GOE 434 AIRFOIL (goe434-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 434 AIRFOIL (goe434-il) Reynolds number: 100,000 Max Cl/Cd: 35.99 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe434-il-100000.txt Download as CSV file: xf-goe434-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 434 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
------ -------- --------- --------- -------- -------- --------
-10.750 0.0215 0.11822 0.11249 -0.0946 0.8944 0.2154
-10.500 0.0568 0.11426 0.10848 -0.0939 0.8855 0.2170
-10.250 -0.4067 0.04631 0.03937 -0.1384 0.8691 0.1568
-10.000 -0.4281 0.04168 0.03413 -0.1421 0.8608 0.1587
-9.750 -0.4251 0.04062 0.03303 -0.1406 0.8500 0.1607
-9.500 -0.3976 0.03990 0.03241 -0.1406 0.8444 0.1638
-9.250 -0.3767 0.03831 0.03067 -0.1415 0.8397 0.1674
-9.000 -0.3722 0.03714 0.02926 -0.1409 0.8312 0.1705
-8.750 -0.3591 0.03601 0.02798 -0.1405 0.8240 0.1739
-8.500 -0.3308 0.03549 0.02763 -0.1404 0.8197 0.1783
-8.250 -0.3061 0.03428 0.02623 -0.1413 0.8160 0.1841
-8.000 -0.2905 0.03373 0.02567 -0.1405 0.8101 0.1888
-7.750 -0.2773 0.03386 0.02594 -0.1387 0.8026 0.1936
-7.500 -0.2569 0.03303 0.02496 -0.1389 0.7975 0.2016
-7.250 -0.2283 0.03287 0.02500 -0.1389 0.7939 0.2100
-7.000 -0.1971 0.03248 0.02467 -0.1394 0.7908 0.2212
-6.750 -0.1854 0.03282 0.02501 -0.1381 0.7845 0.2320
-6.500 -0.1766 0.03371 0.02601 -0.1359 0.7772 0.2417
-6.250 -0.1512 0.03433 0.02676 -0.1351 0.7727 0.2534
-6.000 -0.1188 0.03463 0.02710 -0.1353 0.7692 0.2666
-5.750 -0.0847 0.03464 0.02701 -0.1361 0.7662 0.2806
-5.500 -0.0486 0.03550 0.02801 -0.1357 0.7637 0.2896
-5.250 -0.0760 0.03728 0.02977 -0.1305 0.7518 0.2941
-5.000 -0.0513 0.03779 0.03036 -0.1297 0.7472 0.3023
-4.750 -0.0177 0.03820 0.03079 -0.1296 0.7440 0.3117
-4.500 0.0195 0.03788 0.03040 -0.1308 0.7416 0.3224
-4.250 0.0563 0.03839 0.03098 -0.1305 0.7392 0.3303
-4.000 0.0052 0.04134 0.03402 -0.1229 0.7247 0.3308
-3.750 0.0356 0.04117 0.03367 -0.1241 0.7209 0.3432
-3.500 0.0705 0.04165 0.03433 -0.1232 0.7182 0.3500
-3.250 0.1169 0.04094 0.03339 -0.1259 0.7162 0.3648
-3.000 0.0542 0.04478 0.03738 -0.1170 0.7012 0.3626
-2.750 0.0771 0.04517 0.03781 -0.1165 0.6968 0.3702
-2.500 0.1102 0.04553 0.03828 -0.1157 0.6937 0.3783
-2.250 0.1613 0.04462 0.03717 -0.1189 0.6919 0.3931
-2.000 0.1201 0.04804 0.04065 -0.1133 0.6790 0.3939
-1.750 0.1328 0.04923 0.04196 -0.1114 0.6735 0.3993
-1.500 0.1635 0.04951 0.04224 -0.1112 0.6700 0.4089
-1.250 0.2064 0.04887 0.04149 -0.1131 0.6676 0.4206
-1.000 0.2477 0.04860 0.04131 -0.1127 0.6658 0.4288
-0.750 0.1951 0.05345 0.04622 -0.1082 0.6510 0.4288
-0.500 0.2224 0.05392 0.04663 -0.1088 0.6468 0.4378
-0.250 0.2638 0.05344 0.04601 -0.1108 0.6439 0.4465
0.000 0.3035 0.05298 0.04561 -0.1109 0.6417 0.4528
0.250 0.2662 0.05741 0.05009 -0.1077 0.6297 0.4540
0.500 0.2791 0.05880 0.05148 -0.1073 0.6246 0.4594
0.750 0.3141 0.05896 0.05152 -0.1088 0.6208 0.4678
1.000 0.3580 0.05834 0.05086 -0.1100 0.6180 0.4749
1.250 0.4028 0.05769 0.05025 -0.1103 0.6160 0.4826
1.500 0.3429 0.06377 0.05641 -0.1068 0.6030 0.4814
1.750 0.3756 0.06380 0.05642 -0.1069 0.5972 0.4903
2.000 0.4361 0.06189 0.05441 -0.1086 0.5934 0.5015
2.250 0.4819 0.06068 0.05325 -0.1084 0.5891 0.5097
2.500 0.4568 0.06397 0.05658 -0.1060 0.5735 0.5120
2.750 0.5202 0.06140 0.05388 -0.1077 0.5701 0.5213
3.000 0.5808 0.05881 0.05122 -0.1090 0.5683 0.5290
3.250 0.6366 0.05641 0.04884 -0.1094 0.5672 0.5373
3.500 0.5826 0.06293 0.05544 -0.1064 0.5487 0.5374
3.750 0.5988 0.06404 0.05655 -0.1060 0.5415 0.5436
4.000 0.6837 0.05936 0.05176 -0.1081 0.5449 0.5550
4.250 0.6486 0.06440 0.05688 -0.1058 0.5282 0.5566
4.500 0.6414 0.06724 0.05980 -0.1043 0.5164 0.5606
4.750 0.6748 0.06660 0.05916 -0.1042 0.5110 0.5702
5.000 0.7210 0.06476 0.05731 -0.1044 0.5084 0.5815
5.250 0.7694 0.06251 0.05509 -0.1043 0.5069 0.5937
5.500 0.8218 0.05981 0.05240 -0.1045 0.5059 0.6075
5.750 0.8002 0.06386 0.05654 -0.1025 0.4894 0.6123
6.000 0.8338 0.06292 0.05559 -0.1022 0.4845 0.6276
6.250 0.9004 0.05818 0.05092 -0.1020 0.4873 0.6488
6.500 0.9502 0.05497 0.04777 -0.1013 0.4869 0.6691
6.750 0.8806 0.06418 0.05712 -0.0987 0.4567 0.6678
7.000 0.9258 0.06144 0.05444 -0.0980 0.4548 0.6906
7.250 0.9731 0.05823 0.05127 -0.0971 0.4538 0.7175
7.500 0.9783 0.05953 0.05265 -0.0955 0.4415 0.7365
7.750 1.0233 0.05637 0.04954 -0.0944 0.4394 0.7717
8.000 1.0754 0.05228 0.04551 -0.0932 0.4384 0.8155
8.250 1.1289 0.04746 0.04085 -0.0913 0.4374 0.8967
8.500 1.2170 0.04179 0.03494 -0.0943 0.4354 1.0000
8.750 1.2337 0.04245 0.03549 -0.0939 0.4221 1.0000
9.000 1.3219 0.03781 0.03045 -0.0971 0.4148 1.0000
9.250 1.3213 0.03955 0.03213 -0.0951 0.3999 1.0000
9.500 1.3373 0.04030 0.03275 -0.0941 0.3871 1.0000
9.750 1.3901 0.03862 0.03070 -0.0953 0.3767 1.0000
10.000 1.3747 0.04160 0.03376 -0.0925 0.3647 1.0000
10.250 1.4057 0.04152 0.03345 -0.0924 0.3558 1.0000
10.500 1.4043 0.04370 0.03565 -0.0907 0.3465 1.0000
10.750 1.4383 0.04345 0.03516 -0.0907 0.3390 1.0000
11.000 1.4268 0.04644 0.03827 -0.0886 0.3312 1.0000
11.250 1.4619 0.04605 0.03765 -0.0887 0.3246 1.0000
11.500 1.4581 0.04864 0.04032 -0.0871 0.3185 1.0000
11.750 1.4625 0.05063 0.04234 -0.0860 0.3127 1.0000
12.000 1.5031 0.04990 0.04138 -0.0863 0.3075 1.0000
12.250 1.4952 0.05290 0.04451 -0.0847 0.3027 1.0000
12.500 1.4864 0.05604 0.04777 -0.0833 0.2976 1.0000
12.750 1.5158 0.05602 0.04762 -0.0831 0.2928 1.0000
13.000 1.5443 0.05630 0.04777 -0.0829 0.2884 1.0000
13.250 1.5086 0.06177 0.05354 -0.0809 0.2844 1.0000
13.500 1.5003 0.06509 0.05698 -0.0799 0.2799 1.0000
13.750 1.5523 0.06292 0.05454 -0.0800 0.2753 1.0000
14.000 1.5568 0.06521 0.05687 -0.0792 0.2715 1.0000
14.250 1.4868 0.07476 0.06688 -0.0779 0.2678 1.0000
14.750 1.4617 0.08340 0.07572 -0.0773 0.2602 1.0000
15.000 1.5850 0.07342 0.06520 -0.0767 0.2566 1.0000
15.250 0.9834 0.17332 0.16688 -0.1091 0.2230 1.0000
15.500 0.9506 0.18391 0.17756 -0.1155 0.2131 1.0000
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