GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 795 smoothed (goe795sm-il) Reynolds number: 100,000 Max Cl/Cd: 54.25 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe795sm-il-100000-n5.txt Download as CSV file: xf-goe795sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4620 0.09102 0.08593 -0.0323 1.0000 0.0261
-8.750 -0.4646 0.08721 0.08214 -0.0332 1.0000 0.0260
-8.500 -0.4689 0.08348 0.07848 -0.0341 1.0000 0.0258
-8.250 -0.4747 0.08013 0.07521 -0.0346 1.0000 0.0255
-8.000 -0.4841 0.07578 0.07093 -0.0364 1.0000 0.0257
-7.750 -0.4881 0.07165 0.06684 -0.0379 1.0000 0.0254
-7.500 -0.4927 0.06639 0.06156 -0.0401 1.0000 0.0256
-7.250 -0.4959 0.06106 0.05619 -0.0415 1.0000 0.0257
-7.000 -0.4989 0.05525 0.05023 -0.0422 1.0000 0.0259
-6.750 -0.5004 0.05010 0.04481 -0.0419 1.0000 0.0261
-6.500 -0.4992 0.04634 0.04090 -0.0408 1.0000 0.0269
-6.250 -0.4936 0.04324 0.03757 -0.0394 1.0000 0.0275
-6.000 -0.4875 0.03942 0.03339 -0.0378 1.0000 0.0278
-5.750 -0.4787 0.03607 0.02966 -0.0360 1.0000 0.0281
-5.500 -0.4675 0.03323 0.02644 -0.0342 1.0000 0.0289
-5.250 -0.4543 0.03062 0.02342 -0.0323 1.0000 0.0297
-5.000 -0.4391 0.02831 0.02067 -0.0305 1.0000 0.0309
-4.750 -0.4217 0.02645 0.01836 -0.0288 0.9999 0.0337
-4.500 -0.3896 0.02434 0.01572 -0.0299 0.9957 0.0373
-4.250 -0.3579 0.02289 0.01408 -0.0310 0.9912 0.0403
-4.000 -0.3248 0.02180 0.01263 -0.0322 0.9863 0.0463
-3.750 -0.2919 0.02057 0.01126 -0.0334 0.9820 0.0514
-3.500 -0.2607 0.01972 0.01027 -0.0342 0.9761 0.0581
-3.250 -0.2272 0.01889 0.00938 -0.0356 0.9713 0.0664
-3.000 -0.1967 0.01822 0.00852 -0.0361 0.9648 0.0744
-2.750 -0.1641 0.01758 0.00789 -0.0373 0.9592 0.0872
-2.500 -0.1333 0.01699 0.00731 -0.0381 0.9528 0.1006
-2.250 -0.1016 0.01642 0.00687 -0.0390 0.9465 0.1265
-2.000 -0.0693 0.01585 0.00653 -0.0401 0.9407 0.1822
-1.750 -0.0385 0.01532 0.00631 -0.0410 0.9336 0.2727
-1.500 -0.0018 0.01464 0.00609 -0.0431 0.9295 0.3990
-1.250 0.0950 0.01322 0.00626 -0.0567 0.9401 1.0000
-1.000 0.1304 0.01319 0.00603 -0.0583 0.9323 1.0000
-0.750 0.1651 0.01315 0.00583 -0.0597 0.9243 1.0000
-0.500 0.2032 0.01309 0.00562 -0.0618 0.9172 1.0000
-0.250 0.2361 0.01305 0.00547 -0.0628 0.9075 1.0000
0.000 0.2729 0.01297 0.00529 -0.0645 0.8991 1.0000
0.250 0.3078 0.01289 0.00513 -0.0658 0.8891 1.0000
0.500 0.3400 0.01283 0.00501 -0.0665 0.8773 1.0000
0.750 0.3725 0.01278 0.00491 -0.0673 0.8654 1.0000
1.000 0.4046 0.01274 0.00484 -0.0679 0.8532 1.0000
1.250 0.4360 0.01272 0.00478 -0.0684 0.8407 1.0000
1.500 0.4663 0.01271 0.00475 -0.0686 0.8274 1.0000
1.750 0.4954 0.01273 0.00476 -0.0686 0.8134 1.0000
2.000 0.5235 0.01277 0.00481 -0.0684 0.7986 1.0000
2.250 0.5509 0.01282 0.00487 -0.0680 0.7831 1.0000
2.500 0.5777 0.01289 0.00495 -0.0675 0.7669 1.0000
2.750 0.6042 0.01297 0.00506 -0.0669 0.7498 1.0000
3.000 0.6300 0.01306 0.00516 -0.0661 0.7314 1.0000
3.250 0.6540 0.01318 0.00530 -0.0650 0.7102 1.0000
3.500 0.6779 0.01330 0.00542 -0.0638 0.6858 1.0000
3.750 0.7007 0.01345 0.00553 -0.0623 0.6564 1.0000
4.000 0.7228 0.01363 0.00569 -0.0607 0.6237 1.0000
4.250 0.7444 0.01385 0.00587 -0.0591 0.5891 1.0000
4.500 0.7654 0.01413 0.00607 -0.0574 0.5517 1.0000
4.750 0.7855 0.01448 0.00632 -0.0556 0.5109 1.0000
5.000 0.8047 0.01490 0.00662 -0.0536 0.4670 1.0000
5.250 0.8230 0.01540 0.00702 -0.0516 0.4215 1.0000
5.500 0.8403 0.01599 0.00745 -0.0496 0.3729 1.0000
5.750 0.8567 0.01668 0.00795 -0.0474 0.3217 1.0000
6.000 0.8721 0.01747 0.00851 -0.0453 0.2640 1.0000
6.250 0.8864 0.01843 0.00917 -0.0430 0.2027 1.0000
6.500 0.9008 0.01948 0.00996 -0.0410 0.1519 1.0000
6.750 0.9157 0.02053 0.01082 -0.0390 0.1144 1.0000
7.000 0.9309 0.02160 0.01176 -0.0370 0.0852 1.0000
7.250 0.9450 0.02276 0.01281 -0.0349 0.0651 1.0000
7.500 0.9592 0.02393 0.01398 -0.0327 0.0511 1.0000
7.750 0.9719 0.02520 0.01525 -0.0304 0.0426 1.0000
8.000 0.9854 0.02643 0.01665 -0.0280 0.0381 1.0000
8.250 0.9987 0.02766 0.01799 -0.0258 0.0337 1.0000
8.500 1.0105 0.02913 0.01955 -0.0236 0.0304 1.0000
8.750 1.0247 0.03061 0.02121 -0.0215 0.0281 1.0000
9.000 1.0389 0.03227 0.02302 -0.0196 0.0264 1.0000
9.250 1.0532 0.03403 0.02493 -0.0178 0.0250 1.0000
9.500 1.0668 0.03605 0.02707 -0.0160 0.0238 1.0000
9.750 1.0791 0.03886 0.03003 -0.0145 0.0226 1.0000
10.000 1.0896 0.04076 0.03230 -0.0123 0.0214 1.0000
10.250 1.0960 0.04287 0.03476 -0.0097 0.0200 1.0000
10.500 1.0989 0.04543 0.03763 -0.0069 0.0194 1.0000
10.750 1.0972 0.04817 0.04074 -0.0039 0.0191 1.0000
11.000 1.0919 0.05099 0.04386 -0.0009 0.0187 1.0000
11.250 1.0832 0.05405 0.04721 0.0017 0.0186 1.0000
11.500 1.0710 0.05742 0.05087 0.0038 0.0184 1.0000
11.750 1.0563 0.06116 0.05488 0.0052 0.0183 1.0000
12.000 1.0389 0.06548 0.05945 0.0055 0.0183 1.0000
12.250 1.0198 0.07039 0.06460 0.0047 0.0184 1.0000
12.500 0.9982 0.07625 0.07068 0.0026 0.0186 1.0000
12.750 0.9744 0.08323 0.07786 -0.0011 0.0186 1.0000
13.000 0.9492 0.09166 0.08641 -0.0065 0.0190 1.0000
13.250 0.9211 0.10229 0.09717 -0.0137 0.0194 1.0000
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Polar data table (+)
Polar graphs
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