AH 81-131 (ah81131-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 81-131 (ah81131-il) Reynolds number: 200,000 Max Cl/Cd: 70.57 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah81131-il-200000-n5.txt Download as CSV file: xf-ah81131-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3468 0.11064 0.10714 -0.0112 0.7677 0.0234
-10.250 -0.3446 0.10654 0.10305 -0.0133 0.7666 0.0243
-10.000 -0.4411 0.10373 0.10007 -0.0179 0.7724 0.0203
-9.500 -0.4289 0.09824 0.09453 -0.0187 0.7707 0.0229
-7.000 -0.4662 0.05349 0.04891 -0.0347 0.7543 0.0182
-6.750 -0.4604 0.04969 0.04493 -0.0339 0.7521 0.0168
-6.500 -0.4529 0.04541 0.04033 -0.0323 0.7501 0.0151
-6.000 -0.4247 0.03767 0.03164 -0.0275 0.7467 0.0122
-5.750 -0.4104 0.03479 0.02843 -0.0257 0.7453 0.0120
-5.500 -0.3937 0.03222 0.02548 -0.0239 0.7440 0.0119
-5.250 -0.3747 0.02990 0.02278 -0.0223 0.7429 0.0118
-5.000 -0.3519 0.02785 0.02038 -0.0214 0.7412 0.0118
-4.750 -0.3258 0.02609 0.01831 -0.0212 0.7387 0.0119
-4.500 -0.2995 0.02460 0.01655 -0.0209 0.7365 0.0121
-4.250 -0.2729 0.02337 0.01510 -0.0206 0.7347 0.0124
-4.000 -0.2478 0.02177 0.01334 -0.0202 0.7331 0.0133
-3.750 -0.2232 0.02107 0.01260 -0.0198 0.7317 0.0150
-3.500 -0.1984 0.02032 0.01177 -0.0193 0.7305 0.0162
-3.250 -0.1749 0.01948 0.01084 -0.0183 0.7295 0.0166
-3.000 -0.1510 0.01885 0.01014 -0.0177 0.7279 0.0172
-2.750 -0.1254 0.01845 0.00967 -0.0178 0.7243 0.0180
-2.500 -0.1008 0.01808 0.00920 -0.0174 0.7219 0.0190
-2.250 -0.0767 0.01767 0.00869 -0.0167 0.7200 0.0215
-2.000 -0.0521 0.01735 0.00829 -0.0161 0.7185 0.0295
-1.750 -0.0358 0.01619 0.00788 -0.0144 0.7172 0.2084
-1.500 0.0420 0.01415 0.00856 -0.0232 0.7173 0.9043
-1.000 0.1081 0.01445 0.00855 -0.0249 0.7154 0.9316
-0.750 0.1478 0.01488 0.00889 -0.0279 0.7118 0.9402
-0.500 0.1837 0.01511 0.00904 -0.0300 0.7093 0.9472
-0.250 0.2184 0.01521 0.00905 -0.0317 0.7073 0.9530
0.000 0.2497 0.01526 0.00902 -0.0326 0.7056 0.9592
0.250 0.2860 0.01526 0.00895 -0.0346 0.7044 0.9633
0.500 0.3182 0.01528 0.00891 -0.0357 0.7033 0.9695
0.750 0.3534 0.01515 0.00871 -0.0372 0.7021 0.9740
1.000 0.3916 0.01540 0.00898 -0.0403 0.6961 0.9780
1.250 0.4243 0.01529 0.00884 -0.0415 0.6930 0.9830
1.500 0.4593 0.01507 0.00859 -0.0430 0.6910 0.9867
1.750 0.4944 0.01484 0.00835 -0.0446 0.6895 0.9905
2.000 0.5294 0.01492 0.00845 -0.0467 0.6863 0.9942
2.250 0.5656 0.01507 0.00865 -0.0493 0.6822 0.9971
2.500 0.6004 0.01498 0.00861 -0.0511 0.6797 1.0000
2.750 0.6239 0.01487 0.00852 -0.0504 0.6776 1.0000
3.000 0.6474 0.01473 0.00838 -0.0497 0.6759 1.0000
3.250 0.6731 0.01505 0.00879 -0.0502 0.6705 1.0000
3.500 0.6975 0.01508 0.00888 -0.0499 0.6668 1.0000
3.750 0.7211 0.01485 0.00871 -0.0490 0.6639 1.0000
4.000 0.7456 0.01478 0.00870 -0.0486 0.6577 1.0000
4.250 0.7697 0.01451 0.00849 -0.0479 0.6514 1.0000
4.500 0.7940 0.01437 0.00841 -0.0473 0.6448 1.0000
5.000 0.8426 0.01389 0.00809 -0.0459 0.6241 1.0000
5.250 0.8668 0.01371 0.00797 -0.0453 0.6109 1.0000
5.500 0.8907 0.01355 0.00785 -0.0445 0.5963 1.0000
5.750 0.9141 0.01340 0.00770 -0.0436 0.5715 1.0000
6.000 0.9358 0.01326 0.00742 -0.0422 0.5281 1.0000
6.250 0.9519 0.01376 0.00746 -0.0404 0.4522 1.0000
6.500 0.9641 0.01479 0.00819 -0.0388 0.3983 1.0000
6.750 0.9737 0.01583 0.00904 -0.0368 0.3530 1.0000
7.000 0.9751 0.01717 0.01013 -0.0339 0.3008 1.0000
7.500 0.9582 0.01962 0.01222 -0.0244 0.2332 1.0000
7.750 0.9486 0.02082 0.01323 -0.0193 0.1965 1.0000
8.000 0.9413 0.02217 0.01433 -0.0150 0.1532 1.0000
8.250 0.9358 0.02362 0.01549 -0.0111 0.1110 1.0000
8.500 0.9366 0.02486 0.01662 -0.0081 0.0880 1.0000
8.750 0.9419 0.02593 0.01765 -0.0057 0.0759 1.0000
9.000 0.9499 0.02690 0.01865 -0.0037 0.0686 1.0000
9.250 0.9557 0.02805 0.01976 -0.0016 0.0618 1.0000
9.500 0.9661 0.02893 0.02072 0.0000 0.0552 1.0000
9.750 0.9742 0.03001 0.02177 0.0017 0.0478 1.0000
10.000 0.9847 0.03095 0.02273 0.0031 0.0405 1.0000
10.250 0.9950 0.03193 0.02376 0.0045 0.0351 1.0000
10.500 1.0052 0.03296 0.02480 0.0058 0.0271 1.0000
10.750 1.0136 0.03417 0.02600 0.0073 0.0177 1.0000
11.250 1.0251 0.03713 0.02906 0.0104 0.0107 1.0000
11.500 1.0302 0.03876 0.03079 0.0119 0.0093 1.0000
11.750 1.0359 0.04040 0.03252 0.0133 0.0086 1.0000
12.000 1.0399 0.04225 0.03447 0.0146 0.0080 1.0000
12.250 1.0428 0.04426 0.03660 0.0159 0.0073 1.0000
12.500 1.0495 0.04594 0.03841 0.0168 0.0067 1.0000
12.750 1.0533 0.04798 0.04060 0.0179 0.0067 1.0000
13.000 1.0579 0.04998 0.04272 0.0188 0.0061 1.0000
13.250 1.0624 0.05202 0.04489 0.0195 0.0058 1.0000
13.500 1.0651 0.05432 0.04733 0.0202 0.0056 1.0000
13.750 1.0664 0.05684 0.05000 0.0209 0.0054 1.0000
14.000 1.0673 0.05948 0.05277 0.0214 0.0053 1.0000
14.250 1.0674 0.06227 0.05571 0.0218 0.0051 1.0000
14.500 1.0646 0.06551 0.05910 0.0220 0.0049 1.0000
14.750 1.0620 0.06882 0.06262 0.0221 0.0049 1.0000
15.000 1.0594 0.07222 0.06619 0.0220 0.0048 1.0000
15.250 1.0516 0.07647 0.07061 0.0217 0.0047 1.0000
15.500 1.0442 0.08081 0.07514 0.0211 0.0046 1.0000
15.750 1.0393 0.08493 0.07944 0.0202 0.0047 1.0000
16.000 1.0285 0.09012 0.08482 0.0189 0.0046 1.0000
16.250 1.0186 0.09539 0.09028 0.0172 0.0046 1.0000
16.500 1.0055 0.10147 0.09654 0.0151 0.0046 1.0000
16.750 0.9927 0.10778 0.10305 0.0124 0.0045 1.0000
17.250 0.9664 0.12124 0.11685 0.0062 0.0046 1.0000
17.750 0.9395 0.13632 0.13226 -0.0017 0.0046 1.0000
18.000 0.9247 0.14483 0.14092 -0.0063 0.0047 1.0000
18.250 0.9093 0.15424 0.15049 -0.0114 0.0048 1.0000
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Polar data table (+)
Polar graphs
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