GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 393 AIRFOIL (goe393-il) Reynolds number: 50,000 Max Cl/Cd: 34.68 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe393-il-50000.txt Download as CSV file: xf-goe393-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 393 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4628 0.11516 0.10842 0.0147 1.0000 0.1241
-8.250 -0.4637 0.11394 0.10728 0.0114 1.0000 0.1275
-8.000 -0.4686 0.11433 0.10779 0.0045 1.0000 0.1286
-7.750 -0.4459 0.10558 0.09900 0.0102 1.0000 0.1335
-7.500 -0.4391 0.10253 0.09599 0.0087 1.0000 0.1381
-7.250 -0.4358 0.10131 0.09483 0.0022 1.0000 0.1422
-7.000 -0.4256 0.09698 0.09056 0.0005 1.0000 0.1445
-6.750 -0.4128 0.09249 0.08609 0.0019 1.0000 0.1494
-6.500 -0.4013 0.09043 0.08405 -0.0046 1.0000 0.1563
-6.250 -0.3896 0.08594 0.07961 -0.0049 1.0000 0.1606
-6.000 -0.3745 0.08340 0.07706 -0.0093 1.0000 0.1708
-5.750 -0.3619 0.07901 0.07271 -0.0091 1.0000 0.1763
-5.500 -0.3418 0.07689 0.07053 -0.0165 1.0000 0.1872
-5.250 -0.3304 0.07224 0.06598 -0.0134 1.0000 0.1937
-5.000 -0.3121 0.06905 0.06278 -0.0170 1.0000 0.2046
-4.750 -0.2931 0.06601 0.05972 -0.0199 1.0000 0.2181
-4.500 -0.2769 0.06270 0.05645 -0.0206 1.0000 0.2338
-4.250 -0.2617 0.05952 0.05332 -0.0204 1.0000 0.2528
-4.000 -0.2441 0.05670 0.05052 -0.0221 1.0000 0.2779
-3.750 -0.2285 0.05398 0.04785 -0.0225 1.0000 0.3063
-3.500 -0.2178 0.05105 0.04505 -0.0209 1.0000 0.3369
-3.250 -0.2120 0.04836 0.04254 -0.0179 1.0000 0.3710
-3.000 -0.2140 0.04618 0.04055 -0.0140 1.0000 0.4139
-2.750 -0.2205 0.04452 0.03905 -0.0098 1.0000 0.4477
-2.500 -0.2240 0.04293 0.03754 -0.0069 1.0000 0.4855
-2.250 -0.2251 0.04090 0.03561 -0.0032 1.0000 0.5188
-2.000 -0.2211 0.03895 0.03374 -0.0006 1.0000 0.5557
-1.750 -0.1875 0.03600 0.03080 -0.0029 0.9895 0.6071
-1.500 -0.1111 0.03282 0.02740 -0.0162 0.9726 0.6198
-1.250 0.1049 0.03287 0.02453 -0.0623 0.9502 0.2299
-1.000 0.1667 0.03044 0.02161 -0.0686 0.9344 0.2100
-0.750 0.2254 0.02871 0.01918 -0.0736 0.9183 0.2014
-0.500 0.2727 0.02720 0.01741 -0.0770 0.9014 0.2165
-0.250 0.3145 0.02583 0.01587 -0.0790 0.8847 0.2346
0.000 0.3542 0.02487 0.01473 -0.0803 0.8681 0.2691
0.250 0.3904 0.02417 0.01391 -0.0808 0.8518 0.2980
0.500 0.4223 0.02377 0.01341 -0.0806 0.8357 0.3180
0.750 0.4500 0.02350 0.01321 -0.0799 0.8195 0.3412
1.000 0.4763 0.02334 0.01318 -0.0792 0.8040 0.3714
1.250 0.5012 0.02298 0.01324 -0.0783 0.7895 0.4334
1.500 0.5354 0.02235 0.01334 -0.0781 0.7748 1.0000
1.750 0.5612 0.02308 0.01372 -0.0773 0.7603 1.0000
2.000 0.5859 0.02387 0.01428 -0.0765 0.7462 1.0000
2.250 0.6101 0.02473 0.01499 -0.0760 0.7326 1.0000
2.500 0.6341 0.02568 0.01584 -0.0756 0.7199 1.0000
2.750 0.6581 0.02664 0.01673 -0.0752 0.7080 1.0000
3.000 0.6826 0.02752 0.01757 -0.0744 0.6974 1.0000
3.250 0.7062 0.02863 0.01868 -0.0743 0.6863 1.0000
3.500 0.7289 0.02996 0.02005 -0.0745 0.6753 1.0000
3.750 0.7523 0.03112 0.02123 -0.0742 0.6657 1.0000
4.000 0.7754 0.03238 0.02257 -0.0741 0.6562 1.0000
4.250 0.7959 0.03409 0.02438 -0.0746 0.6459 1.0000
4.500 0.8198 0.03519 0.02554 -0.0738 0.6373 1.0000
4.750 0.8401 0.03673 0.02719 -0.0737 0.6260 1.0000
5.000 0.8607 0.03775 0.02834 -0.0725 0.6115 1.0000
5.250 0.8829 0.03824 0.02890 -0.0702 0.5955 1.0000
5.500 0.9066 0.03826 0.02898 -0.0674 0.5789 1.0000
5.750 0.9271 0.03874 0.02957 -0.0652 0.5605 1.0000
6.000 0.9475 0.03911 0.03012 -0.0630 0.5406 1.0000
6.250 0.9717 0.03871 0.02981 -0.0599 0.5217 1.0000
6.500 0.9977 0.03793 0.02911 -0.0565 0.5035 1.0000
6.750 1.0178 0.03827 0.02967 -0.0544 0.4803 1.0000
7.000 1.0468 0.03655 0.02799 -0.0503 0.4579 1.0000
7.250 1.0701 0.03561 0.02715 -0.0469 0.4261 1.0000
7.500 1.0941 0.03459 0.02613 -0.0435 0.3880 1.0000
7.750 1.1174 0.03373 0.02515 -0.0402 0.3459 1.0000
8.000 1.1380 0.03321 0.02440 -0.0373 0.3027 1.0000
8.250 1.1554 0.03332 0.02429 -0.0350 0.2606 1.0000
8.500 1.1706 0.03418 0.02487 -0.0329 0.2209 1.0000
8.750 1.1840 0.03610 0.02638 -0.0309 0.1845 1.0000
9.000 1.1995 0.03913 0.02913 -0.0293 0.1565 1.0000
9.250 1.2157 0.04254 0.03260 -0.0279 0.1378 1.0000
9.500 1.2344 0.04614 0.03623 -0.0268 0.1257 1.0000
9.750 1.2455 0.04951 0.04007 -0.0255 0.1170 1.0000
10.000 1.2573 0.05349 0.04428 -0.0245 0.1108 1.0000
10.250 1.2589 0.05796 0.04935 -0.0232 0.1083 1.0000
10.500 1.2560 0.06265 0.05452 -0.0222 0.1066 1.0000
10.750 1.2469 0.06749 0.05977 -0.0215 0.1056 1.0000
11.000 1.2287 0.07269 0.06532 -0.0213 0.1058 1.0000
11.250 1.2008 0.07822 0.07110 -0.0218 0.1072 1.0000
11.500 1.1713 0.08488 0.07793 -0.0246 0.1090 1.0000
11.750 1.1439 0.09258 0.08574 -0.0289 0.1107 1.0000
12.000 1.1214 0.10073 0.09394 -0.0332 0.1121 1.0000
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Polar data table (+)
Polar graphs
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