GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 375 AIRFOIL (goe375-il) Reynolds number: 200,000 Max Cl/Cd: 67.47 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe375-il-200000-n5.txt Download as CSV file: xf-goe375-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 375 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3111 0.09110 0.08782 -0.0163 1.0000 0.0159
-7.250 -0.3112 0.08895 0.08574 -0.0163 1.0000 0.0160
-7.000 -0.3084 0.08659 0.08343 -0.0174 1.0000 0.0162
-6.750 -0.3030 0.08403 0.08093 -0.0194 1.0000 0.0163
-6.500 -0.2964 0.08146 0.07840 -0.0213 1.0000 0.0163
-6.250 -0.2892 0.07886 0.07583 -0.0232 1.0000 0.0164
-6.000 -0.2799 0.07615 0.07314 -0.0253 0.9995 0.0164
-5.750 -0.2404 0.07132 0.06822 -0.0347 0.9902 0.0165
-5.500 -0.2035 0.06670 0.06351 -0.0423 0.9802 0.0166
-5.250 -0.1698 0.06239 0.05908 -0.0481 0.9701 0.0166
-5.000 -0.1446 0.05760 0.05426 -0.0516 0.9607 0.0167
-4.750 -0.1231 0.05352 0.05019 -0.0539 0.9522 0.0172
-4.500 -0.0939 0.05015 0.04675 -0.0576 0.9407 0.0189
-4.250 -0.0564 0.04669 0.04312 -0.0622 0.9293 0.0206
-4.000 -0.0141 0.04355 0.03971 -0.0666 0.9177 0.0212
-3.750 0.0234 0.04047 0.03637 -0.0696 0.9059 0.0214
-3.500 0.0577 0.03748 0.03310 -0.0716 0.8933 0.0215
-3.250 0.0890 0.03466 0.03001 -0.0729 0.8800 0.0215
-3.000 0.1189 0.03187 0.02690 -0.0735 0.8659 0.0218
-2.750 0.1385 0.02888 0.02394 -0.0744 0.8482 0.0233
-2.500 0.1653 0.02699 0.02175 -0.0741 0.8282 0.0247
-2.250 0.1971 0.02632 0.02054 -0.0729 0.8087 0.0275
-1.750 0.2463 0.02199 0.01571 -0.0718 0.7753 0.0292
-1.500 0.2714 0.02060 0.01412 -0.0712 0.7582 0.0313
-1.250 0.3008 0.02131 0.01424 -0.0697 0.7381 0.0356
-1.000 0.3230 0.01834 0.01127 -0.0696 0.7164 0.0399
-0.750 0.3482 0.01739 0.01004 -0.0689 0.6902 0.0500
-0.250 0.3991 0.01621 0.00819 -0.0668 0.6234 0.0566
0.250 0.4499 0.01497 0.00631 -0.0644 0.5565 0.0423
0.500 0.4751 0.01452 0.00564 -0.0636 0.5301 0.0407
0.750 0.5001 0.01428 0.00521 -0.0628 0.5067 0.0420
1.000 0.5252 0.01410 0.00487 -0.0621 0.4841 0.0432
1.250 0.5500 0.01386 0.00451 -0.0614 0.4635 0.0420
1.500 0.5750 0.01367 0.00424 -0.0607 0.4442 0.0412
1.750 0.5999 0.01355 0.00404 -0.0600 0.4254 0.0408
2.000 0.6245 0.01349 0.00389 -0.0593 0.4062 0.0409
2.250 0.6491 0.01346 0.00379 -0.0587 0.3853 0.0411
2.500 0.6736 0.01350 0.00372 -0.0581 0.3640 0.0419
2.750 0.6982 0.01362 0.00371 -0.0575 0.3436 0.0448
3.000 0.7232 0.01374 0.00373 -0.0569 0.3252 0.0455
3.250 0.7480 0.01389 0.00376 -0.0564 0.3087 0.0455
3.500 0.7730 0.01406 0.00383 -0.0558 0.2944 0.0456
4.250 0.8478 0.01468 0.00425 -0.0543 0.2618 0.0475
4.500 0.8726 0.01492 0.00445 -0.0538 0.2533 0.0494
4.750 0.8975 0.01517 0.00470 -0.0533 0.2450 0.0543
5.000 0.9365 0.01400 0.00515 -0.0562 0.2359 1.0000
5.250 0.9607 0.01434 0.00542 -0.0556 0.2281 1.0000
5.500 0.9850 0.01465 0.00575 -0.0551 0.2211 1.0000
5.750 1.0091 0.01499 0.00607 -0.0545 0.2141 1.0000
6.000 1.0331 0.01534 0.00642 -0.0539 0.2082 1.0000
6.250 1.0572 0.01567 0.00678 -0.0533 0.2020 1.0000
6.500 1.0804 0.01609 0.00720 -0.0527 0.1965 1.0000
6.750 1.1046 0.01642 0.00762 -0.0521 0.1909 1.0000
7.000 1.1280 0.01681 0.00805 -0.0515 0.1855 1.0000
7.250 1.1509 0.01726 0.00852 -0.0508 0.1808 1.0000
7.500 1.1745 0.01764 0.00904 -0.0501 0.1758 1.0000
7.750 1.1971 0.01807 0.00951 -0.0494 0.1701 1.0000
8.000 1.2201 0.01840 0.00992 -0.0488 0.1604 1.0000
8.250 1.2424 0.01878 0.01032 -0.0481 0.1494 1.0000
8.500 1.2640 0.01925 0.01082 -0.0474 0.1394 1.0000
8.750 1.2857 0.01971 0.01133 -0.0466 0.1282 1.0000
9.000 1.3057 0.02033 0.01191 -0.0458 0.1108 1.0000
9.500 1.3242 0.02401 0.01493 -0.0417 0.0177 1.0000
9.750 1.3396 0.02506 0.01621 -0.0401 0.0149 1.0000
10.000 1.3527 0.02629 0.01764 -0.0382 0.0131 1.0000
10.250 1.3625 0.02773 0.01931 -0.0361 0.0116 1.0000
10.500 1.3686 0.02932 0.02115 -0.0336 0.0104 1.0000
10.750 1.3743 0.03062 0.02266 -0.0309 0.0098 1.0000
11.000 1.3765 0.03214 0.02438 -0.0282 0.0095 1.0000
11.250 1.3756 0.03392 0.02636 -0.0255 0.0091 1.0000
11.500 1.3726 0.03600 0.02864 -0.0234 0.0088 1.0000
11.750 1.3666 0.03855 0.03138 -0.0217 0.0086 1.0000
12.000 1.3593 0.04154 0.03455 -0.0208 0.0084 1.0000
12.250 1.3506 0.04503 0.03822 -0.0207 0.0083 1.0000
12.500 1.3393 0.04927 0.04266 -0.0214 0.0081 1.0000
12.750 1.3278 0.05404 0.04762 -0.0230 0.0081 1.0000
13.000 1.3144 0.05964 0.05339 -0.0254 0.0079 1.0000
13.250 1.3001 0.06576 0.05967 -0.0283 0.0079 1.0000
13.500 1.2846 0.07231 0.06637 -0.0315 0.0077 1.0000
13.750 1.2696 0.07881 0.07302 -0.0345 0.0077 1.0000
14.000 1.2549 0.08533 0.07967 -0.0374 0.0077 1.0000
14.250 1.2409 0.09177 0.08624 -0.0404 0.0077 1.0000
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Polar data table (+)
Polar graphs
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