GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 436 AIRFOIL (goe436-il) Reynolds number: 200,000 Max Cl/Cd: 69.09 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe436-il-200000-n5.txt Download as CSV file: xf-goe436-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 436 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3745 0.09220 0.08844 -0.0390 1.0000 0.0340
-9.500 -0.3889 0.08699 0.08328 -0.0410 1.0000 0.0351
-9.250 -0.4146 0.08062 0.07701 -0.0433 1.0000 0.0360
-9.000 -0.4175 0.07896 0.07541 -0.0422 1.0000 0.0363
-8.750 -0.4318 0.07668 0.07320 -0.0407 1.0000 0.0365
-8.500 -0.4394 0.07413 0.07070 -0.0413 0.9979 0.0369
-8.250 -0.4219 0.06854 0.06506 -0.0498 0.9900 0.0376
-8.000 -0.4055 0.06232 0.05875 -0.0585 0.9827 0.0389
-7.500 -0.4048 0.03638 0.03151 -0.0774 0.9605 0.0431
-7.250 -0.3805 0.03554 0.03060 -0.0778 0.9542 0.0438
-7.000 -0.3539 0.03404 0.02897 -0.0790 0.9494 0.0447
-6.750 -0.3270 0.03116 0.02576 -0.0808 0.9459 0.0458
-6.500 -0.3078 0.02850 0.02272 -0.0805 0.9379 0.0469
-6.250 -0.2813 0.02593 0.01969 -0.0813 0.9324 0.0488
-6.000 -0.2561 0.02384 0.01712 -0.0814 0.9251 0.0500
-5.750 -0.2284 0.02218 0.01512 -0.0818 0.9175 0.0509
-5.500 -0.1995 0.02097 0.01378 -0.0822 0.9098 0.0517
-5.250 -0.1698 0.02016 0.01287 -0.0827 0.9013 0.0527
-5.000 -0.1409 0.01950 0.01211 -0.0829 0.8924 0.0540
-4.750 -0.1098 0.01876 0.01122 -0.0835 0.8843 0.0556
-4.500 -0.0819 0.01799 0.01029 -0.0834 0.8739 0.0568
-4.250 -0.0520 0.01722 0.00934 -0.0836 0.8637 0.0582
-4.000 -0.0225 0.01656 0.00852 -0.0837 0.8532 0.0593
-3.750 0.0050 0.01606 0.00787 -0.0834 0.8421 0.0604
-3.500 0.0326 0.01537 0.00714 -0.0832 0.8323 0.0622
-3.250 0.0603 0.01497 0.00671 -0.0831 0.8217 0.0641
-3.000 0.0866 0.01461 0.00630 -0.0826 0.8102 0.0658
-2.750 0.1133 0.01424 0.00587 -0.0821 0.7985 0.0676
-2.500 0.1400 0.01391 0.00546 -0.0817 0.7866 0.0694
-2.250 0.1659 0.01364 0.00512 -0.0810 0.7732 0.0715
-2.000 0.1911 0.01334 0.00478 -0.0803 0.7583 0.0738
-1.750 0.2161 0.01303 0.00447 -0.0796 0.7423 0.0767
-1.500 0.2414 0.01282 0.00421 -0.0789 0.7249 0.0793
-1.250 0.2666 0.01265 0.00397 -0.0781 0.7060 0.0824
-1.000 0.2918 0.01253 0.00374 -0.0773 0.6854 0.0857
-0.750 0.3162 0.01238 0.00352 -0.0764 0.6642 0.0907
-0.500 0.3408 0.01232 0.00337 -0.0756 0.6435 0.0965
-0.250 0.3653 0.01228 0.00324 -0.0747 0.6236 0.1033
0.000 0.3898 0.01224 0.00315 -0.0739 0.6047 0.1147
0.250 0.4137 0.01217 0.00311 -0.0730 0.5855 0.1406
0.500 0.4360 0.01191 0.00308 -0.0720 0.5654 0.2344
1.000 0.5457 0.01042 0.00337 -0.0830 0.5074 0.9986
1.250 0.5687 0.01063 0.00339 -0.0820 0.4873 1.0000
1.500 0.5899 0.01084 0.00344 -0.0806 0.4709 1.0000
1.750 0.6114 0.01105 0.00351 -0.0793 0.4568 1.0000
2.000 0.6332 0.01126 0.00361 -0.0780 0.4446 1.0000
2.250 0.6552 0.01149 0.00372 -0.0768 0.4344 1.0000
2.500 0.6775 0.01171 0.00384 -0.0757 0.4251 1.0000
2.750 0.7002 0.01192 0.00398 -0.0746 0.4175 1.0000
3.000 0.7231 0.01214 0.00414 -0.0736 0.4104 1.0000
3.250 0.7460 0.01237 0.00430 -0.0726 0.4044 1.0000
3.500 0.7695 0.01257 0.00448 -0.0716 0.3978 1.0000
3.750 0.7925 0.01282 0.00467 -0.0707 0.3919 1.0000
4.000 0.8161 0.01304 0.00487 -0.0698 0.3865 1.0000
4.250 0.8399 0.01326 0.00507 -0.0690 0.3809 1.0000
4.500 0.8628 0.01353 0.00529 -0.0680 0.3747 1.0000
4.750 0.8863 0.01373 0.00551 -0.0672 0.3673 1.0000
5.000 0.9089 0.01398 0.00571 -0.0662 0.3595 1.0000
5.250 0.9318 0.01419 0.00593 -0.0652 0.3507 1.0000
5.500 0.9537 0.01445 0.00614 -0.0641 0.3422 1.0000
5.750 0.9769 0.01465 0.00638 -0.0633 0.3341 1.0000
6.000 0.9992 0.01491 0.00663 -0.0622 0.3272 1.0000
6.250 1.0223 0.01514 0.00690 -0.0614 0.3211 1.0000
6.500 1.0449 0.01538 0.00718 -0.0604 0.3145 1.0000
6.750 1.0670 0.01565 0.00746 -0.0594 0.3081 1.0000
7.000 1.0896 0.01589 0.00777 -0.0585 0.3010 1.0000
7.250 1.1108 0.01619 0.00807 -0.0574 0.2946 1.0000
7.500 1.1333 0.01643 0.00840 -0.0564 0.2873 1.0000
7.750 1.1539 0.01674 0.00873 -0.0552 0.2798 1.0000
8.000 1.1752 0.01701 0.00908 -0.0541 0.2704 1.0000
8.250 1.1951 0.01734 0.00944 -0.0528 0.2621 1.0000
8.500 1.2149 0.01766 0.00981 -0.0515 0.2517 1.0000
8.750 1.2338 0.01802 0.01022 -0.0501 0.2396 1.0000
9.000 1.2513 0.01843 0.01065 -0.0484 0.2257 1.0000
9.250 1.2665 0.01890 0.01111 -0.0464 0.2097 1.0000
9.500 1.2779 0.01950 0.01165 -0.0438 0.1902 1.0000
9.750 1.2862 0.02029 0.01234 -0.0409 0.1674 1.0000
10.000 1.2941 0.02118 0.01315 -0.0381 0.1484 1.0000
10.250 1.3011 0.02216 0.01407 -0.0353 0.1297 1.0000
10.500 1.3072 0.02324 0.01508 -0.0326 0.1126 1.0000
10.750 1.3127 0.02438 0.01618 -0.0300 0.0961 1.0000
11.000 1.3174 0.02561 0.01736 -0.0275 0.0798 1.0000
11.250 1.3204 0.02701 0.01869 -0.0250 0.0709 1.0000
11.500 1.3234 0.02845 0.02016 -0.0227 0.0658 1.0000
11.750 1.3267 0.02995 0.02171 -0.0207 0.0625 1.0000
12.000 1.3315 0.03142 0.02329 -0.0189 0.0597 1.0000
12.250 1.3339 0.03315 0.02510 -0.0173 0.0572 1.0000
12.500 1.3338 0.03517 0.02721 -0.0157 0.0550 1.0000
12.750 1.3305 0.03760 0.02972 -0.0144 0.0529 1.0000
13.000 1.3353 0.03943 0.03169 -0.0135 0.0512 1.0000
13.250 1.3379 0.04155 0.03395 -0.0128 0.0487 1.0000
13.500 1.3372 0.04411 0.03664 -0.0123 0.0466 1.0000
13.750 1.3328 0.04721 0.03984 -0.0121 0.0446 1.0000
14.000 1.3289 0.05042 0.04315 -0.0121 0.0429 1.0000
14.250 1.3308 0.05307 0.04597 -0.0122 0.0404 1.0000
14.500 1.3287 0.05631 0.04932 -0.0126 0.0377 1.0000
14.750 1.3233 0.06009 0.05318 -0.0133 0.0357 1.0000
15.000 1.3214 0.06352 0.05677 -0.0140 0.0332 1.0000
15.250 1.3168 0.06745 0.06078 -0.0150 0.0306 1.0000
15.500 1.3111 0.07163 0.06507 -0.0162 0.0286 1.0000
15.750 1.3051 0.07594 0.06949 -0.0175 0.0270 1.0000
16.000 1.2973 0.08062 0.07424 -0.0191 0.0254 1.0000
16.250 1.2895 0.08537 0.07908 -0.0208 0.0244 1.0000
16.500 1.2820 0.09012 0.08394 -0.0224 0.0232 1.0000
16.750 1.2743 0.09498 0.08889 -0.0242 0.0223 1.0000
17.000 1.2665 0.09992 0.09392 -0.0262 0.0216 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 436 AIRFOIL (goe436-il)