GOE 738 AIRFOIL (goe738-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 738 AIRFOIL (goe738-il) Reynolds number: 100,000 Max Cl/Cd: 44.46 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe738-il-100000-n5.txt Download as CSV file: xf-goe738-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 738 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.8228 0.06561 0.05940 -0.0413 1.0000 0.0580
-12.750 -0.8604 0.05907 0.05258 -0.0446 1.0000 0.0580
-12.500 -0.8824 0.05488 0.04818 -0.0452 1.0000 0.0582
-12.250 -0.8822 0.05261 0.04588 -0.0448 1.0000 0.0588
-12.000 -0.8839 0.05041 0.04359 -0.0440 1.0000 0.0594
-11.750 -0.8863 0.04829 0.04137 -0.0426 1.0000 0.0600
-11.500 -0.8887 0.04624 0.03919 -0.0408 1.0000 0.0606
-11.250 -0.8894 0.04428 0.03708 -0.0389 1.0000 0.0613
-11.000 -0.8857 0.04222 0.03483 -0.0373 1.0000 0.0621
-10.750 -0.8790 0.04018 0.03258 -0.0360 1.0000 0.0630
-10.500 -0.8697 0.03820 0.03036 -0.0348 1.0000 0.0641
-10.250 -0.8585 0.03636 0.02820 -0.0337 0.9727 0.0653
-10.000 -0.8283 0.03475 0.02646 -0.0355 0.9226 0.0668
-9.750 -0.8048 0.03367 0.02528 -0.0356 0.8976 0.0684
-9.500 -0.7861 0.03262 0.02406 -0.0346 0.8788 0.0700
-9.250 -0.7682 0.03153 0.02274 -0.0334 0.8637 0.0716
-9.000 -0.7500 0.03044 0.02138 -0.0320 0.8509 0.0734
-8.750 -0.7303 0.02942 0.02020 -0.0308 0.8390 0.0750
-8.500 -0.7099 0.02860 0.01938 -0.0299 0.8282 0.0769
-8.000 -0.6683 0.02705 0.01760 -0.0278 0.8084 0.0821
-7.750 -0.6471 0.02625 0.01665 -0.0267 0.8000 0.0846
-7.500 -0.6255 0.02552 0.01595 -0.0258 0.7905 0.0872
-7.250 -0.6041 0.02490 0.01525 -0.0247 0.7829 0.0906
-7.000 -0.5810 0.02426 0.01450 -0.0239 0.7737 0.0947
-6.750 -0.5602 0.02366 0.01392 -0.0227 0.7663 0.0984
-6.500 -0.5374 0.02313 0.01335 -0.0219 0.7579 0.1034
-6.250 -0.5153 0.02259 0.01279 -0.0209 0.7503 0.1087
-6.000 -0.4926 0.02214 0.01230 -0.0199 0.7430 0.1150
-5.750 -0.4697 0.02166 0.01183 -0.0191 0.7351 0.1223
-5.500 -0.4464 0.02127 0.01135 -0.0181 0.7289 0.1318
-5.250 -0.4228 0.02083 0.01097 -0.0174 0.7207 0.1420
-5.000 -0.3996 0.02042 0.01058 -0.0165 0.7138 0.1544
-4.750 -0.3762 0.02005 0.01020 -0.0156 0.7073 0.1684
-4.500 -0.3522 0.01970 0.00988 -0.0149 0.6997 0.1840
-4.250 -0.3286 0.01937 0.00954 -0.0140 0.6936 0.2004
-4.000 -0.3044 0.01906 0.00928 -0.0133 0.6867 0.2179
-3.750 -0.2803 0.01875 0.00902 -0.0126 0.6796 0.2369
-3.500 -0.2565 0.01844 0.00873 -0.0116 0.6740 0.2577
-3.250 -0.2321 0.01817 0.00855 -0.0110 0.6670 0.2823
-3.000 -0.2083 0.01785 0.00835 -0.0102 0.6605 0.3108
-2.750 -0.1851 0.01750 0.00811 -0.0091 0.6553 0.3475
-2.500 -0.1625 0.01715 0.00803 -0.0082 0.6480 0.3996
-2.250 -0.1406 0.01676 0.00795 -0.0069 0.6418 0.4652
-2.000 -0.1181 0.01643 0.00787 -0.0054 0.6370 0.5342
-1.750 -0.0937 0.01627 0.00794 -0.0044 0.6303 0.5946
-1.500 -0.0677 0.01615 0.00797 -0.0036 0.6240 0.6451
-1.250 -0.0402 0.01607 0.00794 -0.0028 0.6190 0.6895
-1.000 -0.0120 0.01610 0.00806 -0.0024 0.6124 0.7290
-0.750 0.0176 0.01615 0.00814 -0.0021 0.6064 0.7631
-0.500 0.0477 0.01617 0.00813 -0.0019 0.6015 0.7927
-0.250 0.0810 0.01629 0.00825 -0.0025 0.5953 0.8182
0.000 0.1152 0.01641 0.00837 -0.0032 0.5888 0.8420
0.250 0.1506 0.01652 0.00842 -0.0040 0.5838 0.8653
0.500 0.1902 0.01673 0.00861 -0.0057 0.5777 0.8874
0.750 0.2323 0.01694 0.00878 -0.0079 0.5700 0.9071
1.000 0.2735 0.01702 0.00872 -0.0097 0.5635 0.9232
1.250 0.3149 0.01717 0.00885 -0.0121 0.5526 0.9368
1.500 0.3575 0.01717 0.00872 -0.0146 0.5440 0.9472
1.750 0.3953 0.01724 0.00878 -0.0166 0.5346 0.9577
2.000 0.4313 0.01726 0.00869 -0.0181 0.5286 0.9681
2.250 0.4714 0.01735 0.00879 -0.0207 0.5201 0.9758
2.500 0.5090 0.01736 0.00874 -0.0227 0.5133 0.9839
2.750 0.5471 0.01740 0.00876 -0.0250 0.5064 0.9917
3.000 0.5861 0.01742 0.00877 -0.0275 0.4984 0.9988
3.250 0.6103 0.01742 0.00869 -0.0269 0.4926 1.0000
3.500 0.6303 0.01758 0.00891 -0.0259 0.4841 1.0000
3.750 0.6509 0.01765 0.00892 -0.0247 0.4772 1.0000
4.000 0.6713 0.01781 0.00910 -0.0235 0.4695 1.0000
4.250 0.6919 0.01795 0.00923 -0.0224 0.4619 1.0000
4.500 0.7128 0.01809 0.00933 -0.0212 0.4551 1.0000
4.750 0.7333 0.01831 0.00961 -0.0201 0.4464 1.0000
5.000 0.7547 0.01844 0.00965 -0.0189 0.4397 1.0000
5.250 0.7748 0.01872 0.01002 -0.0177 0.4299 1.0000
5.500 0.7961 0.01887 0.01009 -0.0165 0.4222 1.0000
5.750 0.8160 0.01918 0.01048 -0.0153 0.4115 1.0000
6.000 0.8369 0.01940 0.01065 -0.0141 0.4032 1.0000
6.250 0.8568 0.01973 0.01104 -0.0129 0.3931 1.0000
6.500 0.8770 0.02002 0.01132 -0.0116 0.3838 1.0000
6.750 0.8966 0.02032 0.01160 -0.0103 0.3732 1.0000
7.000 0.9151 0.02069 0.01199 -0.0090 0.3610 1.0000
7.250 0.9335 0.02104 0.01231 -0.0075 0.3495 1.0000
7.500 0.9515 0.02140 0.01262 -0.0061 0.3387 1.0000
7.750 0.9685 0.02188 0.01314 -0.0046 0.3275 1.0000
8.000 0.9855 0.02234 0.01357 -0.0030 0.3180 1.0000
8.250 1.0013 0.02283 0.01404 -0.0014 0.3080 1.0000
8.500 1.0159 0.02339 0.01461 0.0003 0.2977 1.0000
8.750 1.0295 0.02395 0.01510 0.0022 0.2883 1.0000
9.000 1.0416 0.02460 0.01578 0.0041 0.2786 1.0000
9.250 1.0529 0.02526 0.01641 0.0062 0.2702 1.0000
9.500 1.0620 0.02600 0.01717 0.0083 0.2613 1.0000
9.750 1.0700 0.02678 0.01792 0.0107 0.2539 1.0000
10.000 1.0738 0.02764 0.01883 0.0133 0.2464 1.0000
10.250 1.0793 0.02855 0.01968 0.0156 0.2400 1.0000
10.500 1.0841 0.02966 0.02089 0.0174 0.2329 1.0000
10.750 1.0891 0.03083 0.02207 0.0191 0.2259 1.0000
11.000 1.0948 0.03208 0.02335 0.0204 0.2191 1.0000
11.250 1.0989 0.03352 0.02487 0.0216 0.2118 1.0000
11.500 1.1040 0.03492 0.02624 0.0228 0.2051 1.0000
11.750 1.1066 0.03666 0.02812 0.0236 0.1973 1.0000
12.000 1.1090 0.03838 0.02982 0.0244 0.1902 1.0000
12.250 1.1099 0.04045 0.03203 0.0249 0.1816 1.0000
12.500 1.1101 0.04255 0.03415 0.0254 0.1741 1.0000
12.750 1.1091 0.04494 0.03665 0.0257 0.1654 1.0000
13.000 1.1078 0.04738 0.03912 0.0258 0.1579 1.0000
13.250 1.1052 0.05005 0.04181 0.0258 0.1503 1.0000
13.500 1.1032 0.05273 0.04451 0.0257 0.1438 1.0000
13.750 1.1002 0.05558 0.04736 0.0255 0.1377 1.0000
14.000 1.0980 0.05845 0.05023 0.0253 0.1323 1.0000
14.250 1.0969 0.06133 0.05317 0.0249 0.1274 1.0000
14.500 1.0960 0.06416 0.05597 0.0246 0.1232 1.0000
14.750 1.0963 0.06696 0.05880 0.0242 0.1191 1.0000
15.000 1.0959 0.06995 0.06187 0.0237 0.1152 1.0000
15.250 1.0972 0.07268 0.06460 0.0233 0.1119 1.0000
15.500 1.1020 0.07487 0.06673 0.0232 0.1089 1.0000
15.750 1.1013 0.07813 0.07014 0.0224 0.1061 1.0000
16.000 1.1011 0.08130 0.07342 0.0217 0.1033 1.0000
16.250 1.1034 0.08411 0.07628 0.0211 0.1010 1.0000
16.500 1.1093 0.08632 0.07850 0.0208 0.0991 1.0000
16.750 1.1183 0.08804 0.08020 0.0209 0.0972 1.0000
17.000 1.1126 0.09232 0.08468 0.0194 0.0956 1.0000
17.250 1.1065 0.09673 0.08925 0.0178 0.0940 1.0000
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