GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Reynolds number: 200,000 Max Cl/Cd: 72.43 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe255-il-200000.txt Download as CSV file: xf-goe255-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 255 (MVA CA.6) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6152 0.06878 0.06454 -0.0916 1.0000 0.0313
-13.500 -0.6583 0.06318 0.05873 -0.0934 1.0000 0.0309
-13.250 -0.6916 0.06032 0.05579 -0.0924 1.0000 0.0307
-13.000 -0.7052 0.05566 0.05091 -0.0972 0.9957 0.0306
-12.750 -0.7036 0.05005 0.04498 -0.1046 0.9883 0.0307
-12.500 -0.6924 0.04546 0.04013 -0.1100 0.9826 0.0310
-12.250 -0.6758 0.04221 0.03671 -0.1133 0.9742 0.0314
-12.000 -0.6503 0.03936 0.03371 -0.1172 0.9699 0.0320
-11.750 -0.6288 0.03699 0.03116 -0.1194 0.9606 0.0327
-11.500 -0.6004 0.03475 0.02872 -0.1224 0.9560 0.0338
-11.250 -0.5823 0.03303 0.02680 -0.1228 0.9449 0.0349
-11.000 -0.5630 0.03151 0.02502 -0.1231 0.9354 0.0360
-10.750 -0.5412 0.02955 0.02306 -0.1234 0.9279 0.0373
-10.500 -0.5234 0.02833 0.02182 -0.1227 0.9176 0.0386
-10.250 -0.5017 0.02705 0.02044 -0.1225 0.9108 0.0401
-10.000 -0.4850 0.02599 0.01926 -0.1213 0.9002 0.0417
-9.750 -0.4661 0.02467 0.01787 -0.1205 0.8930 0.0437
-9.500 -0.4481 0.02369 0.01689 -0.1196 0.8840 0.0464
-9.250 -0.4265 0.02282 0.01587 -0.1190 0.8770 0.0500
-9.000 -0.4086 0.02169 0.01477 -0.1181 0.8687 0.0543
-8.750 -0.3880 0.02067 0.01368 -0.1174 0.8617 0.0610
-8.500 -0.3684 0.01966 0.01268 -0.1166 0.8536 0.0728
-8.250 -0.3474 0.01857 0.01160 -0.1161 0.8471 0.0946
-8.000 -0.3253 0.01788 0.01096 -0.1156 0.8390 0.1166
-7.750 -0.2995 0.01737 0.01041 -0.1155 0.8331 0.1368
-7.500 -0.2750 0.01705 0.01010 -0.1153 0.8252 0.1558
-7.250 -0.2483 0.01675 0.00972 -0.1152 0.8187 0.1753
-7.000 -0.2224 0.01652 0.00940 -0.1151 0.8116 0.1942
-6.750 -0.1970 0.01619 0.00909 -0.1149 0.8045 0.2139
-6.500 -0.1707 0.01592 0.00882 -0.1148 0.7984 0.2359
-6.250 -0.1454 0.01570 0.00861 -0.1146 0.7906 0.2567
-6.000 -0.1181 0.01549 0.00838 -0.1145 0.7844 0.2755
-5.750 -0.0921 0.01540 0.00834 -0.1143 0.7768 0.2937
-5.500 -0.0645 0.01539 0.00829 -0.1142 0.7698 0.3128
-5.250 -0.0367 0.01546 0.00830 -0.1141 0.7630 0.3317
-5.000 -0.0094 0.01556 0.00833 -0.1139 0.7552 0.3498
-4.750 0.0197 0.01569 0.00833 -0.1140 0.7495 0.3665
-4.500 0.0460 0.01579 0.00842 -0.1137 0.7413 0.3805
-4.250 0.0744 0.01588 0.00841 -0.1137 0.7351 0.3947
-4.000 0.1018 0.01599 0.00846 -0.1136 0.7284 0.4087
-3.750 0.1293 0.01607 0.00845 -0.1135 0.7215 0.4223
-3.500 0.1583 0.01608 0.00840 -0.1136 0.7164 0.4334
-3.250 0.1848 0.01607 0.00838 -0.1135 0.7092 0.4424
-3.000 0.2132 0.01605 0.00827 -0.1135 0.7032 0.4516
-2.750 0.2421 0.01600 0.00814 -0.1137 0.6980 0.4599
-2.500 0.2687 0.01599 0.00813 -0.1136 0.6908 0.4682
-2.250 0.2977 0.01591 0.00795 -0.1138 0.6855 0.4754
-2.000 0.3260 0.01589 0.00790 -0.1139 0.6805 0.4824
-1.750 0.3533 0.01592 0.00786 -0.1140 0.6744 0.4899
-1.500 0.3820 0.01582 0.00777 -0.1141 0.6697 0.4962
-1.250 0.4118 0.01582 0.00767 -0.1145 0.6660 0.5032
-1.000 0.4381 0.01585 0.00773 -0.1145 0.6604 0.5094
-0.750 0.4661 0.01583 0.00772 -0.1146 0.6559 0.5159
-0.500 0.4957 0.01584 0.00764 -0.1150 0.6523 0.5233
-0.250 0.5242 0.01584 0.00767 -0.1152 0.6488 0.5312
0.000 0.5506 0.01595 0.00780 -0.1152 0.6441 0.5410
0.250 0.5782 0.01594 0.00786 -0.1153 0.6402 0.5494
0.500 0.6076 0.01596 0.00782 -0.1157 0.6368 0.5581
0.750 0.6376 0.01593 0.00778 -0.1162 0.6339 0.5648
1.000 0.6629 0.01604 0.00798 -0.1160 0.6295 0.5732
1.250 0.6899 0.01606 0.00809 -0.1160 0.6255 0.5823
1.750 0.7480 0.01605 0.00813 -0.1167 0.6193 0.6066
2.000 0.7743 0.01609 0.00829 -0.1166 0.6154 0.6233
2.250 0.7993 0.01610 0.00847 -0.1163 0.6108 0.6473
2.500 0.8254 0.01600 0.00857 -0.1160 0.6071 0.6867
2.750 0.8507 0.01575 0.00858 -0.1152 0.6038 0.7646
3.000 0.8893 0.01548 0.00871 -0.1168 0.5992 0.9869
3.250 0.9166 0.01565 0.00887 -0.1171 0.5945 1.0000
3.500 0.9443 0.01577 0.00891 -0.1173 0.5905 1.0000
3.750 0.9744 0.01587 0.00890 -0.1179 0.5871 1.0000
4.000 0.9979 0.01612 0.00919 -0.1174 0.5826 1.0000
4.250 1.0225 0.01631 0.00940 -0.1170 0.5778 1.0000
4.500 1.0509 0.01641 0.00944 -0.1172 0.5734 1.0000
4.750 1.0790 0.01656 0.00954 -0.1174 0.5690 1.0000
5.000 1.1005 0.01678 0.00983 -0.1165 0.5629 1.0000
5.250 1.1285 0.01683 0.00983 -0.1166 0.5570 1.0000
5.500 1.1525 0.01700 0.01001 -0.1160 0.5506 1.0000
5.750 1.1762 0.01712 0.01014 -0.1154 0.5432 1.0000
6.000 1.2031 0.01723 0.01020 -0.1153 0.5364 1.0000
6.250 1.2231 0.01741 0.01044 -0.1140 0.5280 1.0000
6.500 1.2492 0.01753 0.01050 -0.1138 0.5203 1.0000
6.750 1.2673 0.01771 0.01076 -0.1122 0.5108 1.0000
7.000 1.2889 0.01790 0.01093 -0.1112 0.5018 1.0000
7.250 1.3081 0.01806 0.01111 -0.1098 0.4917 1.0000
7.500 1.3226 0.01832 0.01143 -0.1075 0.4802 1.0000
7.750 1.3385 0.01855 0.01167 -0.1055 0.4688 1.0000
8.000 1.3528 0.01879 0.01188 -0.1033 0.4568 1.0000
8.250 1.3587 0.01914 0.01228 -0.0996 0.4433 1.0000
8.500 1.3659 0.01959 0.01275 -0.0963 0.4292 1.0000
8.750 1.3738 0.02013 0.01329 -0.0933 0.4150 1.0000
9.000 1.3818 0.02078 0.01391 -0.0906 0.4011 1.0000
9.250 1.3896 0.02154 0.01461 -0.0879 0.3879 1.0000
9.500 1.3972 0.02241 0.01541 -0.0854 0.3761 1.0000
9.750 1.4053 0.02337 0.01627 -0.0831 0.3655 1.0000
10.000 1.4136 0.02441 0.01729 -0.0810 0.3550 1.0000
10.250 1.4234 0.02545 0.01829 -0.0792 0.3461 1.0000
10.500 1.4335 0.02652 0.01930 -0.0775 0.3374 1.0000
10.750 1.4428 0.02766 0.02046 -0.0758 0.3289 1.0000
11.000 1.4528 0.02880 0.02149 -0.0742 0.3196 1.0000
11.250 1.4578 0.03022 0.02304 -0.0724 0.3110 1.0000
11.500 1.4683 0.03138 0.02410 -0.0709 0.3029 1.0000
11.750 1.4722 0.03296 0.02585 -0.0693 0.2953 1.0000
12.000 1.4795 0.03435 0.02718 -0.0678 0.2872 1.0000
12.250 1.4814 0.03619 0.02919 -0.0663 0.2791 1.0000
12.500 1.4836 0.03803 0.03100 -0.0648 0.2703 1.0000
12.750 1.4838 0.04021 0.03335 -0.0636 0.2601 1.0000
13.000 1.4853 0.04235 0.03555 -0.0625 0.2507 1.0000
13.250 1.4851 0.04471 0.03797 -0.0614 0.2407 1.0000
13.500 1.4861 0.04711 0.04046 -0.0605 0.2288 1.0000
13.750 1.4837 0.04990 0.04328 -0.0597 0.2143 1.0000
14.000 1.4774 0.05317 0.04652 -0.0588 0.1976 1.0000
14.250 1.4688 0.05675 0.05004 -0.0580 0.1820 1.0000
14.500 1.4589 0.06057 0.05379 -0.0573 0.1683 1.0000
14.750 1.4502 0.06436 0.05753 -0.0567 0.1563 1.0000
15.000 1.4419 0.06817 0.06133 -0.0562 0.1438 1.0000
15.250 1.4359 0.07179 0.06495 -0.0558 0.1315 1.0000
15.500 1.4296 0.07554 0.06869 -0.0556 0.1178 1.0000
15.750 1.4203 0.07972 0.07283 -0.0555 0.1014 1.0000
16.000 1.4054 0.08466 0.07767 -0.0556 0.0840 1.0000
16.250 1.3889 0.08986 0.08280 -0.0558 0.0688 1.0000
16.500 1.3699 0.09553 0.08837 -0.0562 0.0441 1.0000
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Polar data table (+)
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