GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 450 AIRFOIL (goe450-il) Reynolds number: 200,000 Max Cl/Cd: 85.65 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe450-il-200000-n5.txt Download as CSV file: xf-goe450-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 450 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3050 0.11473 0.11109 -0.0376 1.0000 0.0241
-9.750 -0.3069 0.11264 0.10904 -0.0369 1.0000 0.0254
-9.500 -0.3163 0.11115 0.10762 -0.0366 1.0000 0.0266
-9.250 -0.3113 0.10776 0.10424 -0.0417 0.9966 0.0269
-9.000 -0.2996 0.10353 0.10002 -0.0467 0.9928 0.0270
-8.750 -0.2871 0.09927 0.09575 -0.0511 0.9885 0.0271
-8.500 -0.2735 0.09488 0.09136 -0.0560 0.9844 0.0271
-8.250 -0.2612 0.09058 0.08706 -0.0606 0.9782 0.0271
-8.000 -0.2454 0.08696 0.08343 -0.0592 0.9773 0.0279
-7.750 -0.2258 0.08419 0.08065 -0.0613 0.9749 0.0296
-7.500 -0.2116 0.08086 0.07733 -0.0659 0.9671 0.0325
-7.250 -0.1848 0.07499 0.07140 -0.0818 0.9574 0.0343
-7.000 -0.1608 0.06986 0.06620 -0.0896 0.9516 0.0344
-6.500 -0.1276 0.06102 0.05730 -0.0962 0.9397 0.0354
-6.250 -0.1093 0.05960 0.05589 -0.0956 0.9359 0.0374
-6.000 -0.0862 0.05635 0.05256 -0.0998 0.9294 0.0404
-5.750 -0.0501 0.04708 0.04296 -0.1117 0.9215 0.0337
-5.500 -0.0211 0.04169 0.03730 -0.1167 0.9157 0.0339
-5.000 0.0335 0.03274 0.02769 -0.1226 0.9039 0.0340
-4.750 0.0580 0.02929 0.02388 -0.1238 0.8965 0.0340
-4.500 0.0852 0.02588 0.02000 -0.1252 0.8907 0.0353
-4.250 0.1122 0.02376 0.01758 -0.1259 0.8849 0.0358
-4.000 0.1391 0.02176 0.01521 -0.1261 0.8779 0.0358
-3.750 0.1686 0.02013 0.01325 -0.1267 0.8730 0.0360
-3.500 0.1945 0.01892 0.01179 -0.1265 0.8645 0.0363
-3.250 0.2235 0.01792 0.01057 -0.1267 0.8588 0.0371
-3.000 0.2500 0.01721 0.00973 -0.1265 0.8501 0.0383
-2.750 0.2791 0.01633 0.00863 -0.1266 0.8437 0.0389
-2.500 0.3059 0.01557 0.00772 -0.1263 0.8343 0.0390
-2.250 0.3342 0.01489 0.00689 -0.1262 0.8264 0.0394
-2.000 0.3617 0.01431 0.00620 -0.1260 0.8168 0.0398
-1.750 0.3890 0.01381 0.00563 -0.1257 0.8069 0.0404
-1.500 0.4168 0.01337 0.00511 -0.1256 0.7974 0.0410
-1.250 0.4440 0.01301 0.00469 -0.1253 0.7865 0.0417
-1.000 0.4712 0.01276 0.00438 -0.1251 0.7756 0.0432
-0.750 0.4987 0.01247 0.00405 -0.1249 0.7648 0.0447
-0.500 0.5262 0.01223 0.00374 -0.1247 0.7539 0.0460
-0.250 0.5533 0.01207 0.00353 -0.1245 0.7423 0.0474
0.000 0.5806 0.01197 0.00337 -0.1243 0.7314 0.0494
0.250 0.6080 0.01190 0.00323 -0.1241 0.7210 0.0525
0.500 0.6352 0.01183 0.00316 -0.1239 0.7103 0.0597
0.750 0.6623 0.01170 0.00314 -0.1237 0.7002 0.1072
1.000 0.6873 0.01089 0.00332 -0.1237 0.6907 0.4783
1.500 0.7403 0.01000 0.00334 -0.1226 0.6710 1.0000
2.000 0.7938 0.01029 0.00345 -0.1221 0.6519 1.0000
2.250 0.8204 0.01045 0.00353 -0.1218 0.6421 1.0000
2.500 0.8467 0.01063 0.00362 -0.1214 0.6313 1.0000
2.750 0.8728 0.01079 0.00374 -0.1211 0.6198 1.0000
3.000 0.8989 0.01096 0.00387 -0.1207 0.6087 1.0000
3.250 0.9247 0.01115 0.00401 -0.1203 0.5966 1.0000
3.500 0.9501 0.01135 0.00415 -0.1198 0.5831 1.0000
3.750 0.9752 0.01156 0.00431 -0.1192 0.5684 1.0000
4.000 0.9999 0.01177 0.00450 -0.1187 0.5522 1.0000
4.250 1.0243 0.01199 0.00468 -0.1180 0.5338 1.0000
4.500 1.0483 0.01224 0.00488 -0.1173 0.5144 1.0000
4.750 1.0716 0.01253 0.00510 -0.1165 0.4941 1.0000
5.000 1.0948 0.01284 0.00536 -0.1156 0.4730 1.0000
5.250 1.1172 0.01319 0.00563 -0.1147 0.4510 1.0000
5.500 1.1391 0.01358 0.00594 -0.1137 0.4294 1.0000
5.750 1.1609 0.01398 0.00630 -0.1127 0.4079 1.0000
6.000 1.1821 0.01442 0.00668 -0.1116 0.3871 1.0000
6.250 1.2033 0.01486 0.00708 -0.1105 0.3655 1.0000
6.500 1.2232 0.01537 0.00752 -0.1093 0.3418 1.0000
6.750 1.2408 0.01601 0.00805 -0.1077 0.3079 1.0000
7.000 1.2580 0.01668 0.00860 -0.1060 0.2713 1.0000
7.250 1.2706 0.01767 0.00931 -0.1038 0.2157 1.0000
7.750 1.2909 0.02001 0.01117 -0.0987 0.1294 1.0000
8.000 1.2953 0.02139 0.01224 -0.0953 0.0839 1.0000
8.250 1.3055 0.02241 0.01322 -0.0927 0.0653 1.0000
8.750 1.3258 0.02450 0.01526 -0.0878 0.0445 1.0000
9.000 1.3353 0.02563 0.01640 -0.0855 0.0406 1.0000
9.250 1.3464 0.02665 0.01756 -0.0834 0.0381 1.0000
9.500 1.3555 0.02784 0.01885 -0.0812 0.0357 1.0000
9.750 1.3619 0.02926 0.02035 -0.0788 0.0336 1.0000
10.000 1.3638 0.03106 0.02224 -0.0761 0.0316 1.0000
10.250 1.3727 0.03238 0.02370 -0.0743 0.0302 1.0000
10.500 1.3792 0.03393 0.02538 -0.0724 0.0287 1.0000
10.750 1.3841 0.03566 0.02722 -0.0704 0.0273 1.0000
11.000 1.3879 0.03756 0.02924 -0.0686 0.0259 1.0000
11.250 1.3881 0.03984 0.03158 -0.0667 0.0247 1.0000
11.500 1.3876 0.04227 0.03410 -0.0648 0.0236 1.0000
11.750 1.3944 0.04408 0.03607 -0.0636 0.0226 1.0000
12.000 1.3984 0.04619 0.03832 -0.0622 0.0216 1.0000
12.250 1.4018 0.04842 0.04067 -0.0610 0.0206 1.0000
12.500 1.4050 0.05070 0.04305 -0.0599 0.0197 1.0000
12.750 1.4076 0.05308 0.04553 -0.0590 0.0189 1.0000
13.000 1.4083 0.05571 0.04822 -0.0581 0.0183 1.0000
13.250 1.4096 0.05835 0.05097 -0.0572 0.0176 1.0000
13.500 1.4127 0.06086 0.05366 -0.0564 0.0168 1.0000
13.750 1.4147 0.06354 0.05649 -0.0557 0.0162 1.0000
14.000 1.4161 0.06633 0.05943 -0.0551 0.0157 1.0000
14.250 1.4170 0.06924 0.06248 -0.0546 0.0152 1.0000
14.500 1.4174 0.07227 0.06564 -0.0544 0.0147 1.0000
14.750 1.4170 0.07543 0.06891 -0.0543 0.0144 1.0000
15.000 1.4160 0.07875 0.07235 -0.0545 0.0140 1.0000
15.250 1.4141 0.08223 0.07592 -0.0547 0.0137 1.0000
15.500 1.4108 0.08597 0.07978 -0.0549 0.0133 1.0000
15.750 1.4067 0.09000 0.08405 -0.0554 0.0130 1.0000
16.000 1.4012 0.09438 0.08865 -0.0562 0.0126 1.0000
16.250 1.3946 0.09902 0.09351 -0.0573 0.0123 1.0000
16.500 1.3872 0.10392 0.09862 -0.0587 0.0120 1.0000
16.750 1.3787 0.10914 0.10404 -0.0605 0.0118 1.0000
17.000 1.3692 0.11467 0.10977 -0.0626 0.0116 1.0000
17.250 1.3588 0.12056 0.11585 -0.0651 0.0115 1.0000
17.500 1.3474 0.12688 0.12237 -0.0682 0.0114 1.0000
17.750 1.3351 0.13362 0.12931 -0.0718 0.0113 1.0000
18.000 1.3214 0.14096 0.13685 -0.0760 0.0112 1.0000
18.250 1.3060 0.14905 0.14513 -0.0809 0.0112 1.0000
18.500 1.2879 0.15829 0.15458 -0.0867 0.0112 1.0000
18.750 1.2643 0.16984 0.16635 -0.0944 0.0113 1.0000
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