GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Reynolds number: 50,000 Max Cl/Cd: 5.1 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe255-il-50000.txt Download as CSV file: xf-goe255-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3320 0.13726 0.13152 -0.0237 1.0000 0.2708
-10.000 -0.3619 0.13733 0.13172 -0.0220 1.0000 0.2736
-9.750 -0.4382 0.12350 0.11802 -0.0315 1.0000 0.1782
-9.500 -0.4277 0.12063 0.11516 -0.0290 1.0000 0.1749
-9.250 -0.4654 0.11396 0.10861 -0.0308 1.0000 0.1602
-9.000 -0.5951 0.09477 0.08968 -0.0403 1.0000 0.1329
-8.750 -0.6198 0.09020 0.08516 -0.0404 1.0000 0.1318
-8.500 -0.6485 0.08462 0.07960 -0.0411 1.0000 0.1302
-8.250 -0.6829 0.07719 0.07202 -0.0431 1.0000 0.1277
-8.000 -0.7022 0.06787 0.06222 -0.0484 0.9964 0.1268
-7.750 -0.6964 0.06005 0.05360 -0.0541 0.9900 0.1305
-7.500 -0.6696 0.05619 0.04938 -0.0579 0.9830 0.1380
-7.250 -0.6480 0.05198 0.04438 -0.0609 0.9761 0.1483
-7.000 -0.6130 0.05041 0.04279 -0.0637 0.9692 0.1653
-6.750 -0.5893 0.04934 0.04179 -0.0642 0.9615 0.1846
-6.500 -0.5557 0.04843 0.04082 -0.0665 0.9546 0.2141
-6.250 -0.5346 0.04828 0.04071 -0.0662 0.9472 0.2400
-5.750 -0.4858 0.04950 0.04205 -0.0658 0.9356 0.2903
-5.500 -0.4653 0.05081 0.04351 -0.0641 0.9308 0.3092
-5.250 -0.4333 0.05165 0.04425 -0.0649 0.9259 0.3348
-5.000 -0.4189 0.05153 0.04397 -0.0638 0.9217 0.3542
-4.750 -0.4022 0.05196 0.04438 -0.0623 0.9181 0.3724
-4.500 -0.3832 0.05225 0.04461 -0.0614 0.9156 0.3911
-4.250 -0.5178 0.04884 0.04148 -0.0381 1.0000 0.3583
-4.000 -0.5004 0.04912 0.04170 -0.0370 1.0000 0.3783
-3.750 -0.4815 0.04913 0.04157 -0.0365 1.0000 0.3992
-3.500 -0.4609 0.04899 0.04122 -0.0367 1.0000 0.4217
-3.250 -0.4434 0.04913 0.04132 -0.0357 1.0000 0.4404
-3.000 -0.4260 0.04931 0.04148 -0.0347 1.0000 0.4597
-2.750 -0.4083 0.04949 0.04162 -0.0337 1.0000 0.4800
-2.500 -0.3894 0.04962 0.04168 -0.0332 1.0000 0.5015
-2.250 -0.3679 0.04968 0.04156 -0.0335 1.0000 0.5246
-2.000 -0.3493 0.04982 0.04166 -0.0329 1.0000 0.5437
-1.750 -0.3302 0.05000 0.04180 -0.0324 1.0000 0.5633
-1.500 -0.3111 0.05024 0.04196 -0.0320 1.0000 0.5831
-1.250 -0.2914 0.05053 0.04219 -0.0318 1.0000 0.6030
-1.000 -0.2712 0.05092 0.04249 -0.0318 1.0000 0.6230
-0.750 -0.2507 0.05137 0.04286 -0.0319 1.0000 0.6421
-0.500 -0.2303 0.05190 0.04331 -0.0321 1.0000 0.6608
-0.250 -0.2102 0.05250 0.04383 -0.0322 1.0000 0.6790
0.250 -0.1681 0.05400 0.04522 -0.0329 0.9991 0.7148
0.500 -0.1307 0.05586 0.04704 -0.0362 0.9918 0.7369
0.750 -0.0879 0.05827 0.04939 -0.0406 0.9823 0.7633
1.000 -0.0603 0.05938 0.05055 -0.0421 0.9711 0.7881
1.250 -0.0375 0.06031 0.05154 -0.0427 0.9603 0.8165
1.500 -0.0160 0.06138 0.05274 -0.0427 0.9506 0.8512
1.750 0.0125 0.06273 0.05429 -0.0444 0.9385 0.9147
2.000 0.0434 0.06356 0.05505 -0.0490 0.9187 1.0000
2.250 0.0868 0.06590 0.05712 -0.0561 0.9025 1.0000
2.500 0.1264 0.06826 0.05920 -0.0617 0.8850 1.0000
2.750 0.1636 0.07073 0.06142 -0.0662 0.8673 1.0000
3.000 0.2016 0.07350 0.06397 -0.0702 0.8496 1.0000
3.250 0.2281 0.07572 0.06603 -0.0722 0.8318 1.0000
3.500 0.2437 0.07724 0.06744 -0.0724 0.8131 1.0000
3.750 0.2719 0.07978 0.06985 -0.0744 0.7981 1.0000
4.000 0.3014 0.08233 0.07227 -0.0764 0.7824 1.0000
4.500 0.4152 0.08144 0.07096 -0.0789 0.6823 1.0000
4.750 0.4171 0.08450 0.07402 -0.0788 0.6822 1.0000
5.000 0.3600 0.09017 0.07985 -0.0770 0.7353 1.0000
5.250 0.3691 0.09244 0.08208 -0.0768 0.7288 1.0000
5.500 0.3938 0.09480 0.08439 -0.0780 0.7177 1.0000
5.750 0.3984 0.09693 0.08650 -0.0773 0.7124 1.0000
6.000 0.4114 0.09890 0.08844 -0.0774 0.7035 1.0000
6.250 0.4430 0.10262 0.09211 -0.0797 0.6987 1.0000
6.500 0.4341 0.10331 0.09281 -0.0774 0.6892 1.0000
6.750 0.4725 0.10723 0.09669 -0.0802 0.6829 1.0000
7.000 0.4586 0.10798 0.09746 -0.0777 0.6758 1.0000
7.250 0.4855 0.11093 0.10040 -0.0792 0.6681 1.0000
7.500 0.4858 0.11276 0.10224 -0.0782 0.6613 1.0000
7.750 0.5091 0.11543 0.10491 -0.0793 0.6522 1.0000
8.000 0.5112 0.11742 0.10691 -0.0786 0.6451 1.0000
8.250 0.5392 0.12043 0.10994 -0.0800 0.6353 1.0000
8.500 0.5353 0.12187 0.11140 -0.0787 0.6261 1.0000
8.750 0.5760 0.12626 0.11580 -0.0813 0.6179 1.0000
9.000 0.5643 0.12668 0.11627 -0.0794 0.6066 1.0000
9.250 0.5784 0.12962 0.11923 -0.0799 0.5993 1.0000
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