GOE 628 AIRFOIL (goe628-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 628 AIRFOIL (goe628-il) Reynolds number: 100,000 Max Cl/Cd: 43.66 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe628-il-100000.txt Download as CSV file: xf-goe628-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 628 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1520 0.10095 0.09630 -0.0548 0.9664 0.1903
-8.500 -0.1355 0.09797 0.09331 -0.0588 0.9566 0.1970
-8.250 -0.1452 0.09445 0.08981 -0.0668 0.9456 0.2021
-8.000 -0.3052 0.05703 0.05195 -0.1002 0.9181 0.1279
-7.750 -0.3194 0.05015 0.04467 -0.1032 0.9043 0.1259
-7.500 -0.3035 0.04327 0.03714 -0.1091 0.8988 0.1256
-7.250 -0.3029 0.04045 0.03392 -0.1075 0.8859 0.1258
-7.000 -0.2697 0.03688 0.02975 -0.1109 0.8815 0.1264
-6.750 -0.2602 0.03537 0.02788 -0.1089 0.8700 0.1270
-6.500 -0.2223 0.03324 0.02558 -0.1113 0.8653 0.1288
-6.250 -0.1765 0.03173 0.02399 -0.1145 0.8622 0.1323
-6.000 -0.1657 0.03115 0.02328 -0.1119 0.8504 0.1344
-5.750 -0.1250 0.02965 0.02150 -0.1140 0.8459 0.1378
-5.500 -0.0806 0.02810 0.01973 -0.1166 0.8427 0.1417
-5.250 -0.0698 0.02784 0.01954 -0.1138 0.8304 0.1445
-5.000 -0.0280 0.02678 0.01838 -0.1157 0.8261 0.1519
-4.750 -0.0090 0.02638 0.01800 -0.1141 0.8162 0.1581
-4.500 0.0264 0.02551 0.01710 -0.1148 0.8098 0.1703
-4.250 0.0695 0.02448 0.01624 -0.1166 0.8056 0.1921
-4.000 0.0837 0.02450 0.01636 -0.1140 0.7933 0.2201
-3.750 0.1252 0.02441 0.01638 -0.1151 0.7878 0.2616
-3.500 0.1437 0.02485 0.01683 -0.1131 0.7764 0.2819
-3.250 0.1814 0.02474 0.01664 -0.1137 0.7701 0.3032
-3.000 0.2039 0.02495 0.01685 -0.1123 0.7603 0.3167
-2.750 0.2359 0.02490 0.01675 -0.1122 0.7526 0.3335
-2.500 0.2651 0.02492 0.01667 -0.1119 0.7448 0.3496
-2.250 0.2895 0.02500 0.01676 -0.1108 0.7351 0.3627
-2.000 0.3275 0.02465 0.01634 -0.1116 0.7294 0.3780
-1.750 0.3428 0.02487 0.01655 -0.1093 0.7175 0.3898
-1.500 0.3790 0.02454 0.01607 -0.1099 0.7110 0.4064
-1.250 0.3959 0.02468 0.01632 -0.1078 0.6995 0.4170
-1.000 0.4304 0.02424 0.01574 -0.1083 0.6923 0.4302
-0.750 0.4494 0.02433 0.01580 -0.1066 0.6811 0.4407
-0.500 0.4828 0.02386 0.01524 -0.1069 0.6733 0.4517
-0.250 0.5031 0.02394 0.01523 -0.1055 0.6619 0.4625
0.000 0.5360 0.02347 0.01472 -0.1057 0.6539 0.4736
0.250 0.5562 0.02352 0.01473 -0.1042 0.6424 0.4841
0.500 0.5896 0.02310 0.01423 -0.1046 0.6344 0.4967
0.750 0.6091 0.02312 0.01429 -0.1030 0.6223 0.5074
1.000 0.6448 0.02270 0.01370 -0.1037 0.6145 0.5220
1.250 0.6631 0.02274 0.01384 -0.1019 0.6018 0.5344
1.500 0.6937 0.02248 0.01353 -0.1019 0.5929 0.5503
1.750 0.7165 0.02242 0.01351 -0.1007 0.5816 0.5664
2.000 0.7432 0.02234 0.01345 -0.1002 0.5714 0.5865
2.250 0.7727 0.02212 0.01324 -0.1001 0.5614 0.6129
2.500 0.7958 0.02210 0.01338 -0.0991 0.5504 0.6470
2.750 0.8270 0.02143 0.01313 -0.0990 0.5418 0.7538
3.000 0.8792 0.02160 0.01338 -0.1041 0.5290 1.0000
3.250 0.9136 0.02173 0.01317 -0.1049 0.5215 1.0000
3.500 0.9294 0.02227 0.01371 -0.1029 0.5108 1.0000
3.750 0.9630 0.02241 0.01355 -0.1036 0.5038 1.0000
4.000 0.9770 0.02305 0.01424 -0.1014 0.4941 1.0000
4.250 1.0069 0.02330 0.01431 -0.1015 0.4874 1.0000
4.500 1.0252 0.02395 0.01497 -0.1000 0.4797 1.0000
4.750 1.0483 0.02439 0.01534 -0.0992 0.4725 1.0000
5.000 1.0796 0.02473 0.01547 -0.0996 0.4667 1.0000
5.250 1.0915 0.02551 0.01638 -0.0972 0.4591 1.0000
5.500 1.1175 0.02594 0.01671 -0.0968 0.4532 1.0000
5.750 1.1462 0.02646 0.01712 -0.0970 0.4483 1.0000
6.000 1.1563 0.02739 0.01820 -0.0944 0.4418 1.0000
6.250 1.1798 0.02791 0.01867 -0.0937 0.4363 1.0000
6.500 1.2159 0.02826 0.01882 -0.0949 0.4318 1.0000
6.750 1.2193 0.02943 0.02022 -0.0915 0.4260 1.0000
7.000 1.2360 0.03026 0.02111 -0.0900 0.4210 1.0000
7.250 1.2639 0.03077 0.02155 -0.0900 0.4167 1.0000
7.500 1.2892 0.03153 0.02227 -0.0898 0.4125 1.0000
7.750 1.2890 0.03291 0.02386 -0.0861 0.4072 1.0000
8.000 1.3046 0.03380 0.02481 -0.0845 0.4025 1.0000
8.250 1.3337 0.03434 0.02528 -0.0848 0.3987 1.0000
8.500 1.3571 0.03528 0.02621 -0.0844 0.3950 1.0000
8.750 1.3414 0.03729 0.02849 -0.0790 0.3903 1.0000
9.000 1.3465 0.03859 0.02990 -0.0763 0.3858 1.0000
9.250 1.3750 0.03912 0.03039 -0.0764 0.3819 1.0000
9.500 1.4203 0.03942 0.03057 -0.0789 0.3784 1.0000
9.750 1.3591 0.04304 0.03456 -0.0683 0.3745 1.0000
10.000 1.0706 0.06861 0.06070 -0.0534 0.3621 1.0000
10.250 1.2307 0.05448 0.04643 -0.0542 0.3647 1.0000
10.500 1.3973 0.04640 0.03804 -0.0637 0.3625 1.0000
10.750 0.8021 0.11982 0.11226 -0.0660 0.3416 1.0000
11.000 0.7989 0.12501 0.11749 -0.0673 0.3420 1.0000
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Polar data table (+)
Polar graphs
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