GOE 288 AIRFOIL (goe288-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 288 AIRFOIL (goe288-il) Reynolds number: 100,000 Max Cl/Cd: 50.63 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe288-il-100000-n5.txt Download as CSV file: xf-goe288-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2896 0.08822 0.08297 -0.0693 0.9809 0.0559
-10.250 -0.4598 0.04972 0.04371 -0.1065 0.9445 0.0548
-10.000 -0.4606 0.04295 0.03635 -0.1159 0.9268 0.0552
-9.750 -0.4457 0.03925 0.03222 -0.1198 0.9133 0.0559
-9.500 -0.4197 0.03730 0.03016 -0.1218 0.9028 0.0565
-9.250 -0.3977 0.03555 0.02826 -0.1228 0.8885 0.0572
-9.000 -0.3739 0.03386 0.02641 -0.1239 0.8749 0.0580
-8.750 -0.3486 0.03224 0.02459 -0.1250 0.8623 0.0590
-8.500 -0.3239 0.03076 0.02289 -0.1256 0.8484 0.0601
-8.250 -0.2994 0.02942 0.02131 -0.1260 0.8341 0.0614
-8.000 -0.2737 0.02827 0.01999 -0.1264 0.8211 0.0630
-7.750 -0.2471 0.02739 0.01905 -0.1268 0.8087 0.0647
-7.500 -0.2217 0.02654 0.01808 -0.1269 0.7947 0.0667
-7.250 -0.1955 0.02566 0.01701 -0.1270 0.7820 0.0689
-6.750 -0.1424 0.02420 0.01539 -0.1273 0.7586 0.0737
-6.500 -0.1151 0.02353 0.01455 -0.1274 0.7488 0.0774
-6.250 -0.0880 0.02295 0.01394 -0.1277 0.7386 0.0818
-6.000 -0.0602 0.02239 0.01328 -0.1280 0.7299 0.0886
-5.750 -0.0326 0.02189 0.01269 -0.1282 0.7205 0.0975
-5.500 -0.0042 0.02141 0.01211 -0.1286 0.7128 0.1086
-5.250 0.0236 0.02101 0.01165 -0.1289 0.7040 0.1212
-5.000 0.0523 0.02066 0.01120 -0.1292 0.6972 0.1352
-4.750 0.0806 0.02037 0.01084 -0.1295 0.6903 0.1492
-4.500 0.1090 0.02010 0.01054 -0.1298 0.6834 0.1635
-4.250 0.1378 0.01986 0.01025 -0.1301 0.6775 0.1798
-4.000 0.1661 0.01968 0.01012 -0.1304 0.6709 0.1997
-3.750 0.1944 0.01958 0.01008 -0.1307 0.6645 0.2216
-3.500 0.2233 0.01953 0.01000 -0.1309 0.6593 0.2421
-3.250 0.2520 0.01951 0.00996 -0.1310 0.6535 0.2603
-3.000 0.2801 0.01952 0.00995 -0.1310 0.6462 0.2780
-2.750 0.3089 0.01955 0.00987 -0.1309 0.6394 0.2957
-2.500 0.3366 0.01962 0.00989 -0.1308 0.6312 0.3121
-2.250 0.3646 0.01967 0.00983 -0.1306 0.6231 0.3272
-2.000 0.3931 0.01974 0.00975 -0.1306 0.6162 0.3419
-1.750 0.4207 0.01984 0.00982 -0.1304 0.6090 0.3549
-1.500 0.4490 0.01991 0.00982 -0.1304 0.6033 0.3664
-1.250 0.4779 0.02000 0.00976 -0.1304 0.5984 0.3788
-1.000 0.5050 0.02009 0.00989 -0.1302 0.5920 0.3892
-0.750 0.5329 0.02016 0.00990 -0.1302 0.5861 0.4002
-0.500 0.5615 0.02022 0.00986 -0.1302 0.5811 0.4115
-0.250 0.5884 0.02031 0.00998 -0.1300 0.5749 0.4218
0.000 0.6159 0.02041 0.01003 -0.1299 0.5685 0.4346
0.250 0.6434 0.02044 0.01005 -0.1297 0.5632 0.4455
0.500 0.6708 0.02053 0.01011 -0.1296 0.5574 0.4558
0.750 0.6972 0.02059 0.01021 -0.1293 0.5508 0.4639
1.250 0.7518 0.02068 0.01023 -0.1289 0.5388 0.4803
1.500 0.7778 0.02077 0.01034 -0.1286 0.5314 0.4894
1.750 0.8049 0.02079 0.01034 -0.1284 0.5254 0.4981
2.000 0.8309 0.02091 0.01047 -0.1280 0.5186 0.5077
2.250 0.8568 0.02100 0.01061 -0.1277 0.5114 0.5175
2.500 0.8841 0.02106 0.01059 -0.1275 0.5054 0.5298
2.750 0.9085 0.02120 0.01085 -0.1269 0.4970 0.5419
3.000 0.9342 0.02126 0.01093 -0.1265 0.4896 0.5565
3.250 0.9589 0.02137 0.01110 -0.1259 0.4818 0.5747
3.500 0.9831 0.02146 0.01129 -0.1253 0.4734 0.5988
3.750 1.0073 0.02149 0.01142 -0.1246 0.4662 0.6345
4.000 1.0278 0.02144 0.01170 -0.1232 0.4577 0.7082
4.250 1.0487 0.02117 0.01164 -0.1214 0.4511 1.0000
4.500 1.0717 0.02155 0.01202 -0.1208 0.4417 1.0000
4.750 1.0961 0.02183 0.01216 -0.1202 0.4346 1.0000
5.000 1.1184 0.02224 0.01256 -0.1195 0.4256 1.0000
5.250 1.1415 0.02257 0.01278 -0.1188 0.4185 1.0000
5.500 1.1634 0.02301 0.01320 -0.1179 0.4108 1.0000
5.750 1.1854 0.02342 0.01355 -0.1171 0.4042 1.0000
6.000 1.2076 0.02385 0.01390 -0.1163 0.3985 1.0000
6.250 1.2283 0.02437 0.01443 -0.1154 0.3921 1.0000
6.500 1.2496 0.02483 0.01483 -0.1145 0.3869 1.0000
6.750 1.2710 0.02532 0.01525 -0.1136 0.3821 1.0000
7.000 1.2901 0.02592 0.01588 -0.1125 0.3766 1.0000
7.250 1.3098 0.02647 0.01641 -0.1114 0.3718 1.0000
7.500 1.3315 0.02697 0.01682 -0.1106 0.3678 1.0000
7.750 1.3499 0.02763 0.01751 -0.1095 0.3636 1.0000
8.000 1.3667 0.02831 0.01825 -0.1080 0.3597 1.0000
8.250 1.3845 0.02895 0.01891 -0.1068 0.3561 1.0000
8.500 1.4045 0.02956 0.01949 -0.1058 0.3530 1.0000
8.750 1.4290 0.03010 0.01996 -0.1055 0.3502 1.0000
9.000 1.4418 0.03100 0.02097 -0.1038 0.3469 1.0000
9.250 1.4556 0.03189 0.02195 -0.1022 0.3435 1.0000
9.500 1.4713 0.03272 0.02283 -0.1009 0.3402 1.0000
9.750 1.4893 0.03348 0.02362 -0.0998 0.3373 1.0000
10.000 1.5109 0.03415 0.02428 -0.0993 0.3348 1.0000
10.250 1.5357 0.03479 0.02489 -0.0992 0.3327 1.0000
10.500 1.5424 0.03608 0.02636 -0.0970 0.3301 1.0000
10.750 1.5506 0.03738 0.02782 -0.0952 0.3276 1.0000
11.000 1.5605 0.03865 0.02921 -0.0936 0.3251 1.0000
11.250 1.5725 0.03984 0.03049 -0.0923 0.3227 1.0000
11.500 1.5873 0.04089 0.03160 -0.0913 0.3203 1.0000
11.750 1.6072 0.04170 0.03245 -0.0907 0.3181 1.0000
12.000 1.6328 0.04230 0.03304 -0.0907 0.3162 1.0000
12.250 1.6319 0.04427 0.03520 -0.0885 0.3140 1.0000
12.500 1.6188 0.04711 0.03829 -0.0858 0.3115 1.0000
12.750 1.6062 0.05020 0.04159 -0.0836 0.3088 1.0000
13.000 1.5983 0.05312 0.04469 -0.0819 0.3060 1.0000
13.250 1.6025 0.05513 0.04680 -0.0809 0.3034 1.0000
13.500 1.6251 0.05553 0.04722 -0.0804 0.3008 1.0000
13.750 1.6668 0.05449 0.04609 -0.0807 0.2983 1.0000
14.000 1.3207 0.09936 0.09192 -0.0831 0.2825 1.0000
14.250 1.3528 0.09767 0.09028 -0.0819 0.2820 1.0000
14.500 1.3963 0.09430 0.08692 -0.0803 0.2816 1.0000
14.750 1.4536 0.08911 0.08174 -0.0785 0.2814 1.0000
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Polar data table (+)
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