AG38 (ag38-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG38 (ag38-il) Reynolds number: 100,000 Max Cl/Cd: 48.36 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag38-il-100000-n5.txt Download as CSV file: xf-ag38-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG38
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5362 0.12026 0.11508 0.0040 1.0000 0.0433
-10.500 -0.5361 0.11701 0.11187 0.0003 1.0000 0.0438
-10.250 -0.5350 0.11349 0.10840 -0.0030 1.0000 0.0441
-10.000 -0.5332 0.10980 0.10475 -0.0060 1.0000 0.0442
-9.750 -0.5316 0.10596 0.10097 -0.0091 1.0000 0.0443
-9.500 -0.5305 0.10199 0.09704 -0.0125 1.0000 0.0444
-9.250 -0.5266 0.09753 0.09261 -0.0173 1.0000 0.0444
-9.000 -0.5133 0.09352 0.08859 -0.0071 1.0000 0.0474
-8.750 -0.5090 0.09030 0.08541 -0.0080 1.0000 0.0495
-8.500 -0.5052 0.08657 0.08171 -0.0109 1.0000 0.0514
-8.250 -0.4991 0.08225 0.07742 -0.0156 1.0000 0.0534
-8.000 -0.4876 0.07641 0.07139 -0.0294 1.0000 0.0568
-7.500 -0.4214 0.05409 0.04949 -0.0282 1.0000 0.0400
-7.250 -0.4532 0.05834 0.05308 -0.0339 1.0000 0.0315
-7.000 -0.4394 0.05387 0.04848 -0.0354 1.0000 0.0301
-6.750 -0.4228 0.04895 0.04333 -0.0371 1.0000 0.0287
-6.500 -0.4039 0.04364 0.03767 -0.0386 1.0000 0.0273
-6.250 -0.3829 0.03830 0.03182 -0.0394 1.0000 0.0261
-6.000 -0.3605 0.03384 0.02675 -0.0395 1.0000 0.0255
-5.750 -0.3377 0.03069 0.02314 -0.0393 1.0000 0.0256
-5.500 -0.3152 0.02890 0.02114 -0.0389 1.0000 0.0272
-5.250 -0.2911 0.02690 0.01878 -0.0384 1.0000 0.0292
-5.000 -0.2661 0.02471 0.01614 -0.0378 1.0000 0.0301
-4.750 -0.2408 0.02275 0.01379 -0.0370 1.0000 0.0308
-4.500 -0.2154 0.02113 0.01185 -0.0362 1.0000 0.0318
-4.250 -0.1900 0.01992 0.01039 -0.0353 1.0000 0.0332
-4.000 -0.1657 0.01865 0.00912 -0.0349 1.0000 0.0371
-3.750 -0.1408 0.01770 0.00811 -0.0342 1.0000 0.0403
-3.500 -0.1156 0.01684 0.00715 -0.0334 1.0000 0.0434
-3.250 -0.0907 0.01607 0.00642 -0.0330 1.0000 0.0502
-3.000 -0.0652 0.01546 0.00573 -0.0324 1.0000 0.0587
-2.750 -0.0395 0.01485 0.00521 -0.0321 1.0000 0.0780
-2.500 -0.0130 0.01395 0.00479 -0.0322 1.0000 0.1728
-2.250 0.0122 0.01220 0.00473 -0.0322 1.0000 0.5951
-2.000 0.0362 0.01136 0.00467 -0.0301 1.0000 1.0000
-1.750 0.0691 0.01145 0.00454 -0.0314 0.9955 1.0000
-1.500 0.1126 0.01150 0.00439 -0.0348 0.9847 1.0000
-1.250 0.1553 0.01152 0.00424 -0.0379 0.9723 1.0000
-1.000 0.1971 0.01151 0.00412 -0.0408 0.9585 1.0000
-0.750 0.2366 0.01149 0.00401 -0.0431 0.9419 1.0000
-0.500 0.2710 0.01146 0.00391 -0.0442 0.9186 1.0000
-0.250 0.3038 0.01141 0.00381 -0.0449 0.8893 1.0000
0.000 0.3395 0.01135 0.00366 -0.0461 0.8568 1.0000
0.250 0.3746 0.01132 0.00350 -0.0469 0.8232 1.0000
0.500 0.4051 0.01139 0.00342 -0.0468 0.7867 1.0000
0.750 0.4328 0.01155 0.00344 -0.0463 0.7486 1.0000
1.000 0.4596 0.01176 0.00352 -0.0457 0.7107 1.0000
1.250 0.4859 0.01198 0.00361 -0.0450 0.6713 1.0000
1.500 0.5118 0.01223 0.00370 -0.0443 0.6351 1.0000
1.750 0.5377 0.01253 0.00383 -0.0437 0.6044 1.0000
2.000 0.5636 0.01286 0.00406 -0.0432 0.5764 1.0000
2.250 0.5895 0.01319 0.00429 -0.0427 0.5496 1.0000
2.500 0.6154 0.01353 0.00456 -0.0422 0.5228 1.0000
2.750 0.6412 0.01385 0.00483 -0.0418 0.4949 1.0000
3.000 0.6669 0.01417 0.00516 -0.0413 0.4639 1.0000
3.250 0.6924 0.01449 0.00544 -0.0409 0.4283 1.0000
3.500 0.7174 0.01487 0.00572 -0.0404 0.3887 1.0000
3.750 0.7419 0.01534 0.00606 -0.0399 0.3468 1.0000
4.000 0.7662 0.01589 0.00649 -0.0394 0.3041 1.0000
4.250 0.7902 0.01651 0.00697 -0.0390 0.2628 1.0000
4.500 0.8141 0.01719 0.00751 -0.0386 0.2233 1.0000
4.750 0.8378 0.01791 0.00812 -0.0382 0.1866 1.0000
5.000 0.8612 0.01870 0.00884 -0.0377 0.1540 1.0000
5.250 0.8842 0.01955 0.00961 -0.0373 0.1250 1.0000
5.500 0.9067 0.02050 0.01049 -0.0367 0.1035 1.0000
5.750 0.9289 0.02149 0.01145 -0.0361 0.0866 1.0000
6.000 0.9505 0.02256 0.01253 -0.0354 0.0751 1.0000
6.250 0.9721 0.02362 0.01372 -0.0347 0.0662 1.0000
6.500 0.9932 0.02476 0.01496 -0.0339 0.0589 1.0000
6.750 1.0134 0.02598 0.01625 -0.0331 0.0538 1.0000
7.000 1.0331 0.02747 0.01787 -0.0320 0.0502 1.0000
7.500 1.0727 0.03016 0.02084 -0.0304 0.0424 1.0000
7.750 1.0911 0.03212 0.02295 -0.0293 0.0403 1.0000
8.000 1.1102 0.03409 0.02525 -0.0283 0.0383 1.0000
8.250 1.1277 0.03604 0.02750 -0.0272 0.0360 1.0000
8.500 1.1438 0.03773 0.02939 -0.0262 0.0337 1.0000
8.750 1.1579 0.03981 0.03158 -0.0252 0.0320 1.0000
9.000 1.1687 0.04293 0.03503 -0.0238 0.0310 1.0000
9.250 1.1758 0.04603 0.03863 -0.0221 0.0302 1.0000
9.500 1.1776 0.04946 0.04254 -0.0201 0.0295 1.0000
9.750 1.1740 0.05300 0.04651 -0.0181 0.0287 1.0000
10.000 1.1646 0.05650 0.05038 -0.0159 0.0280 1.0000
10.250 1.1493 0.06009 0.05425 -0.0138 0.0275 1.0000
10.500 1.1312 0.06440 0.05884 -0.0133 0.0273 1.0000
10.750 1.1090 0.07004 0.06474 -0.0151 0.0274 1.0000
11.000 1.0829 0.07756 0.07250 -0.0196 0.0278 1.0000
11.250 1.0533 0.08739 0.08252 -0.0268 0.0285 1.0000
11.500 1.0222 0.09904 0.09428 -0.0350 0.0294 1.0000
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Polar data table (+)
Polar graphs
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