GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 368 AIRFOIL (goe368-il) Reynolds number: 200,000 Max Cl/Cd: 64.35 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe368-il-200000.txt Download as CSV file: xf-goe368-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 368 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4112 0.10336 0.09994 -0.0027 1.0000 0.0386
-8.500 -0.4071 0.10020 0.09681 -0.0042 1.0000 0.0400
-8.250 -0.4082 0.09733 0.09400 -0.0074 1.0000 0.0422
-8.000 -0.3277 0.08178 0.07875 -0.0118 1.0000 0.0457
-7.750 -0.3206 0.07862 0.07560 -0.0116 1.0000 0.0474
-7.500 -0.3174 0.07537 0.07239 -0.0121 1.0000 0.0492
-7.250 -0.4052 0.08342 0.08032 -0.0138 1.0000 0.0452
-7.000 -0.3947 0.08096 0.07787 -0.0126 1.0000 0.0469
-6.750 -0.3870 0.07803 0.07497 -0.0139 1.0000 0.0491
-6.500 -0.3794 0.07459 0.07156 -0.0169 1.0000 0.0519
-6.250 -0.3613 0.06849 0.06538 -0.0318 1.0000 0.0559
-6.000 -0.3589 0.06509 0.06205 -0.0279 1.0000 0.0575
-5.750 -0.3473 0.06323 0.06023 -0.0259 1.0000 0.0602
-5.500 -0.3257 0.05715 0.05400 -0.0353 1.0000 0.0687
-5.250 -0.3158 0.05563 0.05253 -0.0318 1.0000 0.0709
-5.000 -0.2937 0.05143 0.04820 -0.0365 1.0000 0.0810
-4.750 -0.2820 0.05041 0.04727 -0.0332 1.0000 0.0854
-4.500 -0.2467 0.02753 0.02277 -0.0460 1.0000 0.0438
-4.250 -0.2271 0.02170 0.01634 -0.0458 1.0000 0.0370
-4.000 -0.2026 0.01909 0.01295 -0.0446 1.0000 0.0333
-3.750 -0.1798 0.01792 0.01149 -0.0433 1.0000 0.0325
-3.500 -0.1581 0.01654 0.00992 -0.0421 1.0000 0.0325
-3.250 -0.1218 0.01484 0.00808 -0.0437 0.9952 0.0335
-3.000 -0.0769 0.01357 0.00677 -0.0471 0.9855 0.0387
-2.750 -0.0320 0.01272 0.00575 -0.0501 0.9734 0.0426
-2.500 0.0117 0.01174 0.00467 -0.0528 0.9595 0.0544
-2.250 0.0567 0.01224 0.00544 -0.0558 0.9401 0.1554
-2.000 0.0981 0.01284 0.00593 -0.0581 0.9136 0.1767
-1.750 0.1368 0.01318 0.00624 -0.0599 0.8815 0.1946
-1.500 0.1702 0.01302 0.00581 -0.0604 0.8468 0.2002
-1.250 0.1977 0.01279 0.00530 -0.0596 0.8121 0.2026
-1.000 0.2231 0.01260 0.00498 -0.0587 0.7796 0.2059
-0.750 0.2485 0.01246 0.00468 -0.0577 0.7494 0.2094
-0.500 0.2742 0.01233 0.00438 -0.0569 0.7209 0.2132
-0.250 0.2998 0.01215 0.00406 -0.0560 0.6931 0.2174
0.000 0.3251 0.01204 0.00384 -0.0552 0.6659 0.2226
0.250 0.3508 0.01204 0.00366 -0.0544 0.6399 0.2294
0.500 0.3761 0.01193 0.00351 -0.0537 0.6149 0.2369
0.750 0.4017 0.01188 0.00338 -0.0530 0.5893 0.2462
1.000 0.4274 0.01184 0.00329 -0.0524 0.5619 0.2578
1.250 0.4529 0.01177 0.00320 -0.0518 0.5332 0.2719
1.500 0.4781 0.01170 0.00313 -0.0511 0.5042 0.2894
1.750 0.5032 0.01167 0.00309 -0.0505 0.4770 0.3147
2.000 0.5255 0.01107 0.00311 -0.0497 0.4540 0.5413
2.250 0.5624 0.01047 0.00316 -0.0509 0.4301 1.0000
2.500 0.5879 0.01077 0.00328 -0.0503 0.4103 1.0000
2.750 0.6133 0.01109 0.00345 -0.0498 0.3920 1.0000
3.000 0.6389 0.01139 0.00362 -0.0492 0.3739 1.0000
3.250 0.6645 0.01168 0.00382 -0.0487 0.3556 1.0000
3.500 0.6899 0.01199 0.00403 -0.0482 0.3381 1.0000
3.750 0.7153 0.01233 0.00428 -0.0477 0.3219 1.0000
4.000 0.7407 0.01267 0.00454 -0.0472 0.3073 1.0000
4.250 0.7662 0.01302 0.00484 -0.0467 0.2945 1.0000
4.500 0.7918 0.01340 0.00519 -0.0462 0.2838 1.0000
4.750 0.8172 0.01381 0.00556 -0.0458 0.2747 1.0000
5.000 0.8424 0.01405 0.00577 -0.0453 0.2616 1.0000
5.250 0.8676 0.01425 0.00595 -0.0449 0.2476 1.0000
5.500 0.8930 0.01452 0.00624 -0.0444 0.2379 1.0000
5.750 0.9185 0.01478 0.00656 -0.0440 0.2283 1.0000
6.000 0.9437 0.01495 0.00677 -0.0436 0.2132 1.0000
6.250 0.9688 0.01516 0.00697 -0.0432 0.1967 1.0000
6.500 0.9938 0.01545 0.00725 -0.0427 0.1803 1.0000
6.750 1.0186 0.01583 0.00757 -0.0422 0.1544 1.0000
7.000 1.0396 0.01683 0.00819 -0.0414 0.0783 1.0000
7.250 1.0560 0.01867 0.00971 -0.0400 0.0288 1.0000
7.500 1.0787 0.01950 0.01071 -0.0390 0.0261 1.0000
7.750 1.1007 0.02039 0.01184 -0.0380 0.0250 1.0000
8.000 1.1209 0.02147 0.01315 -0.0369 0.0233 1.0000
8.250 1.1389 0.02275 0.01466 -0.0357 0.0218 1.0000
8.500 1.1551 0.02411 0.01622 -0.0342 0.0213 1.0000
8.750 1.1687 0.02562 0.01791 -0.0325 0.0211 1.0000
9.000 1.1804 0.02724 0.01964 -0.0306 0.0209 1.0000
9.250 1.1917 0.02889 0.02139 -0.0286 0.0211 1.0000
9.500 1.2033 0.03056 0.02317 -0.0266 0.0214 1.0000
9.750 1.2159 0.03234 0.02505 -0.0247 0.0220 1.0000
10.000 1.2308 0.03436 0.02716 -0.0229 0.0229 1.0000
10.250 1.2474 0.03673 0.02967 -0.0214 0.0241 1.0000
10.500 1.2628 0.03921 0.03231 -0.0200 0.0244 1.0000
10.750 1.2756 0.04183 0.03512 -0.0186 0.0245 1.0000
11.000 1.3056 0.04750 0.04089 -0.0190 0.0270 1.0000
11.250 1.3100 0.04746 0.04146 -0.0154 0.0307 1.0000
11.500 1.3219 0.05194 0.04658 -0.0130 0.0403 1.0000
15.750 0.7791 0.18499 0.18213 -0.0801 0.0716 1.0000
16.000 0.7815 0.18895 0.18610 -0.0818 0.0709 1.0000
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Polar data table (+)
Polar graphs
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