AH21 9% version (Andrew Hollom) (ah21-9-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH21 9% version (Andrew Hollom) (ah21-9-il) Reynolds number: 500,000 Max Cl/Cd: 78.43 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah21-9-il-500000-n5.txt Download as CSV file: xf-ah21-9-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH21 9% version (Andrew Hollom)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5314 0.08235 0.08011 -0.0257 1.0000 0.0054
-8.500 -0.5427 0.07864 0.07645 -0.0260 1.0000 0.0055
-8.250 -0.5611 0.07541 0.07328 -0.0253 1.0000 0.0055
-8.000 -0.5743 0.07100 0.06890 -0.0275 1.0000 0.0055
-7.750 -0.5623 0.06129 0.05909 -0.0397 0.9967 0.0056
-7.500 -0.5499 0.05065 0.04821 -0.0491 0.9932 0.0060
-7.250 -0.5415 0.03881 0.03588 -0.0544 0.9886 0.0063
-7.000 -0.5342 0.02406 0.01984 -0.0567 0.9846 0.0069
-6.750 -0.5105 0.02003 0.01519 -0.0576 0.9832 0.0074
-6.500 -0.4827 0.01915 0.01416 -0.0582 0.9820 0.0078
-6.250 -0.4593 0.01846 0.01335 -0.0577 0.9794 0.0082
-6.000 -0.4330 0.01752 0.01224 -0.0578 0.9773 0.0090
-5.750 -0.4052 0.01660 0.01113 -0.0581 0.9755 0.0100
-5.500 -0.3762 0.01594 0.01028 -0.0586 0.9740 0.0112
-5.250 -0.3463 0.01536 0.00955 -0.0592 0.9728 0.0118
-5.000 -0.3178 0.01387 0.00785 -0.0596 0.9717 0.0125
-4.750 -0.2881 0.01288 0.00676 -0.0603 0.9707 0.0134
-4.500 -0.2568 0.01244 0.00629 -0.0613 0.9699 0.0147
-4.250 -0.2329 0.01195 0.00575 -0.0606 0.9667 0.0157
-4.000 -0.2063 0.01142 0.00513 -0.0604 0.9640 0.0166
-3.750 -0.1772 0.01096 0.00460 -0.0608 0.9619 0.0173
-3.500 -0.1467 0.01057 0.00416 -0.0614 0.9603 0.0180
-3.250 -0.1152 0.01022 0.00376 -0.0623 0.9589 0.0184
-3.000 -0.0829 0.00994 0.00346 -0.0634 0.9578 0.0190
-2.750 -0.0501 0.00956 0.00299 -0.0645 0.9568 0.0203
-2.500 -0.0235 0.00934 0.00272 -0.0642 0.9534 0.0212
-2.250 0.0043 0.00912 0.00249 -0.0642 0.9499 0.0237
-2.000 0.0357 0.00887 0.00229 -0.0650 0.9477 0.0352
-1.750 0.0680 0.00844 0.00210 -0.0662 0.9458 0.1028
-1.500 0.1006 0.00795 0.00194 -0.0675 0.9440 0.2015
-1.250 0.1278 0.00736 0.00184 -0.0677 0.9400 0.3473
-1.000 0.1535 0.00675 0.00176 -0.0676 0.9347 0.5062
-0.750 0.1816 0.00603 0.00174 -0.0677 0.9309 0.7047
-0.500 0.2043 0.00568 0.00177 -0.0662 0.9240 0.8112
-0.250 0.2333 0.00552 0.00171 -0.0661 0.9174 0.8520
0.000 0.2593 0.00542 0.00167 -0.0653 0.9077 0.8829
0.250 0.2879 0.00532 0.00160 -0.0651 0.8965 0.9077
0.500 0.3175 0.00525 0.00152 -0.0651 0.8817 0.9282
0.750 0.3498 0.00520 0.00143 -0.0658 0.8614 0.9442
1.000 0.3822 0.00522 0.00137 -0.0665 0.8296 0.9578
1.250 0.4140 0.00535 0.00131 -0.0671 0.7804 0.9689
1.500 0.4439 0.00566 0.00131 -0.0673 0.7099 0.9790
1.750 0.4700 0.00625 0.00141 -0.0671 0.5975 0.9901
2.000 0.4942 0.00693 0.00158 -0.0666 0.4813 1.0000
2.250 0.5122 0.00739 0.00174 -0.0647 0.4079 1.0000
2.500 0.5318 0.00787 0.00191 -0.0632 0.3356 1.0000
2.750 0.5522 0.00840 0.00211 -0.0619 0.2594 1.0000
3.000 0.5744 0.00883 0.00234 -0.0610 0.2046 1.0000
3.250 0.5966 0.00930 0.00256 -0.0600 0.1497 1.0000
3.500 0.6194 0.00975 0.00280 -0.0592 0.1054 1.0000
3.750 0.6434 0.01010 0.00304 -0.0586 0.0807 1.0000
4.000 0.6677 0.01042 0.00328 -0.0580 0.0643 1.0000
4.250 0.6922 0.01073 0.00357 -0.0574 0.0520 1.0000
4.500 0.7169 0.01104 0.00385 -0.0568 0.0426 1.0000
4.750 0.7415 0.01136 0.00416 -0.0563 0.0345 1.0000
5.000 0.7656 0.01175 0.00452 -0.0556 0.0278 1.0000
5.250 0.7903 0.01206 0.00488 -0.0551 0.0252 1.0000
5.500 0.8146 0.01243 0.00527 -0.0544 0.0227 1.0000
5.750 0.8383 0.01289 0.00578 -0.0537 0.0204 1.0000
6.000 0.8607 0.01354 0.00651 -0.0527 0.0187 1.0000
6.250 0.8845 0.01398 0.00703 -0.0520 0.0180 1.0000
6.500 0.9080 0.01446 0.00758 -0.0513 0.0172 1.0000
6.750 0.9315 0.01494 0.00812 -0.0506 0.0160 1.0000
7.000 0.9549 0.01541 0.00865 -0.0499 0.0148 1.0000
7.250 0.9780 0.01593 0.00923 -0.0492 0.0137 1.0000
7.500 0.9974 0.01705 0.01046 -0.0478 0.0123 1.0000
7.750 1.0206 0.01755 0.01106 -0.0471 0.0119 1.0000
8.000 1.0437 0.01805 0.01166 -0.0464 0.0111 1.0000
8.250 1.0670 0.01849 0.01217 -0.0458 0.0099 1.0000
8.500 1.0902 0.01888 0.01262 -0.0452 0.0089 1.0000
8.750 1.1116 0.01955 0.01334 -0.0444 0.0080 1.0000
9.000 1.1311 0.02057 0.01450 -0.0431 0.0074 1.0000
9.250 1.1515 0.02141 0.01552 -0.0421 0.0068 1.0000
9.500 1.1707 0.02241 0.01669 -0.0408 0.0062 1.0000
9.750 1.1901 0.02328 0.01769 -0.0397 0.0057 1.0000
10.000 1.2090 0.02416 0.01870 -0.0385 0.0053 1.0000
10.250 1.2267 0.02514 0.01979 -0.0372 0.0049 1.0000
10.500 1.2373 0.02705 0.02194 -0.0350 0.0044 1.0000
10.750 1.2510 0.02846 0.02358 -0.0332 0.0043 1.0000
11.000 1.2631 0.02995 0.02529 -0.0312 0.0040 1.0000
11.250 1.2715 0.03173 0.02732 -0.0289 0.0038 1.0000
11.500 1.2792 0.03326 0.02908 -0.0264 0.0036 1.0000
11.750 1.2791 0.03522 0.03128 -0.0230 0.0035 1.0000
12.000 1.2754 0.03741 0.03371 -0.0194 0.0034 1.0000
12.250 1.2684 0.03986 0.03640 -0.0159 0.0033 1.0000
12.500 1.2581 0.04267 0.03945 -0.0128 0.0033 1.0000
12.750 1.2438 0.04602 0.04303 -0.0103 0.0032 1.0000
13.000 1.2230 0.05039 0.04764 -0.0088 0.0032 1.0000
13.250 1.1974 0.05604 0.05353 -0.0092 0.0032 1.0000
13.500 1.1646 0.06428 0.06201 -0.0131 0.0033 1.0000
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Polar data table (+)
Polar graphs
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