GOE 735 AIRFOIL (goe735-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 735 AIRFOIL (goe735-il) Reynolds number: 50,000 Max Cl/Cd: 16.36 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe735-il-50000-n5.txt Download as CSV file: xf-goe735-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 735 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2437 0.11922 0.11235 -0.0453 0.9351 0.1131
-12.500 -0.2463 0.11324 0.10629 -0.0508 0.9176 0.1152
-12.250 -0.2434 0.10835 0.10134 -0.0547 0.9007 0.1169
-12.000 -0.2261 0.10617 0.09906 -0.0557 0.8822 0.1192
-11.750 -0.2219 0.10285 0.09567 -0.0572 0.8670 0.1216
-11.500 -0.2269 0.09847 0.09123 -0.0595 0.8548 0.1239
-11.250 -0.2448 0.09234 0.08504 -0.0630 0.8450 0.1261
-11.000 -0.3207 0.07683 0.06943 -0.0746 0.8418 0.1282
-10.750 -0.2794 0.08024 0.07285 -0.0696 0.8254 0.1304
-10.500 -0.2947 0.07473 0.06729 -0.0726 0.8150 0.1325
-10.250 -0.3492 0.06638 0.05878 -0.0768 0.8071 0.1337
-10.000 -0.3926 0.06133 0.05353 -0.0762 0.7970 0.1349
-9.750 -0.4269 0.05812 0.05008 -0.0727 0.7872 0.1361
-9.500 -0.4526 0.05530 0.04698 -0.0693 0.7773 0.1379
-9.250 -0.4734 0.05256 0.04384 -0.0654 0.7680 0.1398
-9.000 -0.4833 0.05034 0.04126 -0.0621 0.7584 0.1422
-8.750 -0.4662 0.04945 0.04037 -0.0607 0.7484 0.1449
-8.500 -0.4551 0.04830 0.03909 -0.0589 0.7389 0.1477
-8.250 -0.4490 0.04684 0.03739 -0.0565 0.7294 0.1507
-8.000 -0.4457 0.04520 0.03535 -0.0537 0.7216 0.1541
-7.750 -0.4375 0.04383 0.03370 -0.0515 0.7114 0.1571
-7.500 -0.4176 0.04286 0.03267 -0.0501 0.7041 0.1600
-7.250 -0.4013 0.04204 0.03177 -0.0489 0.6936 0.1634
-7.000 -0.3854 0.04096 0.03043 -0.0471 0.6860 0.1674
-6.750 -0.3711 0.03991 0.02901 -0.0453 0.6777 0.1711
-6.500 -0.3503 0.03905 0.02810 -0.0444 0.6687 0.1744
-6.250 -0.3277 0.03823 0.02719 -0.0432 0.6626 0.1784
-6.000 -0.3086 0.03769 0.02656 -0.0423 0.6525 0.1827
-5.750 -0.2875 0.03687 0.02543 -0.0411 0.6456 0.1873
-5.500 -0.2637 0.03618 0.02469 -0.0404 0.6384 0.1916
-5.250 -0.2411 0.03575 0.02427 -0.0398 0.6296 0.1964
-5.000 -0.2158 0.03507 0.02339 -0.0390 0.6239 0.2024
-4.750 -0.1925 0.03471 0.02292 -0.0385 0.6156 0.2079
-4.500 -0.1670 0.03428 0.02254 -0.0381 0.6083 0.2140
-4.250 -0.1388 0.03367 0.02177 -0.0376 0.6033 0.2220
-4.000 -0.1150 0.03356 0.02169 -0.0374 0.5946 0.2292
-3.750 -0.0883 0.03322 0.02132 -0.0372 0.5882 0.2384
-3.500 -0.0581 0.03266 0.02068 -0.0371 0.5836 0.2497
-3.250 -0.0365 0.03277 0.02084 -0.0367 0.5753 0.2613
-3.000 -0.0119 0.03250 0.02062 -0.0362 0.5690 0.2755
-2.750 0.0151 0.03199 0.02013 -0.0356 0.5647 0.2946
-2.500 0.0333 0.03213 0.02040 -0.0347 0.5576 0.3153
-2.250 0.0522 0.03206 0.02047 -0.0335 0.5512 0.3439
-2.000 0.0741 0.03156 0.02015 -0.0322 0.5468 0.3847
-1.750 0.0938 0.03100 0.01989 -0.0304 0.5429 0.4427
-1.500 0.1007 0.03150 0.02093 -0.0279 0.5347 0.5133
-1.250 0.1489 0.03123 0.02138 -0.0299 0.5294 0.6687
-1.000 0.2323 0.03140 0.02158 -0.0366 0.5252 0.7912
-0.750 0.2637 0.03270 0.02285 -0.0375 0.5176 0.8393
-0.500 0.2996 0.03357 0.02359 -0.0384 0.5117 0.8780
-0.250 0.3502 0.03396 0.02374 -0.0412 0.5075 0.9132
0.000 0.4180 0.03435 0.02387 -0.0473 0.5031 0.9456
0.250 0.4723 0.03564 0.02515 -0.0538 0.4948 0.9717
0.500 0.5311 0.03561 0.02491 -0.0598 0.4897 0.9902
0.750 0.5773 0.03528 0.02435 -0.0632 0.4863 1.0000
1.000 0.5816 0.03647 0.02554 -0.0613 0.4812 1.0000
1.250 0.5797 0.03806 0.02718 -0.0588 0.4751 1.0000
1.500 0.5886 0.03874 0.02778 -0.0567 0.4710 1.0000
1.750 0.6045 0.03893 0.02783 -0.0550 0.4680 1.0000
2.000 0.6252 0.03887 0.02761 -0.0537 0.4657 1.0000
2.250 0.5735 0.04348 0.03247 -0.0473 0.4558 1.0000
2.500 0.5727 0.04469 0.03362 -0.0443 0.4515 1.0000
2.750 0.5854 0.04514 0.03396 -0.0423 0.4488 1.0000
3.000 0.6072 0.04512 0.03380 -0.0409 0.4468 1.0000
3.500 0.4851 0.05458 0.04339 -0.0273 0.4294 1.0000
3.750 0.4126 0.06175 0.05064 -0.0228 0.4183 1.0000
4.000 0.4137 0.06349 0.05230 -0.0210 0.4142 1.0000
4.250 0.4287 0.06418 0.05288 -0.0195 0.4115 1.0000
4.500 0.4503 0.06438 0.05297 -0.0182 0.4096 1.0000
5.000 0.4047 0.07237 0.06094 -0.0148 0.3963 1.0000
5.250 0.4183 0.07347 0.06196 -0.0137 0.3937 1.0000
5.500 0.4376 0.07409 0.06249 -0.0126 0.3915 1.0000
5.750 0.4119 0.07860 0.06701 -0.0115 0.3846 1.0000
6.000 0.4107 0.08109 0.06947 -0.0106 0.3800 1.0000
6.250 0.4207 0.08269 0.07102 -0.0098 0.3770 1.0000
6.500 0.4379 0.08367 0.07192 -0.0089 0.3746 1.0000
6.750 0.4603 0.08422 0.07241 -0.0081 0.3727 1.0000
7.000 0.4278 0.08960 0.07783 -0.0078 0.3648 1.0000
7.250 0.4334 0.09172 0.07992 -0.0072 0.3611 1.0000
7.500 0.4472 0.09312 0.08129 -0.0066 0.3583 1.0000
7.750 0.4671 0.09400 0.08210 -0.0059 0.3560 1.0000
8.000 0.4562 0.09763 0.08575 -0.0057 0.3505 1.0000
8.250 0.4538 0.10054 0.08867 -0.0055 0.3458 1.0000
8.500 0.4635 0.10242 0.09053 -0.0051 0.3425 1.0000
8.750 0.4810 0.10357 0.09163 -0.0045 0.3398 1.0000
9.000 0.5026 0.10442 0.09244 -0.0039 0.3379 1.0000
9.250 0.4794 0.10923 0.09731 -0.0043 0.3309 1.0000
9.500 0.4842 0.11163 0.09971 -0.0042 0.3273 1.0000
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