GOE 288 AIRFOIL (goe288-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 288 AIRFOIL (goe288-il) Reynolds number: 200,000 Max Cl/Cd: 70.21 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe288-il-200000.txt Download as CSV file: xf-goe288-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 288 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1973 0.11458 0.11114 -0.0507 0.9938 0.0905
-10.250 -0.4305 0.05609 0.05225 -0.0985 0.9728 0.0617
-10.000 -0.4439 0.04185 0.03726 -0.1220 0.9549 0.0608
-9.750 -0.4295 0.03673 0.03159 -0.1276 0.9426 0.0610
-9.500 -0.4055 0.03315 0.02754 -0.1312 0.9330 0.0615
-9.250 -0.3808 0.03050 0.02449 -0.1330 0.9211 0.0618
-9.000 -0.3568 0.02851 0.02214 -0.1337 0.9068 0.0622
-8.750 -0.3320 0.02662 0.02002 -0.1341 0.8925 0.0628
-8.500 -0.3065 0.02518 0.01849 -0.1340 0.8778 0.0636
-8.250 -0.2809 0.02408 0.01728 -0.1338 0.8626 0.0645
-8.000 -0.2556 0.02313 0.01618 -0.1335 0.8465 0.0656
-7.750 -0.2303 0.02229 0.01517 -0.1331 0.8297 0.0671
-7.500 -0.2044 0.02151 0.01418 -0.1329 0.8137 0.0687
-7.250 -0.1783 0.02066 0.01315 -0.1326 0.7988 0.0702
-7.000 -0.1523 0.01991 0.01237 -0.1324 0.7855 0.0720
-6.750 -0.1255 0.01934 0.01171 -0.1322 0.7726 0.0741
-6.500 -0.0983 0.01879 0.01104 -0.1321 0.7603 0.0768
-6.250 -0.0711 0.01819 0.01034 -0.1321 0.7506 0.0798
-6.000 -0.0435 0.01777 0.00991 -0.1321 0.7399 0.0843
-5.750 -0.0155 0.01733 0.00939 -0.1323 0.7317 0.0904
-5.500 0.0126 0.01689 0.00895 -0.1324 0.7223 0.0998
-5.250 0.0412 0.01648 0.00850 -0.1327 0.7148 0.1161
-5.000 0.0697 0.01608 0.00815 -0.1330 0.7067 0.1379
-4.750 0.0984 0.01585 0.00790 -0.1333 0.6997 0.1563
-4.500 0.1274 0.01570 0.00768 -0.1335 0.6934 0.1722
-4.250 0.1559 0.01551 0.00751 -0.1337 0.6855 0.1869
-4.000 0.1847 0.01537 0.00732 -0.1339 0.6783 0.2019
-3.750 0.2134 0.01526 0.00721 -0.1340 0.6709 0.2186
-3.500 0.2421 0.01516 0.00714 -0.1341 0.6635 0.2381
-3.250 0.2714 0.01522 0.00712 -0.1342 0.6572 0.2641
-3.000 0.2997 0.01529 0.00731 -0.1343 0.6499 0.2893
-2.750 0.3287 0.01544 0.00744 -0.1343 0.6436 0.3123
-2.500 0.3581 0.01564 0.00755 -0.1344 0.6385 0.3315
-2.250 0.3867 0.01578 0.00771 -0.1344 0.6327 0.3472
-2.000 0.4156 0.01589 0.00776 -0.1344 0.6269 0.3614
-1.750 0.4448 0.01604 0.00783 -0.1345 0.6219 0.3746
-1.500 0.4737 0.01617 0.00793 -0.1345 0.6172 0.3854
-1.250 0.5022 0.01627 0.00797 -0.1346 0.6113 0.3968
-1.000 0.5306 0.01627 0.00801 -0.1345 0.6057 0.4059
-0.750 0.5601 0.01638 0.00796 -0.1347 0.6007 0.4165
-0.500 0.5879 0.01640 0.00806 -0.1346 0.5952 0.4251
-0.250 0.6165 0.01648 0.00807 -0.1347 0.5894 0.4349
0.000 0.6450 0.01645 0.00806 -0.1347 0.5842 0.4433
0.250 0.6741 0.01659 0.00809 -0.1348 0.5793 0.4534
0.500 0.7012 0.01655 0.00816 -0.1346 0.5728 0.4627
0.750 0.7296 0.01658 0.00814 -0.1346 0.5667 0.4746
1.000 0.7584 0.01664 0.00815 -0.1346 0.5614 0.4850
1.250 0.7854 0.01663 0.00820 -0.1345 0.5544 0.4936
1.500 0.8133 0.01658 0.00817 -0.1344 0.5481 0.5018
1.750 0.8424 0.01667 0.00814 -0.1345 0.5425 0.5111
2.000 0.8685 0.01661 0.00822 -0.1342 0.5349 0.5193
2.250 0.8965 0.01662 0.00818 -0.1341 0.5280 0.5302
2.500 0.9235 0.01661 0.00823 -0.1339 0.5209 0.5407
2.750 0.9500 0.01658 0.00824 -0.1336 0.5123 0.5527
3.000 0.9776 0.01660 0.00822 -0.1335 0.5051 0.5671
3.250 1.0026 0.01656 0.00833 -0.1329 0.4954 0.5843
3.500 1.0295 0.01656 0.00831 -0.1327 0.4878 0.6077
3.750 1.0532 0.01648 0.00847 -0.1319 0.4775 0.6431
4.000 1.0727 0.01606 0.00847 -0.1299 0.4698 0.7962
4.250 1.0975 0.01600 0.00854 -0.1292 0.4590 1.0000
4.500 1.1236 0.01625 0.00863 -0.1289 0.4502 1.0000
4.750 1.1482 0.01648 0.00881 -0.1283 0.4402 1.0000
5.000 1.1731 0.01677 0.00900 -0.1279 0.4316 1.0000
5.250 1.1975 0.01706 0.00923 -0.1273 0.4229 1.0000
5.500 1.2223 0.01741 0.00947 -0.1269 0.4158 1.0000
5.750 1.2462 0.01775 0.00980 -0.1263 0.4083 1.0000
6.000 1.2713 0.01813 0.01005 -0.1259 0.4024 1.0000
6.250 1.2950 0.01854 0.01047 -0.1254 0.3962 1.0000
6.500 1.3188 0.01892 0.01083 -0.1248 0.3905 1.0000
6.750 1.3440 0.01936 0.01115 -0.1245 0.3856 1.0000
7.000 1.3672 0.01982 0.01163 -0.1239 0.3806 1.0000
7.250 1.3902 0.02025 0.01208 -0.1232 0.3758 1.0000
7.500 1.4143 0.02070 0.01249 -0.1228 0.3717 1.0000
7.750 1.4419 0.02126 0.01292 -0.1230 0.3679 1.0000
8.000 1.4632 0.02176 0.01352 -0.1221 0.3644 1.0000
8.250 1.4853 0.02227 0.01409 -0.1214 0.3608 1.0000
8.500 1.5086 0.02277 0.01462 -0.1209 0.3575 1.0000
8.750 1.5332 0.02330 0.01512 -0.1206 0.3544 1.0000
9.000 1.5627 0.02395 0.01567 -0.1212 0.3512 1.0000
9.250 1.5815 0.02455 0.01639 -0.1200 0.3484 1.0000
9.500 1.6007 0.02514 0.01709 -0.1189 0.3454 1.0000
9.750 1.6218 0.02575 0.01777 -0.1181 0.3426 1.0000
10.000 1.6445 0.02635 0.01841 -0.1176 0.3401 1.0000
10.250 1.6693 0.02695 0.01901 -0.1174 0.3376 1.0000
10.500 1.6997 0.02768 0.01966 -0.1183 0.3347 1.0000
10.750 1.7152 0.02843 0.02056 -0.1167 0.3321 1.0000
11.000 1.7273 0.02916 0.02144 -0.1146 0.3293 1.0000
11.250 1.7420 0.02987 0.02226 -0.1129 0.3265 1.0000
11.500 1.7592 0.03051 0.02297 -0.1116 0.3237 1.0000
11.750 1.7822 0.03108 0.02353 -0.1112 0.3208 1.0000
12.000 1.8170 0.03182 0.02420 -0.1129 0.3177 1.0000
12.250 1.8259 0.03276 0.02530 -0.1104 0.3157 1.0000
12.500 1.8271 0.03373 0.02646 -0.1068 0.3136 1.0000
12.750 1.8313 0.03476 0.02765 -0.1039 0.3113 1.0000
13.000 1.8386 0.03572 0.02873 -0.1016 0.3086 1.0000
13.250 1.8534 0.03634 0.02938 -0.1002 0.3053 1.0000
13.500 1.8963 0.03651 0.02936 -0.1025 0.3003 1.0000
13.750 1.8803 0.03798 0.03109 -0.0974 0.2981 1.0000
14.000 1.8684 0.03965 0.03297 -0.0933 0.2951 1.0000
14.250 1.8664 0.04108 0.03453 -0.0907 0.2918 1.0000
14.500 1.8784 0.04179 0.03526 -0.0894 0.2881 1.0000
14.750 1.9102 0.04175 0.03510 -0.0898 0.2834 1.0000
15.000 1.8874 0.04442 0.03804 -0.0859 0.2810 1.0000
15.250 1.8704 0.04713 0.04097 -0.0831 0.2777 1.0000
15.500 1.8660 0.04905 0.04299 -0.0813 0.2736 1.0000
15.750 1.8920 0.04863 0.04241 -0.0810 0.2681 1.0000
16.000 1.8690 0.05234 0.04637 -0.0789 0.2650 1.0000
16.250 1.8463 0.05639 0.05065 -0.0773 0.2615 1.0000
16.500 1.8394 0.05921 0.05359 -0.0765 0.2575 1.0000
16.750 1.8521 0.06008 0.05444 -0.0760 0.2535 1.0000
17.000 1.8426 0.06347 0.05797 -0.0755 0.2499 1.0000
17.250 1.8123 0.06946 0.06423 -0.0753 0.2463 1.0000
17.500 1.7989 0.07371 0.06861 -0.0754 0.2420 1.0000
17.750 1.8181 0.07387 0.06870 -0.0751 0.2371 1.0000
18.000 1.7803 0.08155 0.07666 -0.0760 0.2332 1.0000
18.250 1.7447 0.08926 0.08460 -0.0773 0.2285 1.0000
18.500 1.7594 0.09014 0.08543 -0.0773 0.2228 1.0000
18.750 1.7121 0.09993 0.09549 -0.0795 0.2181 1.0000
19.000 1.6606 0.11075 0.10653 -0.0825 0.2122 1.0000
19.250 1.6652 0.11327 0.10906 -0.0832 0.2055 1.0000
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