GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 368 AIRFOIL (goe368-il) Reynolds number: 200,000 Max Cl/Cd: 63.92 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe368-il-200000-n5.txt Download as CSV file: xf-goe368-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3750 0.08274 0.07961 -0.0134 1.0000 0.0153
-7.000 -0.3733 0.07940 0.07633 -0.0147 1.0000 0.0145
-6.750 -0.3687 0.07579 0.07276 -0.0169 1.0000 0.0134
-6.500 -0.3631 0.07150 0.06851 -0.0200 1.0000 0.0127
-6.250 -0.3551 0.06698 0.06401 -0.0236 1.0000 0.0123
-6.000 -0.3444 0.06225 0.05928 -0.0274 1.0000 0.0121
-5.750 -0.3306 0.05784 0.05485 -0.0309 1.0000 0.0127
-5.500 -0.3146 0.05259 0.04953 -0.0349 1.0000 0.0131
-5.250 -0.2963 0.04626 0.04309 -0.0392 1.0000 0.0126
-5.000 -0.2688 0.03418 0.03059 -0.0472 0.9987 0.0119
-4.750 -0.2263 0.02530 0.02064 -0.0545 0.9894 0.0115
-4.500 -0.1880 0.02162 0.01622 -0.0575 0.9783 0.0115
-4.250 -0.1512 0.01918 0.01327 -0.0595 0.9649 0.0117
-4.000 -0.1165 0.01738 0.01111 -0.0608 0.9473 0.0121
-3.750 -0.0802 0.01590 0.00936 -0.0622 0.9263 0.0129
-3.500 -0.0418 0.01489 0.00815 -0.0641 0.8986 0.0151
-3.250 -0.0027 0.01395 0.00696 -0.0659 0.8677 0.0164
-3.000 0.0307 0.01320 0.00593 -0.0666 0.8381 0.0177
-2.750 0.0599 0.01253 0.00495 -0.0664 0.8117 0.0223
-2.500 0.0874 0.01213 0.00426 -0.0658 0.7875 0.0274
-2.250 0.1132 0.01135 0.00370 -0.0652 0.7636 0.1085
-2.000 0.1401 0.01153 0.00375 -0.0647 0.7382 0.1355
-1.750 0.1669 0.01197 0.00401 -0.0641 0.7111 0.1563
-1.500 0.1931 0.01195 0.00375 -0.0635 0.6849 0.1605
-1.250 0.2187 0.01190 0.00351 -0.0627 0.6571 0.1626
-1.000 0.2443 0.01190 0.00330 -0.0620 0.6290 0.1653
-0.750 0.2702 0.01190 0.00312 -0.0614 0.6035 0.1686
-0.500 0.2964 0.01190 0.00295 -0.0609 0.5809 0.1724
-0.250 0.3229 0.01185 0.00285 -0.0604 0.5592 0.1762
0.000 0.3493 0.01185 0.00275 -0.0600 0.5344 0.1810
0.250 0.3755 0.01189 0.00264 -0.0595 0.5046 0.1870
0.500 0.4013 0.01194 0.00259 -0.0590 0.4747 0.1932
0.750 0.4273 0.01205 0.00254 -0.0585 0.4493 0.2009
1.000 0.4533 0.01212 0.00255 -0.0581 0.4290 0.2082
1.250 0.4794 0.01223 0.00257 -0.0577 0.4119 0.2162
1.500 0.5056 0.01231 0.00262 -0.0574 0.3965 0.2249
1.750 0.5319 0.01241 0.00268 -0.0570 0.3819 0.2343
2.000 0.5581 0.01250 0.00276 -0.0567 0.3675 0.2457
2.250 0.5843 0.01259 0.00286 -0.0564 0.3529 0.2605
2.500 0.6104 0.01266 0.00298 -0.0560 0.3383 0.2867
2.750 0.6310 0.01173 0.00313 -0.0548 0.3251 0.7197
3.250 0.6931 0.01175 0.00342 -0.0558 0.2966 1.0000
3.500 0.7191 0.01199 0.00360 -0.0554 0.2841 1.0000
3.750 0.7450 0.01224 0.00382 -0.0550 0.2723 1.0000
4.000 0.7708 0.01251 0.00405 -0.0546 0.2616 1.0000
4.250 0.7964 0.01280 0.00430 -0.0542 0.2517 1.0000
4.500 0.8223 0.01307 0.00458 -0.0538 0.2431 1.0000
4.750 0.8477 0.01339 0.00490 -0.0534 0.2355 1.0000
5.000 0.8729 0.01371 0.00518 -0.0530 0.2198 1.0000
5.250 0.8981 0.01405 0.00547 -0.0526 0.2044 1.0000
5.500 0.9223 0.01449 0.00577 -0.0522 0.1798 1.0000
5.750 0.9463 0.01500 0.00614 -0.0517 0.1501 1.0000
6.000 0.9616 0.01697 0.00733 -0.0504 0.0234 1.0000
6.250 0.9849 0.01771 0.00814 -0.0496 0.0159 1.0000
6.500 1.0089 0.01829 0.00890 -0.0489 0.0145 1.0000
6.750 1.0322 0.01900 0.00981 -0.0481 0.0131 1.0000
7.000 1.0542 0.01987 0.01094 -0.0472 0.0113 1.0000
7.250 1.0745 0.02100 0.01233 -0.0462 0.0101 1.0000
7.500 1.0919 0.02244 0.01406 -0.0449 0.0095 1.0000
7.750 1.1043 0.02426 0.01610 -0.0432 0.0091 1.0000
8.000 1.1177 0.02579 0.01773 -0.0415 0.0089 1.0000
8.250 1.1330 0.02706 0.01910 -0.0400 0.0086 1.0000
8.500 1.1486 0.02824 0.02039 -0.0386 0.0079 1.0000
8.750 1.1618 0.02959 0.02184 -0.0371 0.0072 1.0000
9.000 1.1716 0.03127 0.02360 -0.0352 0.0069 1.0000
9.250 1.1807 0.03301 0.02542 -0.0333 0.0068 1.0000
9.500 1.1885 0.03484 0.02731 -0.0312 0.0066 1.0000
9.750 1.1960 0.03668 0.02923 -0.0291 0.0066 1.0000
10.000 1.2041 0.03872 0.03141 -0.0273 0.0064 1.0000
10.250 1.2129 0.04084 0.03362 -0.0256 0.0063 1.0000
10.500 1.2215 0.04315 0.03605 -0.0242 0.0063 1.0000
10.750 1.2283 0.04554 0.03860 -0.0228 0.0063 1.0000
11.000 1.2334 0.04817 0.04140 -0.0215 0.0063 1.0000
11.250 1.2344 0.05097 0.04442 -0.0205 0.0063 1.0000
11.500 1.2326 0.05400 0.04766 -0.0198 0.0064 1.0000
11.750 1.2280 0.05750 0.05141 -0.0197 0.0065 1.0000
12.000 1.2215 0.06132 0.05546 -0.0201 0.0066 1.0000
12.250 1.2134 0.06555 0.05993 -0.0212 0.0066 1.0000
12.500 1.2049 0.07003 0.06461 -0.0227 0.0066 1.0000
12.750 1.1951 0.07488 0.06966 -0.0249 0.0067 1.0000
13.000 1.1875 0.07959 0.07450 -0.0270 0.0065 1.0000
13.250 1.1744 0.08542 0.08055 -0.0302 0.0066 1.0000
13.500 1.1685 0.09026 0.08547 -0.0325 0.0063 1.0000
13.750 1.1480 0.09804 0.09354 -0.0378 0.0067 1.0000
14.000 1.1324 0.10535 0.10105 -0.0424 0.0069 1.0000
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Polar data table (+)
Polar graphs
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