GOE 676 (= M 12) AIRFOIL (goe676-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 676 (= M 12) AIRFOIL (goe676-il) Reynolds number: 500,000 Max Cl/Cd: 77.73 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe676-il-500000-n5.txt Download as CSV file: xf-goe676-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 676 (= M 12) 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
------ -------- --------- --------- -------- -------- --------
-15.500 -1.1612 0.05004 0.04680 -0.0502 1.0000 0.0129
-15.250 -1.1826 0.04407 0.04061 -0.0535 1.0000 0.0130
-15.000 -1.1934 0.04036 0.03673 -0.0541 1.0000 0.0132
-14.750 -1.1979 0.03769 0.03393 -0.0535 1.0000 0.0135
-14.500 -1.1978 0.03564 0.03176 -0.0524 1.0000 0.0138
-14.250 -1.1947 0.03396 0.02997 -0.0509 1.0000 0.0142
-14.000 -1.1900 0.03248 0.02836 -0.0491 1.0000 0.0147
-13.750 -1.1843 0.03112 0.02686 -0.0471 1.0000 0.0152
-13.500 -1.1768 0.02983 0.02540 -0.0450 1.0000 0.0157
-13.250 -1.1656 0.02854 0.02394 -0.0435 1.0000 0.0162
-13.000 -1.1511 0.02756 0.02288 -0.0422 1.0000 0.0167
-12.750 -1.1334 0.02684 0.02211 -0.0412 1.0000 0.0173
-12.500 -1.1148 0.02616 0.02136 -0.0403 1.0000 0.0179
-12.250 -1.0959 0.02545 0.02055 -0.0394 1.0000 0.0187
-12.000 -1.0770 0.02469 0.01966 -0.0384 1.0000 0.0195
-11.750 -1.0577 0.02390 0.01872 -0.0374 1.0000 0.0202
-11.500 -1.0385 0.02315 0.01788 -0.0365 1.0000 0.0208
-11.250 -1.0177 0.02265 0.01734 -0.0357 1.0000 0.0215
-11.000 -0.9962 0.02220 0.01684 -0.0349 1.0000 0.0221
-10.750 -0.9750 0.02172 0.01630 -0.0341 1.0000 0.0228
-10.500 -0.9540 0.02121 0.01570 -0.0331 1.0000 0.0236
-10.250 -0.9335 0.02069 0.01507 -0.0321 1.0000 0.0244
-10.000 -0.9137 0.02019 0.01446 -0.0308 1.0000 0.0250
-9.750 -0.8947 0.01965 0.01382 -0.0294 0.9998 0.0255
-9.500 -0.8645 0.01886 0.01298 -0.0306 0.9954 0.0264
-9.250 -0.8334 0.01841 0.01250 -0.0317 0.9901 0.0273
-9.000 -0.8020 0.01797 0.01200 -0.0328 0.9849 0.0281
-8.750 -0.7725 0.01751 0.01147 -0.0335 0.9790 0.0290
-8.500 -0.7423 0.01702 0.01090 -0.0343 0.9734 0.0299
-8.250 -0.7140 0.01656 0.01034 -0.0346 0.9658 0.0306
-8.000 -0.6852 0.01615 0.00983 -0.0349 0.9585 0.0311
-7.750 -0.6602 0.01543 0.00905 -0.0346 0.9490 0.0320
-7.500 -0.6350 0.01492 0.00850 -0.0342 0.9400 0.0328
-7.250 -0.6095 0.01456 0.00809 -0.0338 0.9304 0.0336
-7.000 -0.5845 0.01420 0.00768 -0.0333 0.9194 0.0344
-6.750 -0.5596 0.01383 0.00725 -0.0327 0.9086 0.0351
-6.500 -0.5347 0.01348 0.00682 -0.0321 0.8979 0.0358
-6.250 -0.5095 0.01314 0.00641 -0.0316 0.8871 0.0366
-6.000 -0.4841 0.01283 0.00601 -0.0310 0.8766 0.0373
-5.750 -0.4584 0.01256 0.00566 -0.0306 0.8665 0.0380
-5.500 -0.4330 0.01221 0.00525 -0.0301 0.8563 0.0392
-5.250 -0.4072 0.01189 0.00490 -0.0297 0.8469 0.0405
-4.750 -0.3545 0.01143 0.00434 -0.0290 0.8280 0.0432
-4.500 -0.3279 0.01123 0.00408 -0.0287 0.8189 0.0448
-4.250 -0.3010 0.01105 0.00383 -0.0285 0.8090 0.0463
-4.000 -0.2743 0.01083 0.00358 -0.0283 0.7988 0.0488
-3.750 -0.2475 0.01065 0.00338 -0.0280 0.7879 0.0519
-3.500 -0.2204 0.01052 0.00320 -0.0278 0.7758 0.0553
-3.250 -0.1933 0.01036 0.00301 -0.0277 0.7630 0.0592
-3.000 -0.1663 0.01021 0.00283 -0.0275 0.7485 0.0640
-2.750 -0.1390 0.01011 0.00267 -0.0273 0.7324 0.0679
-2.500 -0.1120 0.00998 0.00249 -0.0271 0.7157 0.0733
-2.250 -0.0848 0.00988 0.00234 -0.0270 0.6997 0.0792
-2.000 -0.0576 0.00978 0.00220 -0.0268 0.6848 0.0869
-1.750 -0.0306 0.00964 0.00209 -0.0267 0.6710 0.1038
-1.500 -0.0037 0.00949 0.00201 -0.0265 0.6587 0.1379
-1.250 0.0234 0.00937 0.00193 -0.0264 0.6475 0.1630
-1.000 0.0502 0.00919 0.00184 -0.0263 0.6368 0.1984
-0.750 0.0752 0.00874 0.00173 -0.0260 0.6272 0.3086
-0.250 0.1229 0.00772 0.00160 -0.0249 0.6098 0.5750
0.000 0.1438 0.00717 0.00160 -0.0234 0.6011 0.7325
0.250 0.1677 0.00701 0.00170 -0.0223 0.5900 0.8132
0.500 0.1937 0.00702 0.00177 -0.0216 0.5783 0.8536
0.750 0.2200 0.00708 0.00183 -0.0211 0.5670 0.8800
1.000 0.2465 0.00716 0.00190 -0.0205 0.5560 0.9000
1.250 0.2733 0.00723 0.00195 -0.0201 0.5437 0.9142
1.500 0.3001 0.00733 0.00201 -0.0197 0.5301 0.9272
1.750 0.3277 0.00745 0.00209 -0.0194 0.5142 0.9388
2.000 0.3556 0.00758 0.00215 -0.0193 0.4969 0.9476
2.250 0.3843 0.00772 0.00222 -0.0195 0.4790 0.9546
2.500 0.4127 0.00789 0.00229 -0.0196 0.4586 0.9606
2.750 0.4444 0.00806 0.00239 -0.0205 0.4400 0.9655
3.000 0.4739 0.00824 0.00250 -0.0208 0.4241 0.9725
3.250 0.5092 0.00844 0.00262 -0.0225 0.4073 0.9757
3.500 0.5413 0.00861 0.00273 -0.0236 0.3922 0.9782
3.750 0.5723 0.00877 0.00285 -0.0245 0.3792 0.9806
4.000 0.6018 0.00894 0.00297 -0.0250 0.3667 0.9836
4.250 0.6348 0.00914 0.00311 -0.0263 0.3518 0.9850
4.500 0.6675 0.00933 0.00326 -0.0276 0.3373 0.9867
5.000 0.7313 0.00971 0.00357 -0.0297 0.3116 0.9908
5.250 0.7614 0.00995 0.00376 -0.0305 0.2950 0.9932
5.500 0.7920 0.01023 0.00396 -0.0314 0.2723 0.9949
5.750 0.8224 0.01058 0.00419 -0.0323 0.2441 0.9966
6.000 0.8516 0.01102 0.00447 -0.0331 0.2077 0.9985
6.250 0.8756 0.01179 0.00493 -0.0331 0.1499 1.0000
6.500 0.8938 0.01223 0.00527 -0.0315 0.1323 1.0000
6.750 0.9133 0.01255 0.00558 -0.0301 0.1233 1.0000
7.000 0.9325 0.01290 0.00590 -0.0286 0.1149 1.0000
7.250 0.9526 0.01319 0.00619 -0.0273 0.1086 1.0000
7.500 0.9721 0.01355 0.00653 -0.0259 0.1022 1.0000
7.750 0.9934 0.01379 0.00681 -0.0248 0.0977 1.0000
8.000 1.0138 0.01413 0.00714 -0.0237 0.0900 1.0000
8.250 1.0349 0.01446 0.00747 -0.0226 0.0805 1.0000
8.500 1.0535 0.01501 0.00788 -0.0213 0.0605 1.0000
8.750 1.0709 0.01569 0.00844 -0.0199 0.0447 1.0000
9.000 1.0898 0.01625 0.00899 -0.0186 0.0377 1.0000
9.250 1.1093 0.01677 0.00952 -0.0175 0.0333 1.0000
9.500 1.1277 0.01736 0.01012 -0.0162 0.0295 1.0000
9.750 1.1473 0.01785 0.01065 -0.0152 0.0272 1.0000
10.000 1.1652 0.01844 0.01126 -0.0139 0.0247 1.0000
10.250 1.1827 0.01904 0.01191 -0.0126 0.0226 1.0000
10.500 1.1998 0.01961 0.01252 -0.0112 0.0207 1.0000
10.750 1.2133 0.02028 0.01321 -0.0093 0.0191 1.0000
11.000 1.2264 0.02098 0.01396 -0.0074 0.0179 1.0000
11.250 1.2400 0.02170 0.01475 -0.0058 0.0169 1.0000
11.500 1.2526 0.02252 0.01563 -0.0041 0.0159 1.0000
11.750 1.2640 0.02346 0.01661 -0.0025 0.0150 1.0000
12.000 1.2735 0.02458 0.01779 -0.0009 0.0142 1.0000
12.250 1.2849 0.02562 0.01891 0.0004 0.0137 1.0000
12.500 1.2953 0.02678 0.02016 0.0016 0.0131 1.0000
12.750 1.3049 0.02807 0.02152 0.0027 0.0125 1.0000
13.000 1.3134 0.02950 0.02302 0.0037 0.0120 1.0000
13.250 1.3203 0.03113 0.02474 0.0046 0.0116 1.0000
13.500 1.3248 0.03306 0.02674 0.0054 0.0112 1.0000
13.750 1.3270 0.03529 0.02907 0.0060 0.0109 1.0000
14.000 1.3321 0.03733 0.03121 0.0064 0.0107 1.0000
14.250 1.3357 0.03959 0.03358 0.0067 0.0105 1.0000
14.500 1.3381 0.04208 0.03618 0.0067 0.0102 1.0000
14.750 1.3393 0.04476 0.03897 0.0066 0.0100 1.0000
15.000 1.3396 0.04763 0.04195 0.0064 0.0098 1.0000
15.250 1.3388 0.05071 0.04513 0.0060 0.0096 1.0000
15.500 1.3367 0.05399 0.04852 0.0054 0.0094 1.0000
15.750 1.3337 0.05748 0.05212 0.0047 0.0092 1.0000
16.000 1.3297 0.06123 0.05598 0.0037 0.0090 1.0000
16.250 1.3242 0.06527 0.06012 0.0026 0.0089 1.0000
16.500 1.3174 0.06963 0.06459 0.0012 0.0087 1.0000
16.750 1.3090 0.07434 0.06940 -0.0004 0.0086 1.0000
17.000 1.2988 0.07940 0.07458 -0.0022 0.0085 1.0000
17.250 1.2873 0.08477 0.08006 -0.0042 0.0084 1.0000
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Polar data table (+)
Polar graphs
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