GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 484 AIRFOIL (goe484-il) Reynolds number: 500,000 Max Cl/Cd: 93.42 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe484-il-500000-n5.txt Download as CSV file: xf-goe484-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 484 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3831 0.13139 0.12888 -0.0290 1.0000 0.0099
-11.500 -0.3821 0.12770 0.12520 -0.0295 1.0000 0.0105
-11.250 -0.3839 0.12331 0.12084 -0.0303 1.0000 0.0109
-11.000 -0.3788 0.12150 0.11904 -0.0301 1.0000 0.0110
-10.750 -0.3764 0.11896 0.11651 -0.0301 1.0000 0.0111
-10.500 -0.3739 0.11664 0.11421 -0.0299 1.0000 0.0112
-10.250 -0.3714 0.11451 0.11210 -0.0295 1.0000 0.0116
-10.000 -0.3632 0.11114 0.10873 -0.0315 0.9993 0.0117
-9.750 -0.3508 0.10765 0.10525 -0.0345 0.9981 0.0123
-9.500 -0.3394 0.10367 0.10126 -0.0379 0.9965 0.0131
-9.250 -0.3334 0.09745 0.09504 -0.0430 0.9942 0.0139
-9.000 -0.3202 0.09470 0.09228 -0.0454 0.9920 0.0141
-8.750 -0.3052 0.09219 0.08977 -0.0479 0.9898 0.0144
-8.500 -0.2906 0.08883 0.08640 -0.0515 0.9875 0.0146
-8.250 -0.2742 0.08586 0.08343 -0.0550 0.9850 0.0153
-8.000 -0.2614 0.08229 0.07986 -0.0586 0.9801 0.0161
-7.750 -0.2473 0.07760 0.07516 -0.0643 0.9757 0.0169
-7.500 -0.2332 0.07062 0.06817 -0.0740 0.9682 0.0177
-7.250 -0.2123 0.06854 0.06608 -0.0768 0.9644 0.0180
-7.000 -0.1908 0.06564 0.06316 -0.0811 0.9595 0.0184
-6.750 -0.1632 0.06278 0.06028 -0.0866 0.9569 0.0194
-6.500 -0.1385 0.05846 0.05592 -0.0936 0.9504 0.0202
-6.250 -0.1055 0.05274 0.05012 -0.1039 0.9456 0.0208
-6.000 -0.0661 0.04189 0.03906 -0.1205 0.9362 0.0223
-5.750 -0.0369 0.03977 0.03687 -0.1242 0.9325 0.0229
-5.500 -0.0110 0.03718 0.03420 -0.1272 0.9250 0.0233
-5.250 0.0236 0.03163 0.02840 -0.1338 0.9193 0.0236
-5.000 0.0523 0.02564 0.02206 -0.1381 0.9115 0.0239
-4.750 0.0819 0.02030 0.01620 -0.1413 0.9059 0.0247
-4.500 0.1081 0.01742 0.01286 -0.1421 0.8992 0.0251
-4.250 0.1357 0.01570 0.01080 -0.1427 0.8933 0.0254
-4.000 0.1631 0.01452 0.00936 -0.1429 0.8875 0.0258
-3.750 0.1902 0.01359 0.00820 -0.1429 0.8807 0.0261
-3.250 0.2450 0.01216 0.00642 -0.1429 0.8691 0.0265
-3.000 0.2725 0.01161 0.00573 -0.1428 0.8635 0.0268
-2.750 0.3003 0.01123 0.00524 -0.1427 0.8585 0.0273
-2.500 0.3272 0.01085 0.00477 -0.1425 0.8526 0.0275
-2.250 0.3546 0.01042 0.00425 -0.1423 0.8469 0.0277
-2.000 0.3818 0.01005 0.00381 -0.1421 0.8411 0.0278
-1.750 0.4088 0.00974 0.00345 -0.1418 0.8345 0.0279
-1.500 0.4361 0.00944 0.00310 -0.1416 0.8284 0.0281
-1.250 0.4625 0.00898 0.00261 -0.1413 0.8217 0.0287
-1.000 0.4895 0.00869 0.00229 -0.1410 0.8152 0.0294
-0.750 0.5163 0.00849 0.00209 -0.1407 0.8082 0.0300
-0.500 0.5432 0.00835 0.00193 -0.1404 0.8006 0.0306
-0.250 0.5699 0.00823 0.00182 -0.1401 0.7924 0.0312
0.000 0.5967 0.00816 0.00171 -0.1397 0.7829 0.0318
0.250 0.6227 0.00810 0.00163 -0.1392 0.7683 0.0330
0.500 0.6473 0.00810 0.00154 -0.1383 0.7399 0.0341
0.750 0.6696 0.00823 0.00146 -0.1369 0.6903 0.0348
1.000 0.6909 0.00849 0.00145 -0.1353 0.6443 0.0354
1.500 0.7374 0.00890 0.00158 -0.1332 0.5872 0.0401
1.750 0.7616 0.00895 0.00169 -0.1324 0.5642 0.0913
2.000 0.7861 0.00903 0.00183 -0.1317 0.5437 0.1411
2.250 0.8102 0.00916 0.00196 -0.1310 0.5207 0.1788
2.500 0.8324 0.00891 0.00222 -0.1302 0.4875 0.4623
3.000 0.8677 0.00976 0.00304 -0.1268 0.2639 1.0000
3.250 0.8875 0.01048 0.00340 -0.1254 0.1926 1.0000
3.500 0.9018 0.01177 0.00403 -0.1231 0.0580 1.0000
3.750 0.9257 0.01210 0.00430 -0.1224 0.0486 1.0000
4.000 0.9502 0.01235 0.00455 -0.1217 0.0457 1.0000
4.250 0.9743 0.01264 0.00483 -0.1209 0.0433 1.0000
4.500 0.9980 0.01296 0.00514 -0.1201 0.0412 1.0000
4.750 1.0212 0.01332 0.00551 -0.1192 0.0392 1.0000
5.000 1.0438 0.01374 0.00595 -0.1182 0.0372 1.0000
5.250 1.0671 0.01405 0.00629 -0.1173 0.0366 1.0000
5.500 1.0900 0.01441 0.00669 -0.1164 0.0358 1.0000
5.750 1.1125 0.01479 0.00710 -0.1154 0.0349 1.0000
6.000 1.1347 0.01517 0.00751 -0.1143 0.0338 1.0000
6.250 1.1565 0.01558 0.00795 -0.1133 0.0327 1.0000
6.500 1.1780 0.01600 0.00840 -0.1121 0.0315 1.0000
6.750 1.1987 0.01647 0.00888 -0.1109 0.0303 1.0000
7.000 1.2171 0.01713 0.00957 -0.1093 0.0289 1.0000
7.250 1.2357 0.01775 0.01024 -0.1077 0.0279 1.0000
7.500 1.2572 0.01808 0.01062 -0.1066 0.0271 1.0000
7.750 1.2775 0.01850 0.01110 -0.1053 0.0260 1.0000
8.000 1.2975 0.01892 0.01156 -0.1040 0.0248 1.0000
8.250 1.3171 0.01929 0.01195 -0.1027 0.0235 1.0000
8.500 1.3358 0.01968 0.01235 -0.1012 0.0223 1.0000
8.750 1.3500 0.02039 0.01308 -0.0989 0.0211 1.0000
9.000 1.3679 0.02082 0.01360 -0.0972 0.0203 1.0000
9.250 1.3852 0.02128 0.01413 -0.0956 0.0191 1.0000
9.500 1.4027 0.02173 0.01462 -0.0939 0.0179 1.0000
9.750 1.4206 0.02213 0.01504 -0.0925 0.0167 1.0000
10.000 1.4353 0.02279 0.01571 -0.0905 0.0157 1.0000
10.250 1.4492 0.02351 0.01654 -0.0884 0.0149 1.0000
10.500 1.4630 0.02426 0.01736 -0.0864 0.0140 1.0000
10.750 1.4772 0.02496 0.01813 -0.0846 0.0132 1.0000
11.000 1.4910 0.02571 0.01890 -0.0828 0.0124 1.0000
11.250 1.5015 0.02674 0.01998 -0.0806 0.0116 1.0000
11.500 1.5127 0.02772 0.02108 -0.0785 0.0111 1.0000
11.750 1.5230 0.02882 0.02230 -0.0764 0.0106 1.0000
12.000 1.5327 0.02997 0.02356 -0.0744 0.0102 1.0000
12.250 1.5422 0.03116 0.02484 -0.0724 0.0097 1.0000
12.500 1.5508 0.03246 0.02624 -0.0705 0.0094 1.0000
12.750 1.5580 0.03391 0.02778 -0.0686 0.0090 1.0000
13.000 1.5626 0.03564 0.02962 -0.0666 0.0087 1.0000
13.250 1.5664 0.03752 0.03162 -0.0646 0.0084 1.0000
13.500 1.5710 0.03937 0.03364 -0.0629 0.0082 1.0000
13.750 1.5749 0.04134 0.03576 -0.0613 0.0080 1.0000
14.000 1.5776 0.04350 0.03807 -0.0598 0.0078 1.0000
14.250 1.5795 0.04578 0.04050 -0.0585 0.0076 1.0000
14.500 1.5812 0.04817 0.04302 -0.0574 0.0074 1.0000
14.750 1.5813 0.05080 0.04580 -0.0564 0.0072 1.0000
15.000 1.5801 0.05368 0.04882 -0.0557 0.0070 1.0000
15.250 1.5794 0.05660 0.05187 -0.0553 0.0068 1.0000
15.500 1.5755 0.06010 0.05552 -0.0551 0.0067 1.0000
15.750 1.5707 0.06387 0.05943 -0.0553 0.0066 1.0000
16.000 1.5641 0.06809 0.06380 -0.0559 0.0065 1.0000
16.250 1.5551 0.07291 0.06878 -0.0570 0.0063 1.0000
16.500 1.5440 0.07828 0.07433 -0.0585 0.0063 1.0000
16.750 1.5301 0.08438 0.08060 -0.0607 0.0062 1.0000
17.000 1.5145 0.09109 0.08749 -0.0634 0.0062 1.0000
17.250 1.4976 0.09838 0.09496 -0.0667 0.0061 1.0000
17.500 1.4784 0.10652 0.10328 -0.0709 0.0061 1.0000
17.750 1.4591 0.11518 0.11212 -0.0756 0.0061 1.0000
18.000 1.4376 0.12487 0.12201 -0.0814 0.0061 1.0000
18.250 1.4146 0.13546 0.13279 -0.0879 0.0061 1.0000
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