GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Reynolds number: 100,000 Max Cl/Cd: 61.56 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe303-il-100000-n5.txt Download as CSV file: xf-goe303-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2776 0.10975 0.10499 -0.0317 1.0000 0.0521
-8.500 -0.2870 0.10853 0.10384 -0.0301 1.0000 0.0536
-8.250 -0.2931 0.10716 0.10255 -0.0329 0.9965 0.0550
-8.000 -0.2829 0.10404 0.09943 -0.0426 0.9864 0.0554
-7.750 -0.2647 0.09909 0.09450 -0.0486 0.9791 0.0558
-7.500 -0.2466 0.09452 0.08991 -0.0457 0.9773 0.0569
-7.250 -0.2263 0.09080 0.08618 -0.0479 0.9721 0.0588
-7.000 -0.2051 0.08715 0.08252 -0.0533 0.9646 0.0626
-6.750 -0.1705 0.08297 0.07819 -0.0739 0.9513 0.0662
-6.500 -0.1509 0.07806 0.07325 -0.0777 0.9439 0.0666
-6.250 -0.1341 0.07395 0.06917 -0.0765 0.9392 0.0677
-6.000 -0.1085 0.07027 0.06547 -0.0789 0.9354 0.0694
-5.750 -0.0882 0.06737 0.06253 -0.0813 0.9260 0.0730
-5.500 -0.0315 0.06274 0.05743 -0.0994 0.9184 0.0792
-5.000 0.0203 0.04991 0.04429 -0.1064 0.9045 0.0551
-4.750 0.0485 0.04600 0.04014 -0.1097 0.8948 0.0552
-4.500 0.0798 0.04273 0.03673 -0.1126 0.8889 0.0544
-4.250 0.1069 0.03967 0.03347 -0.1144 0.8793 0.0536
-4.000 0.1415 0.03617 0.02963 -0.1175 0.8729 0.0529
-3.750 0.1713 0.03297 0.02603 -0.1191 0.8629 0.0539
-3.500 0.2063 0.02989 0.02243 -0.1212 0.8564 0.0545
-3.250 0.2339 0.02775 0.01993 -0.1216 0.8457 0.0544
-3.000 0.2668 0.02565 0.01738 -0.1227 0.8383 0.0546
-2.750 0.2954 0.02407 0.01541 -0.1228 0.8277 0.0550
-2.500 0.3246 0.02283 0.01390 -0.1230 0.8179 0.0564
-2.250 0.3552 0.02202 0.01297 -0.1235 0.8092 0.0586
-2.000 0.3830 0.02121 0.01198 -0.1233 0.7979 0.0602
-1.750 0.4129 0.02032 0.01088 -0.1233 0.7884 0.0615
-1.500 0.4430 0.01953 0.00990 -0.1234 0.7789 0.0632
-1.250 0.4712 0.01892 0.00913 -0.1231 0.7681 0.0651
-1.000 0.5004 0.01835 0.00850 -0.1231 0.7588 0.0681
-0.750 0.5287 0.01800 0.00813 -0.1230 0.7487 0.0733
-0.500 0.5565 0.01766 0.00769 -0.1227 0.7384 0.0789
-0.250 0.5857 0.01725 0.00726 -0.1227 0.7297 0.0864
0.000 0.6123 0.01700 0.00701 -0.1223 0.7190 0.0998
0.250 0.6406 0.01681 0.00682 -0.1221 0.7097 0.1281
0.500 0.6690 0.01664 0.00673 -0.1221 0.7002 0.1754
0.750 0.6980 0.01473 0.00676 -0.1224 0.6896 0.9204
1.250 0.7522 0.01500 0.00650 -0.1214 0.6663 1.0000
1.500 0.7778 0.01517 0.00648 -0.1207 0.6522 1.0000
1.750 0.8033 0.01534 0.00649 -0.1201 0.6381 1.0000
2.000 0.8292 0.01553 0.00653 -0.1195 0.6257 1.0000
2.250 0.8558 0.01572 0.00658 -0.1191 0.6159 1.0000
2.500 0.8814 0.01594 0.00673 -0.1186 0.6056 1.0000
2.750 0.9073 0.01616 0.00687 -0.1181 0.5957 1.0000
3.000 0.9334 0.01638 0.00699 -0.1177 0.5860 1.0000
3.250 0.9584 0.01662 0.00720 -0.1171 0.5751 1.0000
3.500 0.9839 0.01686 0.00738 -0.1166 0.5651 1.0000
3.750 1.0091 0.01710 0.00758 -0.1160 0.5550 1.0000
4.000 1.0338 0.01737 0.00783 -0.1154 0.5443 1.0000
4.250 1.0586 0.01763 0.00806 -0.1148 0.5338 1.0000
4.500 1.0829 0.01790 0.00830 -0.1141 0.5224 1.0000
4.750 1.1065 0.01819 0.00859 -0.1133 0.5099 1.0000
5.000 1.1300 0.01849 0.00890 -0.1125 0.4974 1.0000
5.250 1.1533 0.01880 0.00920 -0.1116 0.4848 1.0000
5.500 1.1762 0.01912 0.00950 -0.1107 0.4720 1.0000
5.750 1.1985 0.01947 0.00987 -0.1097 0.4584 1.0000
6.000 1.2203 0.01984 0.01026 -0.1087 0.4441 1.0000
6.250 1.2415 0.02024 0.01066 -0.1076 0.4292 1.0000
6.500 1.2621 0.02066 0.01108 -0.1063 0.4137 1.0000
6.750 1.2821 0.02113 0.01155 -0.1050 0.3984 1.0000
7.000 1.3018 0.02163 0.01204 -0.1037 0.3838 1.0000
7.250 1.3212 0.02216 0.01258 -0.1024 0.3705 1.0000
7.500 1.3403 0.02273 0.01316 -0.1010 0.3584 1.0000
7.750 1.3589 0.02334 0.01374 -0.0996 0.3473 1.0000
8.000 1.3768 0.02396 0.01439 -0.0981 0.3358 1.0000
8.250 1.3942 0.02462 0.01507 -0.0966 0.3248 1.0000
8.500 1.4104 0.02530 0.01577 -0.0948 0.3141 1.0000
8.750 1.4249 0.02603 0.01647 -0.0929 0.3033 1.0000
9.000 1.4388 0.02675 0.01726 -0.0909 0.2921 1.0000
9.250 1.4513 0.02750 0.01804 -0.0887 0.2830 1.0000
9.500 1.4638 0.02829 0.01887 -0.0865 0.2746 1.0000
9.750 1.4772 0.02909 0.01978 -0.0846 0.2674 1.0000
10.000 1.4896 0.02994 0.02072 -0.0826 0.2602 1.0000
10.250 1.5018 0.03084 0.02169 -0.0806 0.2534 1.0000
10.500 1.5130 0.03178 0.02277 -0.0786 0.2460 1.0000
10.750 1.5235 0.03280 0.02384 -0.0766 0.2396 1.0000
11.000 1.5334 0.03385 0.02510 -0.0747 0.2322 1.0000
11.250 1.5414 0.03502 0.02631 -0.0726 0.2253 1.0000
11.500 1.5488 0.03626 0.02777 -0.0706 0.2174 1.0000
11.750 1.5536 0.03767 0.02924 -0.0684 0.2097 1.0000
12.000 1.5575 0.03921 0.03100 -0.0665 0.2002 1.0000
12.250 1.5589 0.04098 0.03288 -0.0645 0.1909 1.0000
12.500 1.5584 0.04298 0.03502 -0.0626 0.1800 1.0000
12.750 1.5573 0.04521 0.03741 -0.0611 0.1675 1.0000
13.000 1.5542 0.04776 0.04005 -0.0598 0.1542 1.0000
13.250 1.5490 0.05066 0.04300 -0.0586 0.1413 1.0000
13.500 1.5422 0.05390 0.04627 -0.0577 0.1298 1.0000
13.750 1.5339 0.05745 0.04985 -0.0570 0.1200 1.0000
14.000 1.5237 0.06141 0.05382 -0.0566 0.1120 1.0000
14.250 1.5146 0.06542 0.05791 -0.0565 0.1045 1.0000
14.500 1.5038 0.06980 0.06235 -0.0566 0.0987 1.0000
14.750 1.4942 0.07420 0.06689 -0.0569 0.0932 1.0000
15.000 1.4811 0.07920 0.07195 -0.0575 0.0891 1.0000
15.250 1.4718 0.08382 0.07673 -0.0582 0.0845 1.0000
15.500 1.4598 0.08898 0.08202 -0.0593 0.0804 1.0000
15.750 1.4454 0.09462 0.08773 -0.0607 0.0773 1.0000
16.000 1.4349 0.09984 0.09313 -0.0620 0.0733 1.0000
16.250 1.4224 0.10552 0.09895 -0.0638 0.0695 1.0000
16.500 1.4079 0.11164 0.10516 -0.0659 0.0664 1.0000
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Polar data table (+)
Polar graphs
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