GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 484 AIRFOIL (goe484-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.74 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe484-il-1000000.txt Download as CSV file: xf-goe484-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3874 0.12953 0.12777 -0.0280 1.0000 0.0135
-11.250 -0.3870 0.12648 0.12473 -0.0286 1.0000 0.0135
-11.000 -0.3861 0.12348 0.12174 -0.0288 1.0000 0.0135
-10.750 -0.3830 0.12016 0.11844 -0.0278 1.0000 0.0138
-10.500 -0.3807 0.11780 0.11609 -0.0273 1.0000 0.0139
-10.250 -0.3779 0.11584 0.11414 -0.0267 1.0000 0.0140
-10.000 -0.3760 0.11392 0.11224 -0.0259 1.0000 0.0143
-9.750 -0.3695 0.11105 0.10937 -0.0271 0.9997 0.0145
-9.500 -0.3547 0.10766 0.10598 -0.0305 0.9988 0.0152
-9.250 -0.3399 0.10373 0.10204 -0.0344 0.9975 0.0165
-9.000 -0.3276 0.09863 0.09695 -0.0418 0.9956 0.0169
-8.750 -0.3129 0.09416 0.09246 -0.0470 0.9943 0.0170
-8.500 -0.3005 0.09007 0.08837 -0.0509 0.9915 0.0170
-8.250 -0.2900 0.08523 0.08353 -0.0540 0.9891 0.0173
-8.000 -0.2713 0.08266 0.08096 -0.0564 0.9874 0.0176
-7.750 -0.2521 0.07968 0.07797 -0.0603 0.9855 0.0178
-7.500 -0.2309 0.07659 0.07488 -0.0650 0.9839 0.0184
-7.250 -0.2155 0.07339 0.07168 -0.0686 0.9783 0.0191
-7.000 -0.1810 0.06696 0.06522 -0.0828 0.9743 0.0211
-6.750 -0.1496 0.06175 0.05998 -0.0922 0.9725 0.0212
-6.500 -0.1136 0.05583 0.05400 -0.1030 0.9711 0.0212
-6.250 -0.0957 0.05053 0.04868 -0.1088 0.9644 0.0219
-6.000 -0.0670 0.04823 0.04634 -0.1128 0.9612 0.0223
-5.750 -0.0336 0.04530 0.04337 -0.1186 0.9584 0.0231
-5.500 -0.0052 0.04168 0.03968 -0.1238 0.9509 0.0242
-5.250 0.0400 0.03500 0.03277 -0.1336 0.9446 0.0264
-5.000 0.0646 0.02283 0.01998 -0.1417 0.9331 0.0274
-4.750 0.0918 0.02178 0.01887 -0.1426 0.9282 0.0278
-4.500 0.1159 0.02065 0.01765 -0.1428 0.9209 0.0284
-4.250 0.1429 0.01910 0.01593 -0.1435 0.9150 0.0294
-4.000 0.1684 0.01731 0.01392 -0.1437 0.9078 0.0310
-3.750 0.1975 0.01747 0.01390 -0.1434 0.9020 0.0331
-3.500 0.2242 0.01645 0.01264 -0.1434 0.8960 0.0332
-3.250 0.2474 0.01256 0.00831 -0.1439 0.8894 0.0351
-3.000 0.2743 0.01192 0.00762 -0.1439 0.8843 0.0362
-2.750 0.3007 0.01135 0.00698 -0.1437 0.8784 0.0376
-2.500 0.3284 0.00967 0.00491 -0.1430 0.8729 0.0313
-2.250 0.3554 0.00901 0.00414 -0.1428 0.8676 0.0310
-2.000 0.3823 0.00853 0.00357 -0.1424 0.8615 0.0310
-1.500 0.4362 0.00776 0.00269 -0.1418 0.8498 0.0308
-1.250 0.4632 0.00748 0.00237 -0.1415 0.8437 0.0309
-1.000 0.4902 0.00726 0.00213 -0.1412 0.8379 0.0314
-0.750 0.5169 0.00704 0.00188 -0.1408 0.8308 0.0315
-0.500 0.5437 0.00686 0.00167 -0.1404 0.8227 0.0318
-0.250 0.5701 0.00674 0.00150 -0.1399 0.8126 0.0324
0.000 0.5965 0.00664 0.00138 -0.1395 0.8014 0.0330
0.250 0.6220 0.00657 0.00124 -0.1388 0.7837 0.0336
0.500 0.6471 0.00651 0.00109 -0.1380 0.7611 0.0348
0.750 0.6717 0.00653 0.00101 -0.1371 0.7326 0.0362
1.000 0.6940 0.00669 0.00098 -0.1357 0.6838 0.0378
1.250 0.7165 0.00691 0.00101 -0.1345 0.6442 0.0407
1.500 0.7396 0.00700 0.00111 -0.1335 0.6114 0.1060
1.750 0.7639 0.00706 0.00125 -0.1327 0.5888 0.1726
2.000 0.7879 0.00690 0.00141 -0.1321 0.5661 0.3614
2.250 0.8101 0.00662 0.00163 -0.1312 0.5420 0.6290
2.500 0.8396 0.00614 0.00179 -0.1316 0.5138 1.0000
2.750 0.8623 0.00649 0.00192 -0.1305 0.4670 1.0000
3.000 0.8755 0.00766 0.00234 -0.1278 0.3099 1.0000
3.250 0.8842 0.00942 0.00308 -0.1246 0.0986 1.0000
3.500 0.9055 0.01003 0.00346 -0.1233 0.0491 1.0000
3.750 0.9302 0.01029 0.00370 -0.1226 0.0449 1.0000
4.000 0.9543 0.01061 0.00399 -0.1218 0.0406 1.0000
4.250 0.9784 0.01092 0.00432 -0.1210 0.0387 1.0000
4.500 1.0031 0.01116 0.00457 -0.1204 0.0379 1.0000
4.750 1.0274 0.01142 0.00484 -0.1196 0.0366 1.0000
5.000 1.0515 0.01171 0.00513 -0.1189 0.0351 1.0000
5.250 1.0751 0.01203 0.00545 -0.1181 0.0338 1.0000
5.500 1.0979 0.01243 0.00586 -0.1171 0.0323 1.0000
5.750 1.1165 0.01321 0.00672 -0.1153 0.0303 1.0000
6.000 1.1401 0.01348 0.00700 -0.1145 0.0298 1.0000
6.250 1.1635 0.01377 0.00731 -0.1137 0.0291 1.0000
6.500 1.1866 0.01408 0.00764 -0.1128 0.0280 1.0000
6.750 1.2094 0.01439 0.00795 -0.1119 0.0268 1.0000
7.000 1.2317 0.01474 0.00830 -0.1109 0.0258 1.0000
7.250 1.2523 0.01522 0.00878 -0.1097 0.0247 1.0000
7.500 1.2662 0.01630 0.00994 -0.1072 0.0232 1.0000
7.750 1.2901 0.01644 0.01011 -0.1065 0.0226 1.0000
8.000 1.3126 0.01670 0.01038 -0.1056 0.0217 1.0000
8.250 1.3341 0.01702 0.01073 -0.1045 0.0208 1.0000
8.500 1.3556 0.01732 0.01103 -0.1035 0.0199 1.0000
8.750 1.3753 0.01775 0.01145 -0.1022 0.0190 1.0000
9.000 1.3859 0.01883 0.01261 -0.0992 0.0179 1.0000
9.250 1.4058 0.01908 0.01290 -0.0979 0.0175 1.0000
9.500 1.4250 0.01936 0.01321 -0.0964 0.0167 1.0000
9.750 1.4430 0.01972 0.01360 -0.0948 0.0160 1.0000
10.000 1.4607 0.02009 0.01400 -0.0931 0.0154 1.0000
10.250 1.4770 0.02056 0.01447 -0.0913 0.0147 1.0000
10.500 1.4820 0.02193 0.01593 -0.0877 0.0139 1.0000
10.750 1.4979 0.02246 0.01653 -0.0859 0.0136 1.0000
11.000 1.5118 0.02315 0.01729 -0.0839 0.0133 1.0000
11.250 1.5267 0.02376 0.01797 -0.0821 0.0127 1.0000
11.500 1.5411 0.02438 0.01864 -0.0803 0.0123 1.0000
11.750 1.5546 0.02508 0.01939 -0.0784 0.0119 1.0000
12.000 1.5679 0.02579 0.02013 -0.0766 0.0114 1.0000
12.250 1.5759 0.02698 0.02138 -0.0741 0.0110 1.0000
12.500 1.5758 0.02901 0.02357 -0.0709 0.0105 1.0000
12.750 1.5854 0.03014 0.02480 -0.0689 0.0104 1.0000
13.000 1.5948 0.03131 0.02607 -0.0670 0.0102 1.0000
13.250 1.6030 0.03262 0.02749 -0.0651 0.0099 1.0000
13.500 1.6096 0.03410 0.02908 -0.0632 0.0097 1.0000
13.750 1.6158 0.03565 0.03073 -0.0614 0.0095 1.0000
14.000 1.6220 0.03721 0.03239 -0.0597 0.0092 1.0000
14.250 1.6271 0.03891 0.03419 -0.0582 0.0090 1.0000
14.500 1.6317 0.04071 0.03608 -0.0567 0.0088 1.0000
14.750 1.6334 0.04289 0.03837 -0.0553 0.0087 1.0000
15.000 1.6351 0.04511 0.04068 -0.0541 0.0085 1.0000
15.250 1.6327 0.04792 0.04361 -0.0530 0.0084 1.0000
15.500 1.6247 0.05156 0.04740 -0.0521 0.0082 1.0000
15.750 1.6116 0.05609 0.05212 -0.0516 0.0080 1.0000
16.000 1.5928 0.06177 0.05804 -0.0518 0.0079 1.0000
16.250 1.5780 0.06720 0.06367 -0.0526 0.0078 1.0000
16.500 1.5739 0.07126 0.06787 -0.0535 0.0078 1.0000
16.750 1.5641 0.07642 0.07319 -0.0550 0.0077 1.0000
17.000 1.5535 0.08194 0.07886 -0.0569 0.0077 1.0000
17.250 1.5404 0.08814 0.08523 -0.0594 0.0076 1.0000
17.500 1.5225 0.09557 0.09284 -0.0628 0.0076 1.0000
17.750 1.5047 0.10337 0.10080 -0.0668 0.0076 1.0000
18.000 1.4817 0.11273 0.11034 -0.0720 0.0076 1.0000
18.250 1.4555 0.12348 0.12129 -0.0785 0.0076 1.0000
18.500 1.4184 0.13768 0.13571 -0.0875 0.0077 1.0000
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