AH 81-131 (ah81131-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 81-131 (ah81131-il) Reynolds number: 100,000 Max Cl/Cd: 38.15 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah81131-il-100000-n5.txt Download as CSV file: xf-ah81131-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 81-131
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3773 0.10235 0.09770 -0.0355 0.8169 0.0476
-9.500 -0.3757 0.09822 0.09358 -0.0383 0.8154 0.0480
-9.250 -0.3752 0.09410 0.08948 -0.0412 0.8138 0.0483
-9.000 -0.3099 0.07603 0.07160 -0.0513 0.8061 0.0284
-8.750 -0.3119 0.07124 0.06682 -0.0538 0.8047 0.0275
-8.500 -0.3217 0.06574 0.06130 -0.0577 0.8030 0.0268
-8.250 -0.4061 0.07193 0.06707 -0.0573 0.8049 0.0279
-8.000 -0.4100 0.06852 0.06360 -0.0573 0.8028 0.0269
-7.750 -0.4128 0.06514 0.06008 -0.0570 0.8006 0.0260
-7.500 -0.4151 0.06169 0.05645 -0.0560 0.7986 0.0250
-7.250 -0.4158 0.05826 0.05278 -0.0544 0.7967 0.0239
-7.000 -0.4118 0.05428 0.04847 -0.0536 0.7940 0.0225
-6.750 -0.4074 0.04984 0.04344 -0.0514 0.7914 0.0206
-6.500 -0.3947 0.04741 0.04058 -0.0496 0.7890 0.0199
-6.000 -0.3682 0.04309 0.03555 -0.0459 0.7848 0.0194
-5.750 -0.3550 0.04068 0.03278 -0.0437 0.7832 0.0193
-5.250 -0.3198 0.03605 0.02749 -0.0421 0.7776 0.0207
-5.000 -0.2999 0.03471 0.02597 -0.0414 0.7752 0.0223
-4.750 -0.2783 0.03338 0.02437 -0.0404 0.7730 0.0238
-4.500 -0.2542 0.03178 0.02242 -0.0393 0.7712 0.0239
-4.250 -0.2288 0.03033 0.02073 -0.0385 0.7698 0.0243
-4.000 -0.2019 0.02922 0.01947 -0.0387 0.7670 0.0249
-3.750 -0.1769 0.02828 0.01843 -0.0386 0.7641 0.0257
-3.500 -0.1546 0.02747 0.01753 -0.0377 0.7615 0.0268
-3.250 -0.1344 0.02680 0.01674 -0.0363 0.7592 0.0281
-3.000 -0.1147 0.02626 0.01606 -0.0347 0.7574 0.0297
-2.750 -0.0955 0.02568 0.01538 -0.0331 0.7560 0.0360
-2.500 -0.0773 0.02562 0.01526 -0.0324 0.7512 0.0446
-2.250 0.0401 0.02262 0.01571 -0.0448 0.7560 0.9074
-2.000 0.0810 0.02321 0.01602 -0.0480 0.7524 0.9253
-1.750 0.1193 0.02353 0.01612 -0.0506 0.7497 0.9379
-1.500 0.1572 0.02378 0.01616 -0.0531 0.7477 0.9492
-1.250 0.1925 0.02394 0.01615 -0.0550 0.7458 0.9595
-1.000 0.2301 0.02400 0.01603 -0.0574 0.7442 0.9674
-0.750 0.2660 0.02402 0.01591 -0.0593 0.7428 0.9748
-0.500 0.3032 0.02442 0.01623 -0.0627 0.7393 0.9827
-0.250 0.3423 0.02463 0.01635 -0.0661 0.7361 0.9894
0.000 0.3805 0.02471 0.01636 -0.0690 0.7336 0.9960
0.250 0.4132 0.02474 0.01632 -0.0706 0.7315 1.0000
0.500 0.4323 0.02475 0.01627 -0.0692 0.7294 1.0000
0.750 0.4487 0.02526 0.01678 -0.0687 0.7222 1.0000
1.000 0.4678 0.02526 0.01673 -0.0673 0.7182 1.0000
1.250 0.4883 0.02511 0.01653 -0.0657 0.7158 1.0000
1.750 0.5221 0.02587 0.01732 -0.0636 0.7048 1.0000
2.000 0.5435 0.02579 0.01721 -0.0623 0.7025 1.0000
2.250 0.5548 0.02662 0.01808 -0.0610 0.6946 1.0000
2.500 0.5749 0.02669 0.01816 -0.0598 0.6912 1.0000
2.750 0.5975 0.02657 0.01809 -0.0586 0.6890 1.0000
3.000 0.6056 0.02748 0.01904 -0.0568 0.6802 1.0000
3.250 0.6277 0.02742 0.01901 -0.0556 0.6772 1.0000
3.750 0.6575 0.02816 0.01986 -0.0523 0.6651 1.0000
4.000 0.6823 0.02793 0.01973 -0.0513 0.6626 1.0000
4.250 0.6881 0.02873 0.02059 -0.0488 0.6527 1.0000
4.500 0.7157 0.02822 0.02016 -0.0479 0.6495 1.0000
4.750 0.7241 0.02867 0.02068 -0.0454 0.6390 1.0000
5.000 0.7548 0.02787 0.01997 -0.0447 0.6357 1.0000
5.250 0.7621 0.02838 0.02057 -0.0420 0.6246 1.0000
5.500 0.7896 0.02779 0.02015 -0.0411 0.6209 1.0000
5.750 0.7980 0.02822 0.02067 -0.0385 0.6103 1.0000
6.000 0.8065 0.02857 0.02111 -0.0357 0.5999 1.0000
6.250 0.8400 0.02731 0.02002 -0.0351 0.5946 1.0000
6.500 0.8471 0.02722 0.02000 -0.0315 0.5795 1.0000
6.750 0.8462 0.02750 0.02032 -0.0271 0.5607 1.0000
7.000 0.8623 0.02684 0.01975 -0.0243 0.5377 1.0000
7.250 0.8777 0.02643 0.01937 -0.0216 0.5095 1.0000
7.500 0.9082 0.02524 0.01811 -0.0203 0.4704 1.0000
7.750 0.9342 0.02449 0.01710 -0.0184 0.4195 1.0000
8.000 0.9399 0.02505 0.01739 -0.0150 0.3721 1.0000
8.250 0.9397 0.02609 0.01819 -0.0114 0.3211 1.0000
8.500 0.9361 0.02745 0.01922 -0.0077 0.2691 1.0000
8.750 0.9325 0.02900 0.02050 -0.0044 0.2169 1.0000
9.000 0.9296 0.03068 0.02184 -0.0013 0.1620 1.0000
9.250 0.9286 0.03238 0.02323 0.0013 0.1223 1.0000
9.500 0.9317 0.03390 0.02461 0.0036 0.1027 1.0000
9.750 0.9362 0.03535 0.02603 0.0056 0.0909 1.0000
10.000 0.9418 0.03677 0.02747 0.0074 0.0829 1.0000
10.250 0.9476 0.03820 0.02897 0.0092 0.0773 1.0000
10.500 0.9527 0.03974 0.03055 0.0110 0.0729 1.0000
10.750 0.9608 0.04110 0.03205 0.0125 0.0666 1.0000
11.000 0.9665 0.04265 0.03364 0.0138 0.0580 1.0000
11.250 0.9715 0.04430 0.03527 0.0148 0.0486 1.0000
11.500 0.9780 0.04591 0.03694 0.0157 0.0383 1.0000
11.750 0.9855 0.04751 0.03877 0.0169 0.0306 1.0000
12.000 0.9896 0.04948 0.04079 0.0180 0.0244 1.0000
12.250 0.9940 0.05148 0.04287 0.0189 0.0202 1.0000
12.500 0.9949 0.05389 0.04532 0.0201 0.0183 1.0000
12.750 0.9994 0.05605 0.04767 0.0213 0.0169 1.0000
13.000 1.0034 0.05837 0.05017 0.0224 0.0154 1.0000
13.250 1.0080 0.06068 0.05263 0.0233 0.0146 1.0000
13.500 1.0113 0.06316 0.05527 0.0241 0.0139 1.0000
13.750 1.0129 0.06593 0.05819 0.0247 0.0133 1.0000
14.000 1.0133 0.06889 0.06131 0.0251 0.0128 1.0000
14.250 1.0122 0.07216 0.06476 0.0255 0.0125 1.0000
14.500 1.0075 0.07608 0.06888 0.0257 0.0122 1.0000
14.750 1.0013 0.08033 0.07334 0.0255 0.0120 1.0000
15.000 0.9938 0.08478 0.07805 0.0249 0.0120 1.0000
15.250 0.9830 0.08991 0.08342 0.0238 0.0119 1.0000
15.500 0.9702 0.09554 0.08930 0.0222 0.0118 1.0000
15.750 0.9568 0.10151 0.09548 0.0200 0.0119 1.0000
16.000 0.9407 0.10831 0.10249 0.0170 0.0119 1.0000
16.250 0.9242 0.11561 0.10997 0.0135 0.0119 1.0000
16.500 0.9063 0.12372 0.11826 0.0092 0.0120 1.0000
16.750 0.8871 0.13271 0.12739 0.0043 0.0120 1.0000
17.000 0.8680 0.14291 0.13779 -0.0016 0.0124 1.0000
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Polar data table (+)
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