GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 591 AIRFOIL (goe591-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.33 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe591-il-1000000.txt Download as CSV file: xf-goe591-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 591 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3095 0.13383 0.13212 -0.0349 1.0000 0.0129
-12.250 -0.3056 0.13091 0.12921 -0.0354 1.0000 0.0134
-10.500 -0.5592 0.02725 0.02474 -0.1090 0.9754 0.0146
-10.250 -0.5392 0.02263 0.01963 -0.1126 0.9721 0.0152
-10.000 -0.5046 0.02218 0.01915 -0.1145 0.9704 0.0156
-9.750 -0.4768 0.02239 0.01941 -0.1144 0.9638 0.0159
-9.500 -0.4453 0.02195 0.01891 -0.1156 0.9592 0.0163
-9.250 -0.4173 0.02116 0.01802 -0.1164 0.9526 0.0168
-9.000 -0.3929 0.01998 0.01663 -0.1166 0.9435 0.0175
-8.750 -0.3678 0.01943 0.01592 -0.1164 0.9330 0.0181
-8.500 -0.3498 0.01753 0.01368 -0.1156 0.9199 0.0187
-8.250 -0.3261 0.01687 0.01293 -0.1151 0.9071 0.0192
-8.000 -0.3006 0.01667 0.01266 -0.1147 0.8934 0.0196
-7.750 -0.2759 0.01639 0.01227 -0.1142 0.8794 0.0202
-7.250 -0.2282 0.01544 0.01103 -0.1129 0.8544 0.0215
-7.000 -0.2031 0.01519 0.01064 -0.1123 0.8440 0.0222
-6.750 -0.1767 0.01528 0.01060 -0.1119 0.8345 0.0226
-6.500 -0.1577 0.01333 0.00840 -0.1107 0.8250 0.0236
-6.250 -0.1328 0.01291 0.00791 -0.1102 0.8170 0.0242
-6.000 -0.1072 0.01261 0.00754 -0.1098 0.8088 0.0250
-5.750 -0.0814 0.01231 0.00716 -0.1094 0.8012 0.0257
-5.500 -0.0555 0.01199 0.00675 -0.1089 0.7935 0.0266
-5.250 -0.0296 0.01164 0.00630 -0.1085 0.7865 0.0272
-5.000 -0.0033 0.01136 0.00593 -0.1080 0.7787 0.0277
-4.750 0.0235 0.01129 0.00577 -0.1077 0.7714 0.0280
-4.500 0.0465 0.01008 0.00446 -0.1069 0.7640 0.0292
-4.250 0.0721 0.00971 0.00403 -0.1064 0.7568 0.0300
-4.000 0.0983 0.00941 0.00369 -0.1060 0.7488 0.0306
-3.750 0.1243 0.00917 0.00339 -0.1055 0.7410 0.0314
-3.500 0.1508 0.00895 0.00313 -0.1051 0.7327 0.0323
-3.250 0.1771 0.00877 0.00289 -0.1047 0.7248 0.0331
-3.000 0.2035 0.00858 0.00265 -0.1043 0.7159 0.0337
-2.750 0.2300 0.00843 0.00244 -0.1039 0.7070 0.0342
-2.500 0.2561 0.00829 0.00224 -0.1034 0.6975 0.0347
-2.250 0.2823 0.00806 0.00195 -0.1030 0.6882 0.0363
-2.000 0.3086 0.00793 0.00178 -0.1025 0.6785 0.0382
-1.750 0.3349 0.00786 0.00166 -0.1021 0.6678 0.0402
-1.500 0.3616 0.00779 0.00155 -0.1018 0.6572 0.0422
-1.250 0.3878 0.00770 0.00147 -0.1013 0.6468 0.0508
-1.000 0.4135 0.00762 0.00143 -0.1009 0.6355 0.0794
-0.750 0.4400 0.00757 0.00139 -0.1005 0.6239 0.0943
-0.500 0.4661 0.00753 0.00137 -0.1001 0.6122 0.1138
-0.250 0.4917 0.00745 0.00137 -0.0997 0.6005 0.1580
0.000 0.5173 0.00742 0.00139 -0.0992 0.5875 0.1980
0.250 0.5426 0.00740 0.00140 -0.0987 0.5731 0.2326
0.500 0.5671 0.00728 0.00143 -0.0981 0.5585 0.3100
0.750 0.5898 0.00694 0.00150 -0.0972 0.5460 0.4855
1.000 0.6029 0.00611 0.00161 -0.0942 0.5357 0.8251
1.250 0.6577 0.00606 0.00177 -0.0999 0.5230 0.9780
1.500 0.7154 0.00623 0.00184 -0.1065 0.5105 0.9967
1.750 0.7534 0.00637 0.00189 -0.1088 0.4981 1.0000
2.000 0.7764 0.00647 0.00194 -0.1078 0.4872 1.0000
2.250 0.7991 0.00660 0.00200 -0.1067 0.4764 1.0000
2.500 0.8216 0.00673 0.00207 -0.1056 0.4672 1.0000
2.750 0.8452 0.00683 0.00214 -0.1047 0.4592 1.0000
3.000 0.8681 0.00696 0.00222 -0.1037 0.4515 1.0000
3.250 0.8919 0.00706 0.00230 -0.1028 0.4442 1.0000
3.500 0.9149 0.00721 0.00240 -0.1018 0.4369 1.0000
3.750 0.9389 0.00731 0.00249 -0.1011 0.4296 1.0000
4.000 0.9618 0.00747 0.00260 -0.1001 0.4213 1.0000
4.250 0.9858 0.00758 0.00269 -0.0993 0.4137 1.0000
4.500 1.0088 0.00774 0.00282 -0.0984 0.4062 1.0000
4.750 1.0329 0.00786 0.00293 -0.0976 0.3992 1.0000
5.000 1.0558 0.00803 0.00306 -0.0967 0.3912 1.0000
5.250 1.0798 0.00816 0.00319 -0.0960 0.3829 1.0000
5.500 1.1026 0.00835 0.00333 -0.0950 0.3709 1.0000
5.750 1.1249 0.00856 0.00349 -0.0940 0.3569 1.0000
6.000 1.1472 0.00878 0.00366 -0.0930 0.3438 1.0000
6.250 1.1692 0.00901 0.00385 -0.0920 0.3298 1.0000
6.500 1.1906 0.00928 0.00405 -0.0909 0.3131 1.0000
6.750 1.2108 0.00961 0.00428 -0.0895 0.2930 1.0000
7.250 1.2494 0.01035 0.00485 -0.0866 0.2553 1.0000
7.500 1.2681 0.01073 0.00515 -0.0851 0.2376 1.0000
7.750 1.2864 0.01112 0.00547 -0.0835 0.2213 1.0000
8.000 1.3031 0.01157 0.00583 -0.0816 0.2032 1.0000
8.250 1.3176 0.01204 0.00620 -0.0793 0.1836 1.0000
8.500 1.3248 0.01278 0.00673 -0.0758 0.1495 1.0000
8.750 1.3321 0.01354 0.00733 -0.0724 0.1235 1.0000
9.000 1.3401 0.01431 0.00796 -0.0691 0.1010 1.0000
9.250 1.3377 0.01559 0.00896 -0.0645 0.0583 1.0000
9.500 1.3323 0.01710 0.01026 -0.0595 0.0223 1.0000
9.750 1.3420 0.01790 0.01105 -0.0570 0.0170 1.0000
10.000 1.3541 0.01860 0.01179 -0.0549 0.0156 1.0000
10.250 1.3639 0.01945 0.01269 -0.0527 0.0141 1.0000
10.500 1.3752 0.02025 0.01354 -0.0507 0.0134 1.0000
10.750 1.3871 0.02103 0.01439 -0.0489 0.0129 1.0000
11.000 1.3972 0.02197 0.01538 -0.0470 0.0122 1.0000
11.250 1.4062 0.02302 0.01649 -0.0452 0.0119 1.0000
11.500 1.4137 0.02422 0.01775 -0.0433 0.0113 1.0000
11.750 1.4166 0.02581 0.01942 -0.0412 0.0108 1.0000
12.000 1.4191 0.02752 0.02123 -0.0392 0.0105 1.0000
12.250 1.4283 0.02877 0.02255 -0.0380 0.0103 1.0000
12.500 1.4349 0.03028 0.02413 -0.0366 0.0101 1.0000
12.750 1.4417 0.03183 0.02574 -0.0355 0.0097 1.0000
13.000 1.4452 0.03372 0.02771 -0.0343 0.0095 1.0000
13.250 1.4496 0.03558 0.02964 -0.0333 0.0092 1.0000
13.500 1.4513 0.03779 0.03193 -0.0323 0.0090 1.0000
13.750 1.4532 0.04005 0.03425 -0.0315 0.0087 1.0000
14.000 1.4510 0.04282 0.03710 -0.0308 0.0085 1.0000
14.250 1.4467 0.04594 0.04032 -0.0303 0.0083 1.0000
14.500 1.4360 0.04993 0.04442 -0.0299 0.0082 1.0000
14.750 1.4227 0.05439 0.04900 -0.0298 0.0080 1.0000
15.000 1.4172 0.05806 0.05278 -0.0300 0.0079 1.0000
15.250 1.4137 0.06158 0.05638 -0.0303 0.0079 1.0000
15.500 1.4143 0.06464 0.05953 -0.0306 0.0078 1.0000
15.750 1.4113 0.06823 0.06321 -0.0310 0.0077 1.0000
16.000 1.4071 0.07207 0.06713 -0.0317 0.0076 1.0000
16.250 1.4012 0.07619 0.07135 -0.0324 0.0075 1.0000
16.500 1.3961 0.08027 0.07551 -0.0333 0.0074 1.0000
16.750 1.3903 0.08453 0.07987 -0.0343 0.0073 1.0000
17.000 1.3852 0.08875 0.08417 -0.0354 0.0072 1.0000
17.250 1.3802 0.09302 0.08853 -0.0365 0.0071 1.0000
17.500 1.3740 0.09750 0.09310 -0.0378 0.0070 1.0000
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