AH 94-156 (ah94156-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 94-156 (ah94156-il) Reynolds number: 100,000 Max Cl/Cd: 36.26 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah94156-il-100000-n5.txt Download as CSV file: xf-ah94156-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 94-156
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2204 0.09348 0.08819 -0.0966 0.8841 0.0293
-11.000 -0.2210 0.08903 0.08375 -0.0987 0.8800 0.0291
-10.750 -0.2201 0.08526 0.07999 -0.1004 0.8755 0.0288
-10.500 -0.2218 0.08088 0.07562 -0.1028 0.8713 0.0285
-10.250 -0.2335 0.07367 0.06840 -0.1077 0.8676 0.0282
-10.000 -0.2480 0.06759 0.06228 -0.1121 0.8628 0.0278
-9.750 -0.2670 0.06274 0.05734 -0.1142 0.8577 0.0274
-9.500 -0.2881 0.05859 0.05302 -0.1142 0.8530 0.0273
-9.250 -0.3061 0.05547 0.04975 -0.1128 0.8475 0.0270
-9.000 -0.3242 0.05290 0.04700 -0.1098 0.8425 0.0269
-8.750 -0.3363 0.05001 0.04382 -0.1070 0.8388 0.0270
-8.500 -0.3428 0.04736 0.04086 -0.1043 0.8350 0.0273
-8.250 -0.3464 0.04480 0.03795 -0.1016 0.8303 0.0278
-8.000 -0.3460 0.04225 0.03496 -0.0988 0.8265 0.0284
-7.750 -0.3418 0.03984 0.03199 -0.0961 0.8235 0.0292
-7.500 -0.3315 0.03771 0.02947 -0.0941 0.8208 0.0296
-7.250 -0.3190 0.03592 0.02747 -0.0926 0.8168 0.0300
-7.000 -0.3031 0.03436 0.02569 -0.0912 0.8133 0.0307
-6.750 -0.2842 0.03291 0.02401 -0.0902 0.8105 0.0314
-6.500 -0.2629 0.03153 0.02237 -0.0893 0.8083 0.0324
-6.250 -0.2401 0.03040 0.02101 -0.0886 0.8065 0.0343
-6.000 -0.2219 0.02966 0.02003 -0.0873 0.8023 0.0365
-5.750 -0.2007 0.02855 0.01886 -0.0865 0.7989 0.0382
-5.500 -0.1784 0.02765 0.01791 -0.0858 0.7961 0.0400
-5.250 -0.1552 0.02687 0.01704 -0.0851 0.7939 0.0426
-5.000 -0.1312 0.02623 0.01625 -0.0845 0.7920 0.0466
-4.750 -0.1161 0.02574 0.01582 -0.0828 0.7881 0.0500
-4.500 -0.1003 0.02539 0.01543 -0.0811 0.7839 0.0540
-4.250 -0.0816 0.02492 0.01491 -0.0797 0.7809 0.0606
-4.000 -0.0602 0.02447 0.01440 -0.0787 0.7785 0.0704
-3.750 -0.0382 0.02385 0.01385 -0.0778 0.7766 0.0881
-3.500 -0.0273 0.02372 0.01390 -0.0755 0.7715 0.1173
-3.250 -0.0137 0.02323 0.01384 -0.0736 0.7675 0.1994
-3.000 -0.0007 0.02227 0.01370 -0.0715 0.7645 0.3753
-2.750 0.0109 0.02142 0.01400 -0.0675 0.7623 0.6171
-2.500 0.0524 0.02274 0.01565 -0.0660 0.7614 0.7811
-2.250 0.0413 0.02356 0.01643 -0.0594 0.7541 0.8171
-2.000 0.0546 0.02418 0.01692 -0.0558 0.7503 0.8492
-1.750 0.0784 0.02458 0.01716 -0.0539 0.7480 0.8742
-1.500 0.1255 0.02488 0.01727 -0.0563 0.7469 0.8936
-1.250 0.1785 0.02499 0.01718 -0.0603 0.7460 0.9087
-1.000 0.2036 0.02551 0.01762 -0.0606 0.7402 0.9206
-0.750 0.2347 0.02565 0.01763 -0.0616 0.7366 0.9302
-0.500 0.2838 0.02555 0.01739 -0.0660 0.7346 0.9345
-0.250 0.3171 0.02542 0.01713 -0.0672 0.7324 0.9410
0.000 0.3580 0.02518 0.01677 -0.0698 0.7308 0.9447
0.250 0.3767 0.02577 0.01735 -0.0695 0.7236 0.9512
0.500 0.4015 0.02577 0.01728 -0.0694 0.7197 0.9566
0.750 0.4408 0.02556 0.01698 -0.0718 0.7176 0.9590
1.000 0.4791 0.02525 0.01660 -0.0739 0.7158 0.9615
1.250 0.4868 0.02602 0.01739 -0.0717 0.7071 0.9681
1.500 0.5181 0.02588 0.01721 -0.0726 0.7039 0.9709
1.750 0.5545 0.02560 0.01689 -0.0744 0.7018 0.9727
2.250 0.5962 0.02619 0.01749 -0.0736 0.6898 0.9804
2.500 0.6271 0.02590 0.01719 -0.0742 0.6873 0.9826
2.750 0.6639 0.02550 0.01677 -0.0759 0.6855 0.9838
3.000 0.6716 0.02643 0.01777 -0.0740 0.6751 0.9885
3.250 0.7044 0.02608 0.01743 -0.0749 0.6725 0.9902
3.500 0.7370 0.02574 0.01711 -0.0758 0.6700 0.9917
3.750 0.7422 0.02662 0.01805 -0.0733 0.6596 0.9963
4.000 0.7761 0.02618 0.01764 -0.0743 0.6571 0.9975
4.500 0.7943 0.02674 0.01830 -0.0688 0.6432 1.0000
5.000 0.7888 0.02723 0.01883 -0.0587 0.6283 1.0000
5.500 0.7886 0.02764 0.01930 -0.0499 0.6132 1.0000
6.000 0.7959 0.02793 0.01967 -0.0423 0.5982 1.0000
6.250 0.7820 0.02883 0.02058 -0.0366 0.5862 1.0000
6.500 0.8122 0.02807 0.01988 -0.0363 0.5833 1.0000
6.750 0.8081 0.02896 0.02080 -0.0324 0.5714 1.0000
7.000 0.8415 0.02814 0.02007 -0.0325 0.5683 1.0000
7.500 0.8620 0.02921 0.02126 -0.0287 0.5479 1.0000
7.750 0.8883 0.02888 0.02100 -0.0283 0.5409 1.0000
8.250 0.9378 0.02857 0.02085 -0.0274 0.5246 1.0000
8.500 0.9519 0.02914 0.02151 -0.0262 0.5131 1.0000
8.750 0.9755 0.02912 0.02157 -0.0257 0.5032 1.0000
9.000 1.0076 0.02858 0.02111 -0.0259 0.4942 1.0000
9.250 1.0245 0.02904 0.02165 -0.0250 0.4815 1.0000
9.500 1.0440 0.02935 0.02204 -0.0242 0.4690 1.0000
9.750 1.0650 0.02958 0.02235 -0.0236 0.4558 1.0000
10.000 1.0841 0.02990 0.02271 -0.0228 0.4407 1.0000
10.250 1.1006 0.03036 0.02320 -0.0217 0.4234 1.0000
10.500 1.1157 0.03092 0.02374 -0.0206 0.4049 1.0000
10.750 1.1256 0.03186 0.02468 -0.0192 0.3859 1.0000
11.000 1.1324 0.03306 0.02592 -0.0176 0.3660 1.0000
11.250 1.1394 0.03426 0.02709 -0.0161 0.3455 1.0000
11.500 1.1440 0.03569 0.02852 -0.0146 0.3242 1.0000
11.750 1.1471 0.03729 0.03009 -0.0131 0.3019 1.0000
12.000 1.1489 0.03907 0.03182 -0.0117 0.2786 1.0000
12.250 1.1492 0.04105 0.03373 -0.0103 0.2546 1.0000
12.500 1.1480 0.04329 0.03590 -0.0090 0.2290 1.0000
12.750 1.1461 0.04571 0.03824 -0.0079 0.2040 1.0000
13.000 1.1424 0.04841 0.04085 -0.0069 0.1790 1.0000
13.250 1.1378 0.05135 0.04368 -0.0061 0.1542 1.0000
13.500 1.1333 0.05441 0.04666 -0.0054 0.1304 1.0000
13.750 1.1286 0.05763 0.04979 -0.0050 0.1107 1.0000
14.000 1.1236 0.06100 0.05309 -0.0047 0.0931 1.0000
14.250 1.1190 0.06447 0.05652 -0.0046 0.0795 1.0000
14.500 1.1146 0.06802 0.06006 -0.0046 0.0684 1.0000
14.750 1.1105 0.07163 0.06371 -0.0048 0.0606 1.0000
15.000 1.1060 0.07542 0.06752 -0.0052 0.0542 1.0000
15.250 1.1035 0.07904 0.07123 -0.0056 0.0485 1.0000
15.500 1.0989 0.08303 0.07526 -0.0063 0.0444 1.0000
15.750 1.0967 0.08673 0.07908 -0.0070 0.0413 1.0000
16.000 1.0952 0.09043 0.08290 -0.0078 0.0378 1.0000
16.250 1.0911 0.09455 0.08706 -0.0088 0.0353 1.0000
16.500 1.0916 0.09798 0.09060 -0.0096 0.0333 1.0000
16.750 1.0934 0.10124 0.09399 -0.0104 0.0313 1.0000
17.000 1.0937 0.10479 0.09763 -0.0114 0.0294 1.0000
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Polar data table (+)
Polar graphs
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