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Feature 2.5.2 #31

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Mar 17, 2022
Merged

Feature 2.5.2 #31

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517e67b
updated existing tutorials
planes Mar 15, 2022
fb39e39
new tutorials
planes Mar 16, 2022
b239799
removing redundant airfoils
planes Mar 16, 2022
e219743
airfoil clean up and versioning
planes Mar 16, 2022
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40 changes: 40 additions & 0 deletions Airfoils/NACA_4412.txt
View file
Open in desktop
Original file line number Diff line number Diff line change
@@ -0,0 +1,40 @@
NACA 4412
18. 18.

0.000000 0.000000
0.012500 0.024400
0.025000 0.033900
0.050000 0.047300
0.075000 0.057600
0.100000 0.065900
0.150000 0.078900
0.200000 0.088000
0.250000 0.094100
0.300000 0.097600
0.400000 0.098000
0.500000 0.091900
0.600000 0.081400
0.700000 0.066900
0.800000 0.048900
0.900000 0.027100
0.950000 0.014700
1.000000 0.001300

0.000000 0.000000
0.012500 -0.014300
0.025000 -0.019500
0.050000 -0.024900
0.075000 -0.027400
0.100000 -0.028600
0.150000 -0.028800
0.200000 -0.027400
0.250000 -0.025000
0.300000 -0.022600
0.400000 -0.018000
0.500000 -0.014000
0.600000 -0.010000
0.700000 -0.006500
0.800000 -0.003900
0.900000 -0.002200
0.950000 -0.001600
1.000000 -0.001300
119 changes: 119 additions & 0 deletions Airfoils/Polars/NACA_4412_polar_Re_100000.txt
View file
Open in desktop
Original file line number Diff line number Diff line change
@@ -0,0 +1,119 @@

XFOIL Version 6.96

Calculated polar for: NACA 4412

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3426 0.10705 0.10189 -0.0379 1.0000 0.1297
-9.250 -0.3784 0.10671 0.10171 -0.0397 1.0000 0.1327
-9.000 -0.4173 0.10641 0.10160 -0.0391 1.0000 0.1332
-8.750 -0.3682 0.09949 0.09457 -0.0361 1.0000 0.1363
-8.500 -0.3611 0.09726 0.09235 -0.0338 1.0000 0.1402
-8.250 -0.3724 0.09561 0.09079 -0.0319 1.0000 0.1442
-8.000 -0.4032 0.09481 0.09013 -0.0296 1.0000 0.1469
-7.750 -0.4436 0.09403 0.08951 -0.0287 1.0000 0.1481
-7.500 -0.4819 0.09082 0.08639 -0.0339 1.0000 0.1493
-7.250 -0.4471 0.08830 0.08388 -0.0235 1.0000 0.1526
-7.000 -0.4480 0.08640 0.08202 -0.0209 1.0000 0.1558
-6.750 -0.4588 0.08412 0.07980 -0.0206 1.0000 0.1600
-6.500 -0.4847 0.07929 0.07495 -0.0287 1.0000 0.1662
-6.250 -0.4783 0.07718 0.07290 -0.0243 1.0000 0.1680
-6.000 -0.4744 0.07516 0.07091 -0.0219 1.0000 0.1710
-5.750 -0.4612 0.06965 0.06522 -0.0315 0.9966 0.1830
-5.500 -0.4309 0.06730 0.06289 -0.0316 0.9913 0.1898
-5.250 -0.3801 0.03672 0.02954 -0.0608 0.9884 0.1054
-5.000 -0.3390 0.03524 0.02804 -0.0644 0.9827 0.1094
-4.750 -0.2986 0.03253 0.02478 -0.0679 0.9764 0.1116
-4.500 -0.2547 0.03033 0.02199 -0.0716 0.9711 0.1152
-4.250 -0.2155 0.02874 0.02008 -0.0743 0.9639 0.1211
-4.000 -0.1732 0.02773 0.01892 -0.0774 0.9576 0.1286
-3.750 -0.1342 0.02656 0.01755 -0.0797 0.9500 0.1373
-3.500 -0.0916 0.02579 0.01667 -0.0827 0.9435 0.1516
-3.250 -0.0546 0.02511 0.01596 -0.0846 0.9347 0.1675
-3.000 -0.0135 0.02457 0.01552 -0.0873 0.9278 0.1881
-2.750 0.0233 0.02414 0.01507 -0.0891 0.9186 0.2119
-2.500 0.0621 0.02363 0.01470 -0.0912 0.9110 0.2389
-2.250 0.0998 0.02306 0.01425 -0.0931 0.9024 0.2721
-2.000 0.1378 0.02248 0.01382 -0.0950 0.8945 0.3153
-1.750 0.1759 0.02179 0.01342 -0.0968 0.8865 0.3683
-1.500 0.2137 0.02102 0.01305 -0.0985 0.8792 0.4420
-1.250 0.2473 0.02001 0.01285 -0.0990 0.8713 0.6046
-1.000 0.3011 0.01877 0.01237 -0.1014 0.8681 1.0000
-0.750 0.3304 0.01877 0.01214 -0.1016 0.8562 1.0000
-0.500 0.3765 0.01838 0.01153 -0.1044 0.8513 1.0000
-0.250 0.4028 0.01841 0.01142 -0.1039 0.8387 1.0000
0.000 0.4335 0.01835 0.01123 -0.1041 0.8283 1.0000
0.250 0.4720 0.01803 0.01077 -0.1054 0.8210 1.0000
0.500 0.4988 0.01808 0.01072 -0.1049 0.8090 1.0000
0.750 0.5348 0.01782 0.01035 -0.1058 0.8013 1.0000
1.000 0.5631 0.01782 0.01026 -0.1055 0.7900 1.0000
1.250 0.5902 0.01789 0.01027 -0.1051 0.7784 1.0000
1.500 0.6265 0.01763 0.00990 -0.1059 0.7710 1.0000
1.750 0.6506 0.01784 0.01006 -0.1050 0.7582 1.0000
2.000 0.6774 0.01798 0.01015 -0.1045 0.7469 1.0000
2.250 0.7110 0.01786 0.00993 -0.1050 0.7386 1.0000
2.500 0.7347 0.01814 0.01020 -0.1041 0.7259 1.0000
2.750 0.7611 0.01836 0.01039 -0.1036 0.7150 1.0000
3.000 0.7929 0.01834 0.01028 -0.1038 0.7060 1.0000
3.250 0.8161 0.01870 0.01065 -0.1029 0.6937 1.0000
3.500 0.8423 0.01895 0.01090 -0.1024 0.6829 1.0000
3.750 0.8728 0.01902 0.01091 -0.1024 0.6736 1.0000
4.000 0.8957 0.01941 0.01134 -0.1015 0.6614 1.0000
4.250 0.9217 0.01970 0.01163 -0.1010 0.6508 1.0000
4.500 0.9513 0.01982 0.01170 -0.1009 0.6411 1.0000
4.750 0.9739 0.02025 0.01220 -0.0999 0.6291 1.0000
5.000 0.9995 0.02057 0.01254 -0.0994 0.6185 1.0000
5.250 1.0286 0.02074 0.01268 -0.0992 0.6086 1.0000
5.500 1.0508 0.02119 0.01322 -0.0982 0.5964 1.0000
5.750 1.0755 0.02148 0.01355 -0.0974 0.5844 1.0000
6.000 1.1016 0.02159 0.01364 -0.0966 0.5709 1.0000
6.250 1.1279 0.02168 0.01370 -0.0958 0.5569 1.0000
6.500 1.1534 0.02184 0.01386 -0.0950 0.5432 1.0000
6.750 1.1757 0.02207 0.01413 -0.0937 0.5281 1.0000
7.000 1.1987 0.02216 0.01423 -0.0924 0.5114 1.0000
7.250 1.2212 0.02223 0.01428 -0.0911 0.4939 1.0000
7.500 1.2409 0.02240 0.01449 -0.0893 0.4761 1.0000
7.750 1.2594 0.02262 0.01478 -0.0875 0.4582 1.0000
8.000 1.2769 0.02285 0.01510 -0.0854 0.4393 1.0000
8.250 1.2933 0.02308 0.01539 -0.0832 0.4192 1.0000
8.500 1.3086 0.02333 0.01564 -0.0809 0.3979 1.0000
8.750 1.3197 0.02372 0.01612 -0.0779 0.3730 1.0000
9.000 1.3281 0.02421 0.01659 -0.0746 0.3445 1.0000
9.250 1.3316 0.02495 0.01728 -0.0707 0.3104 1.0000
9.500 1.3276 0.02605 0.01816 -0.0657 0.2733 1.0000
9.750 1.3204 0.02765 0.01952 -0.0608 0.2346 1.0000
10.000 1.3127 0.02965 0.02123 -0.0564 0.2023 1.0000
10.250 1.3077 0.03176 0.02308 -0.0527 0.1788 1.0000
10.500 1.3074 0.03378 0.02497 -0.0497 0.1606 1.0000
10.750 1.3110 0.03571 0.02678 -0.0472 0.1474 1.0000
11.000 1.3189 0.03755 0.02847 -0.0451 0.1369 1.0000
11.250 1.3289 0.03922 0.03015 -0.0434 0.1279 1.0000
11.500 1.3439 0.04092 0.03184 -0.0420 0.1203 1.0000
11.750 1.3595 0.04250 0.03339 -0.0408 0.1136 1.0000
12.000 1.3787 0.04430 0.03522 -0.0399 0.1076 1.0000
12.250 1.3912 0.04604 0.03710 -0.0386 0.1025 1.0000
12.500 1.4202 0.04801 0.03893 -0.0387 0.0966 1.0000
12.750 1.4239 0.05002 0.04125 -0.0367 0.0932 1.0000
13.000 1.4319 0.05205 0.04343 -0.0351 0.0895 1.0000
13.250 1.4604 0.05447 0.04574 -0.0355 0.0845 1.0000
13.500 1.4540 0.05696 0.04860 -0.0329 0.0825 1.0000
13.750 1.4507 0.05963 0.05156 -0.0309 0.0802 1.0000
14.000 1.4512 0.06218 0.05428 -0.0294 0.0775 1.0000
14.250 1.4783 0.06519 0.05713 -0.0297 0.0734 1.0000
14.500 1.4597 0.06850 0.06082 -0.0274 0.0727 1.0000
14.750 1.4404 0.07234 0.06501 -0.0257 0.0720 1.0000
15.000 1.4201 0.07667 0.06967 -0.0247 0.0712 1.0000
15.250 1.3983 0.08150 0.07481 -0.0243 0.0706 1.0000
15.500 1.3742 0.08690 0.08051 -0.0247 0.0701 1.0000
15.750 1.3474 0.09302 0.08692 -0.0259 0.0699 1.0000
16.000 1.3171 0.10006 0.09424 -0.0282 0.0701 1.0000
16.250 1.2836 0.10833 0.10277 -0.0317 0.0706 1.0000
16.500 1.2473 0.11795 0.11263 -0.0367 0.0714 1.0000
16.750 1.2101 0.12886 0.12372 -0.0430 0.0723 1.0000
17.000 1.1753 0.14068 0.13565 -0.0500 0.0732 1.0000
148 changes: 148 additions & 0 deletions Airfoils/Polars/NACA_4412_polar_Re_1000000.txt
View file
Open in desktop
Original file line number Diff line number Diff line change
@@ -0,0 +1,148 @@

XFOIL Version 6.96

Calculated polar for: NACA 4412

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8374 0.08373 0.08141 -0.0585 1.0000 0.0169
-15.500 -0.9127 0.06837 0.06591 -0.0687 1.0000 0.0166
-15.250 -1.0965 0.03328 0.03022 -0.0993 1.0000 0.0153
-15.000 -1.1161 0.03120 0.02803 -0.0956 1.0000 0.0154
-14.750 -1.1210 0.02977 0.02651 -0.0926 1.0000 0.0156
-14.500 -1.1215 0.02857 0.02523 -0.0896 1.0000 0.0159
-14.250 -1.1181 0.02751 0.02407 -0.0870 1.0000 0.0162
-14.000 -1.0990 0.02637 0.02282 -0.0871 0.9992 0.0166
-13.750 -1.0711 0.02533 0.02165 -0.0885 0.9979 0.0170
-13.500 -1.0462 0.02365 0.01985 -0.0903 0.9963 0.0177
-13.250 -1.0163 0.02288 0.01905 -0.0918 0.9951 0.0183
-13.000 -0.9847 0.02237 0.01850 -0.0933 0.9943 0.0189
-12.750 -0.9549 0.02183 0.01790 -0.0943 0.9930 0.0195
-12.500 -0.9260 0.02126 0.01724 -0.0952 0.9911 0.0201
-12.250 -0.8954 0.02078 0.01666 -0.0963 0.9894 0.0206
-12.000 -0.8682 0.01946 0.01525 -0.0976 0.9877 0.0214
-11.750 -0.8365 0.01894 0.01471 -0.0990 0.9866 0.0220
-11.500 -0.8038 0.01852 0.01424 -0.1004 0.9857 0.0227
-11.250 -0.7707 0.01808 0.01375 -0.1019 0.9849 0.0235
-11.000 -0.7369 0.01769 0.01328 -0.1035 0.9843 0.0242
-10.750 -0.7070 0.01745 0.01297 -0.1041 0.9819 0.0246
-10.500 -0.6803 0.01619 0.01161 -0.1049 0.9793 0.0257
-10.250 -0.6491 0.01569 0.01109 -0.1060 0.9775 0.0264
-10.000 -0.6172 0.01529 0.01065 -0.1071 0.9759 0.0271
-9.750 -0.5850 0.01491 0.01022 -0.1082 0.9742 0.0279
-9.500 -0.5547 0.01456 0.00981 -0.1089 0.9718 0.0287
-9.250 -0.5287 0.01426 0.00944 -0.1085 0.9665 0.0292
-9.000 -0.5023 0.01345 0.00855 -0.1085 0.9622 0.0299
-8.750 -0.4769 0.01285 0.00791 -0.1082 0.9574 0.0309
-8.500 -0.4513 0.01249 0.00752 -0.1078 0.9519 0.0317
-8.250 -0.4243 0.01214 0.00713 -0.1076 0.9474 0.0324
-8.000 -0.3979 0.01184 0.00678 -0.1073 0.9422 0.0333
-7.750 -0.3715 0.01155 0.00644 -0.1070 0.9363 0.0340
-7.500 -0.3442 0.01127 0.00609 -0.1068 0.9313 0.0345
-7.250 -0.3183 0.01080 0.00556 -0.1064 0.9249 0.0354
-7.000 -0.2921 0.01033 0.00505 -0.1061 0.9186 0.0365
-6.750 -0.2649 0.01003 0.00471 -0.1059 0.9125 0.0375
-6.500 -0.2377 0.00977 0.00441 -0.1057 0.9053 0.0384
-6.000 -0.1825 0.00935 0.00389 -0.1054 0.8910 0.0404
-5.750 -0.1549 0.00912 0.00360 -0.1052 0.8835 0.0414
-5.500 -0.1275 0.00880 0.00325 -0.1051 0.8751 0.0435
-5.000 -0.0718 0.00845 0.00283 -0.1049 0.8578 0.0476
-4.750 -0.0441 0.00824 0.00259 -0.1047 0.8488 0.0519
-4.500 -0.0162 0.00810 0.00243 -0.1046 0.8388 0.0569
-4.250 0.0117 0.00793 0.00228 -0.1045 0.8288 0.0655
-4.000 0.0394 0.00780 0.00213 -0.1044 0.8184 0.0745
-3.750 0.0674 0.00769 0.00201 -0.1044 0.8073 0.0820
-3.500 0.0954 0.00761 0.00191 -0.1043 0.7964 0.0890
-3.250 0.1232 0.00752 0.00180 -0.1042 0.7851 0.0977
-3.000 0.1512 0.00745 0.00171 -0.1041 0.7733 0.1066
-2.750 0.1791 0.00737 0.00163 -0.1040 0.7616 0.1182
-2.500 0.2069 0.00729 0.00156 -0.1040 0.7497 0.1332
-2.250 0.2346 0.00723 0.00150 -0.1039 0.7378 0.1502
-2.000 0.2625 0.00715 0.00145 -0.1038 0.7254 0.1697
-1.750 0.2903 0.00709 0.00142 -0.1038 0.7132 0.1927
-1.500 0.3180 0.00703 0.00141 -0.1037 0.7012 0.2214
-1.250 0.3456 0.00701 0.00139 -0.1036 0.6886 0.2466
-1.000 0.3734 0.00697 0.00138 -0.1035 0.6754 0.2686
-0.750 0.4012 0.00694 0.00137 -0.1035 0.6626 0.2903
-0.500 0.4288 0.00691 0.00138 -0.1034 0.6497 0.3203
-0.250 0.4562 0.00686 0.00139 -0.1033 0.6365 0.3629
0.000 0.4833 0.00678 0.00141 -0.1032 0.6232 0.4192
0.250 0.5102 0.00658 0.00146 -0.1031 0.6101 0.5177
0.500 0.5366 0.00635 0.00153 -0.1029 0.5975 0.6393
0.750 0.5622 0.00617 0.00160 -0.1024 0.5856 0.7449
1.000 0.5842 0.00594 0.00170 -0.1009 0.5740 0.8717
1.250 0.6163 0.00588 0.00177 -0.1014 0.5622 0.9842
1.500 0.6525 0.00598 0.00181 -0.1033 0.5505 1.0000
1.750 0.6788 0.00611 0.00186 -0.1029 0.5398 1.0000
2.000 0.7055 0.00622 0.00192 -0.1026 0.5294 1.0000
2.250 0.7325 0.00633 0.00199 -0.1024 0.5204 1.0000
2.500 0.7592 0.00646 0.00206 -0.1022 0.5112 1.0000
2.750 0.7865 0.00656 0.00213 -0.1020 0.5029 1.0000
3.250 0.8405 0.00681 0.00231 -0.1016 0.4847 1.0000
3.500 0.8672 0.00696 0.00240 -0.1014 0.4746 1.0000
3.750 0.8941 0.00709 0.00250 -0.1012 0.4646 1.0000
4.000 0.9210 0.00722 0.00260 -0.1010 0.4540 1.0000
4.250 0.9473 0.00739 0.00272 -0.1007 0.4426 1.0000
4.500 0.9734 0.00758 0.00284 -0.1004 0.4273 1.0000
4.750 0.9993 0.00778 0.00297 -0.1001 0.4110 1.0000
5.000 1.0254 0.00797 0.00311 -0.0998 0.3979 1.0000
5.250 1.0518 0.00813 0.00326 -0.0995 0.3861 1.0000
5.500 1.0777 0.00834 0.00342 -0.0992 0.3731 1.0000
5.750 1.1031 0.00857 0.00359 -0.0988 0.3575 1.0000
6.000 1.1280 0.00884 0.00379 -0.0983 0.3398 1.0000
6.250 1.1523 0.00914 0.00401 -0.0978 0.3207 1.0000
6.500 1.1761 0.00948 0.00426 -0.0971 0.2993 1.0000
6.750 1.1988 0.00989 0.00455 -0.0963 0.2737 1.0000
7.000 1.2208 0.01036 0.00488 -0.0954 0.2461 1.0000
7.250 1.2417 0.01089 0.00526 -0.0943 0.2173 1.0000
7.500 1.2614 0.01149 0.00569 -0.0931 0.1865 1.0000
7.750 1.2793 0.01220 0.00621 -0.0915 0.1526 1.0000
8.000 1.2973 0.01288 0.00672 -0.0900 0.1252 1.0000
8.250 1.3164 0.01345 0.00719 -0.0887 0.1065 1.0000
8.500 1.3346 0.01404 0.00769 -0.0872 0.0893 1.0000
8.750 1.3514 0.01469 0.00823 -0.0854 0.0729 1.0000
9.000 1.3676 0.01527 0.00875 -0.0836 0.0622 1.0000
9.250 1.3835 0.01581 0.00926 -0.0817 0.0563 1.0000
9.500 1.4004 0.01631 0.00976 -0.0799 0.0521 1.0000
9.750 1.4171 0.01682 0.01028 -0.0782 0.0491 1.0000
10.000 1.4317 0.01746 0.01091 -0.0762 0.0459 1.0000
10.250 1.4484 0.01797 0.01147 -0.0746 0.0442 1.0000
10.500 1.4653 0.01849 0.01203 -0.0731 0.0427 1.0000
10.750 1.4805 0.01911 0.01267 -0.0714 0.0411 1.0000
11.000 1.4938 0.01986 0.01343 -0.0695 0.0392 1.0000
11.250 1.5061 0.02069 0.01430 -0.0676 0.0376 1.0000
11.500 1.5221 0.02129 0.01495 -0.0662 0.0368 1.0000
11.750 1.5369 0.02199 0.01570 -0.0647 0.0356 1.0000
12.000 1.5500 0.02282 0.01656 -0.0631 0.0343 1.0000
12.250 1.5608 0.02382 0.01758 -0.0614 0.0330 1.0000
12.500 1.5688 0.02506 0.01888 -0.0594 0.0316 1.0000
12.750 1.5831 0.02588 0.01975 -0.0582 0.0308 1.0000
13.000 1.5959 0.02683 0.02075 -0.0569 0.0298 1.0000
13.250 1.6066 0.02796 0.02192 -0.0555 0.0286 1.0000
13.500 1.6141 0.02939 0.02338 -0.0540 0.0273 1.0000
13.750 1.6213 0.03089 0.02494 -0.0526 0.0262 1.0000
14.000 1.6325 0.03209 0.02620 -0.0516 0.0252 1.0000
14.250 1.6414 0.03354 0.02770 -0.0505 0.0241 1.0000
14.500 1.6474 0.03528 0.02947 -0.0493 0.0229 1.0000
14.750 1.6508 0.03731 0.03156 -0.0482 0.0218 1.0000
15.000 1.6585 0.03899 0.03332 -0.0474 0.0209 1.0000
15.250 1.6638 0.04096 0.03533 -0.0466 0.0198 1.0000
15.500 1.6661 0.04330 0.03772 -0.0458 0.0187 1.0000
15.750 1.6666 0.04589 0.04037 -0.0451 0.0179 1.0000
16.000 1.6698 0.04827 0.04284 -0.0447 0.0171 1.0000
16.250 1.6706 0.05099 0.04562 -0.0443 0.0164 1.0000
16.500 1.6692 0.05402 0.04871 -0.0440 0.0157 1.0000
16.750 1.6638 0.05759 0.05235 -0.0439 0.0151 1.0000
17.000 1.6605 0.06101 0.05587 -0.0439 0.0146 1.0000
17.250 1.6584 0.06435 0.05931 -0.0441 0.0142 1.0000
17.500 1.6548 0.06793 0.06298 -0.0444 0.0138 1.0000
17.750 1.6497 0.07175 0.06689 -0.0448 0.0134 1.0000
18.000 1.6430 0.07583 0.07106 -0.0453 0.0131 1.0000
18.250 1.6346 0.08024 0.07555 -0.0461 0.0128 1.0000
18.500 1.6237 0.08507 0.08047 -0.0470 0.0124 1.0000
18.750 1.6097 0.09040 0.08590 -0.0482 0.0121 1.0000
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