 6478.628035, CM: -0.259126, L/D: 26.764926
D_Wing:1155.571422, D_fuselage:3770.664809
----------Loiter---------------------------------
alfa: 3.691530, Cd0: 0.005699, CL: 0.348726, CD: 0.011851, D: 4550.243775, CM: -0.448949, L/D: 29.426995
----------Landing--------------------------------
alfa: 4.625000, Cd0: 0.009677, CL: 0.401000, CD: 0.018645, D: 9062.166794, CM: -0.509625, L/D: 21.507190
Inputs--------------------------------------------------
laminarflow_to 0.4 laminarflow_cruise 0.4
laminarflow_cruise 0.4 laminarflow_loiter 0.4
laminarflow_loiter 0.4 laminarflow_landing 0.4
laminarflow_landing 0.4 M_cruise 0.8
M_cruise 0.8 M_to 0.2
M_to 0.2 M_loiter 0.3
M_loiter 0.3 M_landing 0.2
M_landing 0.2 cLalpha 0.056
cLalpha 0.056 cL0 0.142
cL0 0.142 cMalpha-0.065
cMalpha-0.065 cM0-0.209
cM0-0.209 efficiency_to 0.8
efficiency_to 0.8 efficiency_cruise 0.8
efficiency_cruise 0.8 efficiency_loiter 0.8
efficiency_loiter 0.8 efficiency_landing 0.8
efficiency_landing 0.8 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise160000
weight_cruise160000 weight_to160000
weight_to160000 weight_loiter130000
weight_loiter130000 weight_landing130000
weight_landing130000 cd_correction 0
cd_correction 0 c_f 0.003

42
ronald-plus/Ronaldplus Outputs/FDR005.txt Executable file
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FDR005
Outputs--------------------------------------------------
Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8638.340407
----------Takeoff--------------------------------
alfa: 6.035714, Cd0: 0.009897, CL: 0.480000, CD: 0.024414, D: 9527.785965, CM: -0.570214, L/D: 18.540333
----------Cruise---------------------------------
alfa: 0.771164, Cd0: 0.005203, CL: 0.185185, CD: 0.006919, D: 6478.628035, CM: -0.243812, L/D: 26.764926
D_Wing:1155.571422, D_fuselage:3770.664809
----------Loiter---------------------------------
alfa: 3.691530, Cd0: 0.005699, CL: 0.348726, CD: 0.011851, D: 4550.243775, CM: -0.424875, L/D: 29.426995
----------Landing--------------------------------
alfa: 4.625000, Cd0: 0.009677, CL: 0.401000, CD: 0.018645, D: 9062.166794, CM: -0.482750, L/D: 21.507190
Inputs--------------------------------------------------
laminarflow_to 0.4 laminarflow_cruise 0.4
laminarflow_cruise 0.4 laminarflow_loiter 0.4
laminarflow_loiter 0.4 laminarflow_landing 0.4
laminarflow_landing 0.4 M_cruise 0.8
M_cruise 0.8 M_to 0.2
M_to 0.2 M_loiter 0.3
M_loiter 0.3 M_landing 0.2
M_landing 0.2 cLalpha 0.056
cLalpha 0.056 cL0 0.142
cL0 0.142 cMalpha-0.062
cMalpha-0.062 cM0-0.196
cM0-0.196 efficiency_to 0.8
efficiency_to 0.8 efficiency_cruise 0.8
efficiency_cruise 0.8 efficiency_loiter 0.8
efficiency_loiter 0.8 efficiency_landing 0.8
efficiency_landing 0.8 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise160000
weight_cruise160000 weight_to160000
weight_to160000 weight_loiter130000
weight_loiter130000 weight_landing130000
weight_landing130000 cd_correction 0
cd_correction 0 c_f 0.003

42
ronald-plus/Ronaldplus Outputs/FDR006.txt Executable file
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FDR006
Outputs--------------------------------------------------
Wingspan: 160.000000, AR: 5.372164, Planform Area: 4765.305000, Wetted Area: 9841.204819
----------Takeoff--------------------------------
alfa: 5.789474, Cd0: 0.009366, CL: 0.480000, CD: 0.025911, D: 11524.531436, CM: -0.623684, L/D: 17.469300
----------Cruise---------------------------------
alfa: 0.219059, Cd0: 0.005093, CL: 0.162486, CD: 0.006598, D: 7041.632125, CM: -0.244896, L/D: 24.624973
D_Wing:1611.158629, D_fuselage:3912.112692
----------Loiter---------------------------------
alfa: 2.736511, Cd0: 0.005543, CL: 0.305981, CD: 0.010941, D: 4787.724124, CM: -0.416083, L/D: 27.967359
----------Landing--------------------------------
alfa: 4.403509, Cd0: 0.009162, CL: 0.401000, CD: 0.019382, D: 10736.626548, CM: -0.529439, L/D: 20.688886
Inputs--------------------------------------------------
laminarflow_to 0.4 laminarflow_cruise 0.4
laminarflow_cruise 0.4 laminarflow_loiter 0.4
laminarflow_loiter 0.4 laminarflow_landing 0.4
laminarflow_landing 0.4 M_cruise 0.8
M_cruise 0.8 M_to 0.2
M_to 0.2 M_loiter 0.3
M_loiter 0.3 M_landing 0.2
M_landing 0.2 cLalpha 0.057
cLalpha 0.057 cL0 0.15
cL0 0.15 cMalpha-0.068
cMalpha-0.068 cM0 -0.23
cM0 -0.23 efficiency_to 0.8
efficiency_to 0.8 efficiency_cruise 0.8
efficiency_cruise 0.8 efficiency_loiter 0.8
efficiency_loiter 0.8 efficiency_landing 0.8
efficiency_landing 0.8 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise160000
weight_cruise160000 weight_to160000
weight_to160000 weight_loiter130000
weight_loiter130000 weight_landing130000
weight_landing130000 cd_correction 0
cd_correction 0 c_f 0.003

42
ronald-plus/Ronaldplus Outputs/FDR007.txt Executable file
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FDR007
Outputs--------------------------------------------------
Wingspan: 160.000000, AR: 5.961418, Planform Area: 4294.280000, Wetted Area: 8871.044819
----------Takeoff--------------------------------
alfa: 5.689655, Cd0: 0.009789, CL: 0.480000, CD: 0.024698, D: 9899.382825, CM: -0.646655, L/D: 18.326955
----------Cruise---------------------------------
alfa: 0.522568, Cd0: 0.005184, CL: 0.180309, CD: 0.006854, D: 6591.510141, CM: -0.274625, L/D: 26.306567
D_Wing:1275.276731, D_fuselage:3770.664809
----------Loiter---------------------------------
alfa: 3.267986, Cd0: 0.005670, CL: 0.339543, CD: 0.011659, D: 4597.941876, CM: -0.472295, L/D: 29.121725
----------Landing--------------------------------
alfa: 4.327586, Cd0: 0.009572, CL: 0.401000, CD: 0.018782, D: 9375.811144, CM: -0.548586, L/D: 21.349896
Inputs--------------------------------------------------
laminarflow_to 0.4 laminarflow_cruise 0.4
laminarflow_cruise 0.4 laminarflow_loiter 0.4
laminarflow_loiter 0.4 laminarflow_landing 0.4
laminarflow_landing 0.4 M_cruise 0.8
M_cruise 0.8 M_to 0.2
M_to 0.2 M_loiter 0.3
M_loiter 0.3 M_landing 0.2
M_landing 0.2 cLalpha 0.058
cLalpha 0.058 cL0 0.15
cL0 0.15 cMalpha-0.072
cMalpha-0.072 cM0-0.237
cM0-0.237 efficiency_to 0.8
efficiency_to 0.8 efficiency_cruise 0.8
efficiency_cruise 0.8 efficiency_loiter 0.8
efficiency_loiter 0.8 efficiency_landing 0.8
efficiency_landing 0.8 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise160000
weight_cruise160000 weight_to160000
weight_to160000 weight_loiter130000
weight_loiter130000 weight_landing130000
weight_landing130000 cd_correction 0
cd_correction 0 c_f 0.003

42
ronald-plus/Ronaldplus Outputs/FDR008.txt Executable file
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FDR008
Outputs--------------------------------------------------
Wingspan: 160.000000, AR: 5.961418, Planform Area: 4294.280000, Wetted Area: 8680.251229
----------Takeoff--------------------------------
alfa: 5.689655, Cd0: 0.009659, CL: 0.480000, CD: 0.024568, D: 9847.386405, CM: -0.646655, L/D: 18.423725
----------Cruise---------------------------------
alfa: 0.522568, Cd0: 0.005081, CL: 0.180309, CD: 0.006751, D: 6492.653630, CM: -0.274625, L/D: 26.707108
D_Wing:1275.276731, D_fuselage:3665.832878
----------Loiter---------------------------------
alfa: 3.267986, Cd0: 0.005564, CL: 0.339543, CD: 0.011554, D: 4556.282608, CM: -0.472295, L/D: 29.387993
----------Landing--------------------------------
alfa: 4.327586, Cd0: 0.009445, CL: 0.401000, CD: 0.018655, D: 9312.077689, CM: -0.548586, L/D: 21.496018
Inputs--------------------------------------------------
laminarflow_to 0.4 laminarflow_cruise 0.4
laminarflow_cruise 0.4 laminarflow_loiter 0.4
laminarflow_loiter 0.4 laminarflow_landing 0.4
laminarflow_landing 0.4 M_cruise 0.8
M_cruise 0.8 M_to 0.2
M_to 0.2 M_loiter 0.3
M_loiter 0.3 M_landing 0.2
M_landing 0.2 cLalpha 0.058
cLalpha 0.058 cL0 0.15
cL0 0.15 cMalpha-0.072
cMalpha-0.072 cM0-0.237
cM0-0.237 efficiency_to 0.8
efficiency_to 0.8 efficiency_cruise 0.8
efficiency_cruise 0.8 efficiency_loiter 0.8
efficiency_loiter 0.8 efficiency_landing 0.8
efficiency_landing 0.8 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise160000
weight_cruise160000 weight_to160000
weight_to160000 weight_loiter130000
weight_loiter130000 weight_landing130000
weight_landing130000 cd_correction 0
cd_correction 0 c_f 0.003

42
ronald-plus/Ronaldplus Outputs/FDR009.txt Executable file
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FDR009
Outputs--------------------------------------------------
Wingspan: 160.000000, AR: 5.478266, Planform Area: 4673.011400, Wetted Area: 9672.757115
----------Takeoff--------------------------------
alfa: 6.490566, Cd0: 0.009421, CL: 0.480000, CD: 0.025645, D: 11185.579599, CM: -0.603415, L/D: 17.650069
----------Cruise---------------------------------
alfa: 0.560293, Cd0: 0.005099, CL: 0.165696, CD: 0.006634, D: 6942.134663, CM: -0.235738, L/D: 24.977908
D_Wing:1264.133474, D_fuselage:4153.626223
----------Loiter---------------------------------
alfa: 3.321215, Cd0: 0.005554, CL: 0.312024, CD: 0.011058, D: 4745.180987, CM: -0.406915, L/D: 28.218102
----------Landing--------------------------------
alfa: 5.000000, Cd0: 0.009216, CL: 0.401000, CD: 0.019238, D: 10450.457803, CM: -0.511000, L/D: 20.843746
Inputs--------------------------------------------------
laminarflow_to 0.4 laminarflow_cruise 0.4
laminarflow_cruise 0.4 laminarflow_loiter 0.4
laminarflow_loiter 0.4 laminarflow_landing 0.4
laminarflow_landing 0.4 M_cruise 0.8
M_cruise 0.8 M_to 0.2
M_to 0.2 M_loiter 0.3
M_loiter 0.3 M_landing 0.2
M_landing 0.2 cLalpha 0.053
cLalpha 0.053 cL0 0.136
cL0 0.136 cMalpha-0.062
cMalpha-0.062 cM0-0.201
cM0-0.201 efficiency_to 0.8
efficiency_to 0.8 efficiency_cruise 0.8
efficiency_cruise 0.8 efficiency_loiter 0.8
efficiency_loiter 0.8 efficiency_landing 0.8
efficiency_landing 0.8 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise160000
weight_cruise160000 weight_to160000
weight_to160000 weight_loiter130000
weight_loiter130000 weight_landing130000
weight_landing130000 cd_correction 0
cd_correction 0 c_f 0.003

42
ronald-plus/Ronaldplus Outputs/FDR010.txt Executable file
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FDR010
Outputs--------------------------------------------------
Wingspan: 160.020000, AR: 4.351054, Planform Area: 5885.103300, Wetted Area: 12255.124748
----------Takeoff--------------------------------
alfa: 5.961538, Cd0: 0.008588, CL: 0.480000, CD: 0.029016, D: 15938.254235, CM: -0.569846, L/D: 15.599885
----------Cruise---------------------------------
alfa: -0.739058, Cd0: 0.004911, CL: 0.131569, CD: 0.006130, D: 8078.320210, CM: -0.194613, L/D: 21.464858
D_Wing:1785.236663, D_fuselage:4837.811550
----------Loiter---------------------------------
alfa: 1.495386, Cd0: 0.005295, CL: 0.247760, CD: 0.009664, D: 5222.865680, CM: -0.319742, L/D: 25.637267
----------Landing--------------------------------
alfa: 4.442308, Cd0: 0.008409, CL: 0.401000, CD: 0.021028, D: 14385.111589, CM: -0.484769, L/D: 19.070194
Inputs--------------------------------------------------
laminarflow_to 0.4 laminarflow_cruise 0.4
laminarflow_cruise 0.4 laminarflow_loiter 0.4
laminarflow_loiter 0.4 laminarflow_landing 0.4
laminarflow_landing 0.4 M_cruise 0.8
M_cruise 0.8 M_to 0.2
M_to 0.2 M_loiter 0.3
M_loiter 0.3 M_landing 0.2
M_landing 0.2 cLalpha 0.052
cLalpha 0.052 cL0 0.17
cL0 0.17 cMalpha-0.056
cMalpha-0.056 cM0-0.236
cM0-0.236 efficiency_to 0.8
efficiency_to 0.8 efficiency_cruise 0.8
efficiency_cruise 0.8 efficiency_loiter 0.8
efficiency_loiter 0.8 efficiency_landing 0.8
efficiency_landing 0.8 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise160000
weight_cruise160000 weight_to160000
weight_to160000 weight_loiter130000
weight_loiter130000 weight_landing130000
weight_landing130000 cd_correction 0
cd_correction 0 c_f 0.003

47
ronald-plus/Ronaldplus Outputs/FDR020.txt Executable file
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FDR020
Outputs--------------------------------------------------
Wingspan: 160.000000, AR: 4.929075, Planform Area: 5193.672700, Wetted Area: 10834.744604
----------Takeoff--------------------------------
alfa: 10.689189, Cd0: 0.009040, CL: 0.480000, CD: 0.027072, D: 13123.396794, CM: -0.033693, L/D: 16.720004
----------Cruise---------------------------------
alfa: 1.745533, Cd0: 0.005030, CL: 0.149085, CD: 0.006411, D: 7456.834503, CM: -0.036376, L/D: 23.253835
D_Wing:1310.651767, D_fuselage:4652.919001
----------Loiter---------------------------------
alfa: 5.303897, Cd0: 0.005450, CL: 0.280744, CD: 0.010403, D: 4961.487808, CM: -0.035309, L/D: 26.987872
----------Landing--------------------------------
alfa: 8.554054, Cd0: 0.008847, CL: 0.401000, CD: 0.019986, D: 12066.388294, CM: -0.034334, L/D: 20.063723
Inputs--------------------------------------------------
laminarflow_to 0.35 laminarflow_cruise 0.5
laminarflow_cruise 0.5 laminarflow_loiter 0.5
laminarflow_loiter 0.5 laminarflow_landing 0.35
laminarflow_landing 0.35 M_cruise 0.8
M_cruise 0.8 M_to 0.2509
M_to 0.2509 M_loiter 0.3
M_loiter 0.3 M_landing 0.28
M_landing 0.28 cLalpha 0.037
cLalpha 0.037 cL0 0.0845
cL0 0.0845 cMalpha 0.0003
cMalpha 0.0003 cM0-0.0369
cM0-0.0369 efficiency_to 0.7781
efficiency_to 0.7781 efficiency_cruise 0.98
efficiency_cruise 0.98 efficiency_loiter 0.9692
efficiency_loiter 0.9692 efficiency_landing 0.8791
efficiency_landing 0.8791 alt_cruise 35000
alt_cruise 35000 alt_to 0
alt_to 0 alt_loiter 10000
alt_loiter 10000 alt_landing 0
alt_landing 0 weight_cruise 173400
weight_cruise 173400 weight_to 173400
weight_to 173400 weight_loiter 133900
weight_loiter 133900 weight_landing 133900
weight_landing 133900 cd_correction 0
cd_correction 0 c_f 0.003
c_f 0.003 D_engine 240.5
D_engine 240.5 fuse_width 57.96
fuse_width 57.96 Dragredux_BLI 5.7
Dragredux_BLI 5.7 sfront_landinggear 33.7
sfront_landinggear 33.7 cd_landinggear 0.4

539
ronald-plus/Ronaldplus.m Executable file
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%Ronald
%all alfas in DEGREES!
%by ascorrea, with help from Jacob Huffman
%"filler" variable just makes it easier to switch between Ronald and Grimace
function Ronald(paramfile, pranformfile, filler)
testrange={'20'};
for testnumber=1:length(testrange)
prefix='FDR0';
name=strcat(prefix, testrange{testnumber});
paramfile=strcat(name, '.param');
pranformfile=strcat(name, '.plan');
%DIRECTORY LOCATIONS--------------------------------------------------------------]
rootLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Matlab Code';
airfoilLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Airfoils';
pranformLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planforms';
pranformConstraintLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planform Constraints';
paramLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Parameter Files';
outputsLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Ronaldplus Outputs';
%-----------------------------------------------------------------------]
n=50;
cd(paramLOCATION);
[variablenames, variablevalues]=textread(paramfile, '%s %f');
inputvalues=num2str(variablevalues);
input=strcat(variablenames, inputvalues);
[constantnames, constantvalues]=textread('constants.param', '%s %f');
cd(pranformLOCATION)
[spans, chords, offsets, airfoil]=textread(pranformfile, '%f %f %f %s');
cd(airfoilLOCATION)
[sref swet]=WhettedArea(spans, chords, offsets, airfoil, n);
for k = 1:length(variablenames)
eval([variablenames{k} '= variablevalues(k);']);
end
for k = 1:length(constantnames)
eval([constantnames{k} '= constantvalues(k);']);
end
Dragredux_BLI=(1-Dragredux_BLI/100);
wingspan=2*spans(end);
AR=wingspan^2/sref;
% wakeplot=findwake(airfoil, chords, spans, offsets, n, alt_cruise, M_cruise, laminarflow_cruise, fuse_width);
%TAKEOFF------------------------------------------------------------------]
% cd0_to=findcd0(c_f, M_to, sref, swet);
[cd0_to D_wing_to D_fuse_to]=findcd0(spans, chords, offsets, airfoil, n, laminarflow_to, alt_to, M_to, sref, c_f, D_engine, cd_landinggear, sfront_landinggear, fuse_width);
% finddragpolar(cd0_to, cLalpha_to, cL0, efficiency_to, AR, cd_correction, 'Takeoff')
% cLreq_to=findcLrequired(alt_to, sref, M_to, weight_to);
cLreq_to=.48;
alphareq_to=findalpharequired(cLalpha, cL0, cLreq_to);
cD_to=findcD(AR, efficiency_to, cd0_to, cLreq_to, cd_correction);
eloverdee_to=cLreq_to/cD_to;
cM_to=cMalpha*alphareq_to+cM0;
q_to=finddynpress(alt_to, M_to);
cD_to=cD_to*Dragredux_BLI;
cd0_to=cd0_to*Dragredux_BLI;
D_to=cD_to*q_to*sref;
%CRUISE------------------------------------------------------------------]
[cd0_cruise D_wing_cruise D_fuse_cruise]=findcd0(spans, chords, offsets, airfoil, n, laminarflow_cruise, alt_cruise, M_cruise, sref, c_f, D_engine, 0, 0, fuse_width);
% finddragpolar(cd0_cruise, cLalpha, cL0, efficiency_cruise, AR, cd_correction, 'Cruise')
cLreq_cruise=findcLrequired(alt_cruise, sref, M_cruise, weight_cruise);
alphareq_cruise=findalpharequired(cLalpha, cL0, cLreq_cruise);
cD_cruise=findcD(AR, efficiency_cruise, cd0_cruise, cLreq_cruise, cd_correction);
cM_cruise=cMalpha*alphareq_cruise+cM0;
q_cruise=finddynpress(alt_cruise, M_cruise);
cD_cruise=cD_cruise*Dragredux_BLI;
cd0_cruise=cd0_cruise*Dragredux_BLI;
D_cruise=cD_cruise*q_cruise*sref;
eloverdee_cruise=cLreq_cruise/cD_cruise;
%LOITER------------------------------------------------------------------]
[cd0_loiter D_wing_loiter D_fuse_loiter]=findcd0(spans, chords, offsets, airfoil, n, laminarflow_loiter, alt_loiter, M_loiter, sref, c_f, D_engine, 0, 0, fuse_width);
% finddragpolar(cd0_loiter, cLalpha_loiter, cL0, efficiency_loiter, AR, cd_correction, 'Loiter')
cLreq_loiter=findcLrequired(alt_loiter, sref, M_loiter, weight_loiter);
alphareq_loiter=findalpharequired(cLalpha, cL0, cLreq_loiter);
cD_loiter=findcD(AR, efficiency_loiter, cd0_loiter, cLreq_loiter, cd_correction);
cM_loiter=cMalpha*alphareq_loiter+cM0;
q_loiter=finddynpress(alt_loiter, M_loiter);
cD_loiter=cD_loiter*Dragredux_BLI;
cd0_loiter=cd0_loiter*Dragredux_BLI;
D_loiter=cD_loiter*q_loiter*sref;
eloverdee_loiter=cLreq_loiter/cD_loiter;
%LANDING------------------------------------------------------------------]
[cd0_landing D_wing_landing D_fuse_landing]=findcd0(spans, chords, offsets, airfoil, n, laminarflow_landing, alt_landing, M_landing, sref, c_f, D_engine, cd_landinggear, sfront_landinggear, fuse_width);
% finddragpolar(cd0_landing, cLalpha_landing, cL0, efficiency_landing, AR, cd_correction, 'Landing')
% cLreq_landing=findcLrequired(alt_landing, sref, M_landing, weight_landing);
cLreq_landing=.401;
alphareq_landing=findalpharequired(cLalpha, cL0, cLreq_landing);
cD_landing=findcD(AR, efficiency_landing, cd0_landing, cLreq_landing, cd_correction);
cM_landing=cMalpha*alphareq_landing+cM0;
q_landing=finddynpress(alt_landing, M_landing);
cD_landing=cD_landing*Dragredux_BLI;
cd0_landing=cd0_landing*Dragredux_BLI;
D_landing=cD_landing*q_landing*sref;
eloverdee_landing=cLreq_landing/cD_landing;
cd(outputsLOCATION)
filenameplan=regexprep(pranformfile, '.plan', '_planform.tiff');
filenameoutput=regexprep(pranformfile, '.plan', '.txt');
plottitle=regexprep(pranformfile, '.plan', '');
fid = fopen(filenameoutput, 'w');
plottitle
fprintf(fid, plottitle);
fprintf(fid,'\nOutputs--------------------------------------------------\n');
fprintf(fid, 'Wingspan: %f, AR: %f, Planform Area: %f, Wetted Area: %f \n', wingspan, AR, sref, swet);
fprintf(fid, '\n----------Takeoff--------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_to, cd0_to, cLreq_to, cD_to, D_to, cM_to, eloverdee_to);
fprintf(fid, '\n----------Cruise---------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n D_Wing:%f, D_fuselage:%f', alphareq_cruise, cd0_cruise, cLreq_cruise, cD_cruise, D_cruise, cM_cruise, eloverdee_cruise, D_wing_cruise, D_fuse_cruise);
fprintf(fid, '\n----------Loiter---------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_loiter, cd0_loiter, cLreq_loiter, cD_loiter, D_loiter, cM_loiter, eloverdee_loiter);
fprintf(fid, '\n----------Landing--------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_landing, cd0_landing, cLreq_landing, cD_landing, D_landing, cM_landing, eloverdee_landing);
fprintf(fid, '\nInputs--------------------------------------------------\n');
for k=1:length(input)-1
fprintf(fid, '%s %s \n',input{k}, input{k+1});
end
fclose(fid);
cd(rootLOCATION)
end
end
% function cd0=findcd0(c_f, M, sref, swet)
% if M>.7
% c_f=c_f*(1-.09*M^2);
% end
% cd0=c_f*(swet/sref);
% end
function [cd0 D_wing D_fuse]=findcd0(spans, chords, offsets, airfoil, n, laminarflow, alt, v_mach, sref, c_f, D_engine, cd_lg, Sfront_lg, width)
wingSpan = 1;
% n = 50;
width=width/2;
[q v_fps dynvisc]=findconstants(alt, v_mach);
drag=0;
drag_fuse=0;
drag_wing=0;
Chords = findChords(n, chords, spans);
for i = 1:(size(chords)-1)
for j = 1:n
dist = wingSpan*(spans(i+1)-spans(i))./n;
chordloc=linspace(0, Chords(i,j));
delta_x = Chords(i,j)/100;
if spans(i)>width
for k = 1:100
x(k)= k * Chords(i,j)/100;
Re_x(k)= v_fps * x(k)/dynvisc;
if (k <= 100*laminarflow )
cf_x(k) = 0.664 /(sqrt(Re_x(k)));
else % Turbulent
cf_x(k) = 0.455 /(log(0.06 * Re_x(k))^2);
end
xcf_x(k)=x(k)*cf_x(k);
end
t = trapz(cf_x);
Cf = 2 * delta_x * t /Chords(i,j);
drag_section = q*Cf*findPerim(airfoil{i}, Chords(i,j), wingSpan).*dist;
drag_wing=drag_wing+drag_section;
else
for k = 1:100
x(k)= k * Chords(i,j)/100;
Re_x(k)= v_fps * x(k)/dynvisc;
if (k <= 100*laminarflow -10)
cf_x(k) = 0.664 /(sqrt(Re_x(k)));
else % Turbulent
cf_x(k) = 0.455 /(log(0.06 * Re_x(k))^2);
end
xcf_x(k)=x(k)*cf_x(k);
end
t = trapz(cf_x);
Cf = 2 * delta_x * t /Chords(i,j);
drag_section = q*Cf*findPerim(airfoil{i}, Chords(i,j), wingSpan).*dist;
drag_fuse=drag_fuse+drag_section;
end
t = trapz(cf_x);
Cf = 2 * delta_x * t /Chords(i,j);
drag_section = q*Cf*findPerim(airfoil{i}, Chords(i,j), wingSpan).*dist;
drag=drag+drag_section;
end
end
if v_mach>.7
c_f=c_f*(1-.09*v_mach)^2;
end
% cd0engine=c_f*(s_engine/sref);
D_lg=Sfront_lg*q*cd_lg;
D_wing=drag_wing*2;
D_fuse=drag_fuse*2;
drag_tot=D_wing+D_engine+D_lg+D_fuse;
cd0=drag_tot/(q*sref);
cD_lg=D_lg/(q*sref);
cD_engine=D_engine/(q*sref);
cD_wing=D_wing/(q*sref);
cD_fuse=D_fuse/(q*sref);
end
function finddragpolar(cd0, cl_alfa, cL0, e, ar, cd_correction, filename)
alphadeg=[-12:10];
% alpha=(pi/180)*(alphadeg);
alpha=alphadeg;
cL_alfa=cl_alfa*(ar/(ar+(2*(ar+4)/(ar+2))));
for i=1:length(alpha)
C_L(i)=cL_alfa*(alpha(i))+cL0;
cd_i(i)=C_L(i)^2/(pi*ar*e);
C_d(i)=cd0+cd_i(i)+cd_correction;
end
graphname='Drag Polar';
hold on
grid on
axisX0=linspace(0,max(cd));
axisY0=zeros(1,length(axisX0));
plot(axisX0, axisY0,'k--');
plot(C_d, C_L, 'k', 'LineWidth', 2);
plot(C_d, C_L, 'k.');
title(graphname);
xlabel('C_d', 'FontSize', 16);
ylabel('C_L', 'FontSize', 16);
axis([0, .02, -.3, .4]);
set(gca, 'FontSize',16)
% for i=1:length(alphadeg)
% alphalabel=num2str(alphadeg(i));
% label=[' \alpha =' alphalabel];
% text(C_d(i), C_L(i), label)
% end
print ('-dtiff', filename)
grid off
close(1)
end
function q=finddynpress(alt, v_mach)
if alt < 36152
temp=59-.00356*alt;
press=2116*((temp+459.7)/518.6)^5.256;
elseif alt < 82345
temp=-70;
press=473.1*exp(1.73-.000048*alt);
else
print('Program Not Valid for given altitude')
end
%slpcuft: clugs ber cubic foot
density_slpcuft=press/(1718*(temp+459.7));
v_fps=v_mach*sqrt(1.4*1718*(temp+459.7));
q=.5*density_slpcuft*v_fps^2;
end
function [q v_fps dynvisc]=findconstants(alt, v_mach)
if alt < 36152
temp=59-.00356*alt;
press=2116*((temp+459.7)/518.6)^5.256;
elseif alt < 82345
temp=-70;
press=473.1*exp(1.73-.000048*alt);
else
print('Program Not Valid for given altitude')
end
%slpcuft: clugs ber cubic foot
density_slpcuft=press/(1718*(temp+459.7));
v_fps=v_mach*sqrt(1.4*1718*(temp+459.7));
q=finddynpress(alt, v_mach);
S = 110.4;
beta = 1.458e-6;
temp_k=[(temp-32) / (1.8)] + 273 ;
viscosity_pascalseconds = (beta*temp_k^(1.5))/(temp_k+S);
%kgpmcu:kilograms per meter cubed
%msqpse:meters squared per second
%sqftpsec:square feet per second
density_kgpmcu=density_slpcuft*515.4;
dynamic_viscosity_msqpsec=viscosity_pascalseconds/density_kgpmcu;
dynamic_viscosity_sqftpsec=dynamic_viscosity_msqpsec*10.76;
dynvisc=dynamic_viscosity_sqftpsec;
density=density_slpcuft;
end
function cLreq=findcLrequired(alt, s, v_mach, lift)
q=finddynpress(alt, v_mach);
cLreq=lift/(q*s);
end
function alpha=findalpharequired(cLalpha, cL0, cLrequired)
alpha=(cLrequired-cL0)/cLalpha;
end
function cD=findcD(ar, e, cd0, C_L, cd_correction)
% e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1;
cd_i=C_L^2/(pi*ar*e);
cd_i=C_L^2/(pi*ar*e);
cD=cd0+cd_i+cd_correction;
end
function [pranformArea WetArea]=WhettedArea(spans, chords, offsets, airfoil, n)
% fileName = 'AirData.mat';
wingSpan = 1;
% n = 50;
engineArea=0;
Area = 0;
pranformArea = 0;
Chords = findChords(n, chords, spans);
for i = 1:(size(chords)-1)
for j = 1:n
Chords(i,j);
dist = wingSpan*(spans(i+1)-spans(i))./n;
Area = Area+findPerim( airfoil{i}, Chords(i,j), wingSpan).*dist;
end
end
for i = 1:(size(chords)-1)
for j = 1:n
dist = wingSpan*(spans(i+1)-spans(i))./n;
pranformArea = pranformArea+Chords(i,j).*dist;
% fprintf('Chord: %f pranformArea: %f \n', Chords(i,j), pranformArea)
end
end
Area = Area *2+engineArea;
WetArea = Area;
pranformArea = pranformArea*2;
end
function Chords = findChords( n, Chord, X )
for( i = 1:(length(Chord)-1) )
Xtemp = linspace(X(i),X(i+1),n);
Chords(i,:) = (Chord(i+1)-Chord(i))./(X(i+1)-X(i)).*(Xtemp-X(i))+Chord(i);
end
end
function peri = findPerim(airFile, chord, span)
peri = 0;
Airfoil = load(airFile);
Airfoil = Airfoil*chord*span;
for i = 1:(size(Airfoil,1)-1)
peri = peri + sqrt((Airfoil(i+1,1)-Airfoil(i,1))^2+(Airfoil(i+1,2)-Airfoil(i,2))^2);
end
end
function [plotLE plotTE]=plotpranform(spans, chords, offsets, n)
Chords = findChords(n, chords, spans);
%plot planform
for i = 1:(size(chords)-1)
dist=0;
for j = 1:n
Chords(i,j);
dist = (spans(i+1)-spans(i))./n;
if i==1
xplotLE(i,j+1)=spans(1)+dist*(j);
else
xplotLE(i,1)=xplotLE(i-1,end);
xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j);
end
fitX(1)=spans(i);
fitX(2)=spans(i+1);
fitY(1)=offsets(i);
fitY(2)=offsets(i+1);
a = polyfit(fitX, fitY,1);
yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2);
end
end
plotLE=zeros(1,2);
plotTE=zeros(1,2);
for i=1:(size(chords)-1)
for j=1:n
plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)];
plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))];
end
end
plotTE(1,:)=[];
plotLE(1,:)=[];
end
function [wakeplot]=findwake(airfoil, chords, spans, offsets, n, alt, v_mach, laminarflow, width)
[q v_fps dynvisc]=findconstants(alt, v_mach);
Chords = findChords(n, chords, spans);
wakeplot=zeros(100,1);
wakeplotX=zeros(100,1);
wakeplotY=zeros(100,1);
width=width/2;
% for i = 1:(size(chords)-1)
for i=1:1:(size(chords)-1)
for j = 1:n
% wakecoord(j,:)=linspace(0, Chords(i,j), n);
dist = (spans(i+1)-spans(i))./n;
y(j)=spans(i)+j*dist;
if i==1
xplotLE(i,j+1)=spans(1)+dist*(j);
else
xplotLE(i,1)=xplotLE(i-1,end);
xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j);
end
fitX(1)=spans(i);
fitX(2)=spans(i+1);
fitY(1)=offsets(i);
fitY(2)=offsets(i+1);
a = polyfit(fitX, fitY,1);
yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2);
if spans(i)>width
lam=laminarflow;
else
lam=laminarflow-.15;
end
x=linspace(0, Chords(i,j));
for k = 1:length(x)
if (k <= 100*lam)
delta_x=( 5.2 * x(k) )*(v_fps*x(k)/dynvisc)^-0.5;
wake(k,j)= delta_x;
else %if turbulent
x_tr=x(100*lam);
Re_xtr = v_fps * x_tr / dynvisc;
delta_xtr=(5.2*x_tr)*(v_fps*x(k)/dynvisc)^-(0.5);
delta_l = ((delta_xtr*((v_fps)^0.2))/(0.37*((dynvisc)^0.2)))^(1/0.8);
lt = x(k) - x_tr + delta_l;
Re_lt = v_fps * lt / dynvisc;
delta = 0.37 * lt /(Re_lt)^0.2;
wake(k,j) = delta;
end
wakeX(k,j)=x(k)+yplotLE(i,j);
wakeY(k,j)=y(j);
end
for k = 1:100
wakeX(k,j)=x(k)+yplotLE(i,j);
wakeY(k,j)=y(j);
end
wakeplot=[wakeplot, wake];
wakeplotX=[wakeplotX, wakeX];
wakeplotY=[wakeplotY, wakeY];
end
end
wakeplot(:,1)=[ ];
wakeplotX(:,1)=[ ];
wakeplotY(:,1)=[ ];
wakeplot(1,:)=[0];
flipud(wakeplot);
end
function thickness=findthickness(airfoil, Chord, xLoc)
Airfoil = load(airfoil);
Airfoil = Airfoil*Chord;
% blah....goodnight
AirfoilX=Airfoil(:,1);
[min_diff, k]=min(abs(AirfoilX));
for j=1:k
AirfoilYupper(j)=Airfoil(j,2);
AirfoilXupper(j)=Airfoil(j,1);
end
for j=1:length(Airfoil)-k
AirfoilYlower(j)=Airfoil(length(Airfoil)-(j-1), 2);
AirfoilXlower(j)=Airfoil(length(Airfoil)-(j-1), 1);
end
AirfoilYupper=fliplr(AirfoilYupper);
AirfoilXupper=fliplr(AirfoilXupper);
AirfoilYlower=fliplr(AirfoilYlower);
AirfoilXlower=fliplr(AirfoilXlower);
AirfoilYlower=[0 AirfoilYlower];
AirfoilXlower=[0 AirfoilXlower];
[min_diff, k]=min(abs(AirfoilX));
[min_diff, kU]=min(abs(AirfoilXupper-xLoc));
[min_diff, kL]=min(abs(AirfoilXlower-xLoc));
if xLoc<AirfoilXupper(kU)
xFitU(1)=AirfoilXupper(kU-1);
xFitU(2)=AirfoilXupper(kU);
yFitU(1)=AirfoilYupper(kU-1);
yFitU(2)=AirfoilYupper(kU);
else
xFitU(1)=AirfoilXupper(kU);
xFitU(2)=AirfoilXupper(kU+1);
yFitU(1)=AirfoilYupper(kU);
yFitU(2)=AirfoilYupper(kU+1);
end
if xLoc<AirfoilXlower(kL)
xFitL(1)=AirfoilXlower(kL-1);
xFitL(2)=AirfoilXlower(kL);
yFitL(1)=AirfoilYlower(kL-1);
yFitL(2)=AirfoilYlower(kL);
else
xFitL(1)=AirfoilXlower(kL);
xFitL(2)=AirfoilXlower(kL+1);
yFitL(1)=AirfoilYlower(kL);
yFitL(2)=AirfoilYlower(kL+1);
end
aU = polyfit(xFitU, yFitU,1);
aL = polyfit(xFitL, yFitL,1);
% yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2);
% thickness = AirfoilYupper(xLoc_indu)-AirfoilYlower(xLoc_indl);
thickness = (aU(1)*xLoc+aU(2))-(aL(1)*xLoc+aL(2));
end