AH 94-156 (ah94156-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 94-156 (ah94156-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.43 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah94156-il-1000000-n5.txt Download as CSV file: xf-ah94156-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7164 0.05069 0.04742 -0.1043 0.7811 0.0059
-14.750 -0.7420 0.04408 0.04061 -0.1083 0.7779 0.0059
-14.500 -0.7694 0.03889 0.03521 -0.1095 0.7749 0.0059
-14.250 -0.7756 0.03629 0.03248 -0.1092 0.7723 0.0059
-14.000 -0.7855 0.03369 0.02973 -0.1081 0.7693 0.0059
-13.750 -0.7795 0.03241 0.02835 -0.1071 0.7664 0.0060
-13.500 -0.7830 0.03055 0.02633 -0.1052 0.7633 0.0060
-13.250 -0.7865 0.02877 0.02438 -0.1030 0.7604 0.0060
-13.000 -0.7835 0.02743 0.02293 -0.1010 0.7580 0.0061
-12.750 -0.7800 0.02614 0.02152 -0.0988 0.7556 0.0061
-12.500 -0.7855 0.02429 0.01949 -0.0955 0.7529 0.0063
-12.250 -0.7796 0.02322 0.01830 -0.0931 0.7504 0.0063
-12.000 -0.7722 0.02227 0.01724 -0.0908 0.7480 0.0064
-11.750 -0.7625 0.02152 0.01638 -0.0885 0.7457 0.0065
-11.500 -0.7512 0.02086 0.01563 -0.0863 0.7436 0.0066
-11.250 -0.7357 0.02023 0.01494 -0.0848 0.7415 0.0067
-11.000 -0.7175 0.01969 0.01433 -0.0837 0.7394 0.0069
-10.750 -0.6993 0.01908 0.01364 -0.0826 0.7374 0.0070
-10.500 -0.6810 0.01843 0.01289 -0.0815 0.7354 0.0070
-10.250 -0.6604 0.01794 0.01233 -0.0807 0.7334 0.0073
-10.000 -0.6403 0.01737 0.01166 -0.0798 0.7314 0.0074
-9.750 -0.6195 0.01681 0.01101 -0.0790 0.7295 0.0075
-9.500 -0.5976 0.01629 0.01043 -0.0783 0.7278 0.0077
-9.250 -0.5756 0.01576 0.00983 -0.0777 0.7261 0.0079
-9.000 -0.5528 0.01530 0.00929 -0.0771 0.7243 0.0080
-8.750 -0.5293 0.01489 0.00882 -0.0767 0.7225 0.0082
-8.500 -0.5058 0.01448 0.00834 -0.0762 0.7206 0.0083
-8.250 -0.4826 0.01402 0.00781 -0.0757 0.7188 0.0085
-8.000 -0.4595 0.01353 0.00727 -0.0752 0.7169 0.0089
-7.750 -0.4348 0.01323 0.00693 -0.0749 0.7151 0.0092
-7.500 -0.4097 0.01291 0.00658 -0.0747 0.7137 0.0095
-7.250 -0.3843 0.01260 0.00625 -0.0745 0.7122 0.0099
-7.000 -0.3590 0.01229 0.00591 -0.0743 0.7106 0.0102
-6.750 -0.3335 0.01199 0.00557 -0.0741 0.7087 0.0106
-6.500 -0.3078 0.01172 0.00526 -0.0739 0.7068 0.0109
-6.250 -0.2819 0.01146 0.00495 -0.0738 0.7050 0.0111
-6.000 -0.2566 0.01113 0.00460 -0.0735 0.7033 0.0118
-5.750 -0.2306 0.01089 0.00433 -0.0734 0.7017 0.0124
-5.500 -0.2042 0.01069 0.00410 -0.0734 0.6999 0.0131
-5.250 -0.1774 0.01048 0.00388 -0.0734 0.6984 0.0139
-5.000 -0.1505 0.01029 0.00368 -0.0734 0.6966 0.0147
-4.750 -0.1239 0.01006 0.00346 -0.0734 0.6948 0.0159
-4.500 -0.0969 0.00988 0.00327 -0.0734 0.6929 0.0172
-4.250 -0.0697 0.00973 0.00309 -0.0735 0.6909 0.0184
-4.000 -0.0428 0.00954 0.00292 -0.0735 0.6890 0.0209
-3.750 -0.0156 0.00941 0.00277 -0.0736 0.6871 0.0233
-3.500 0.0115 0.00926 0.00262 -0.0737 0.6852 0.0280
-3.250 0.0389 0.00910 0.00250 -0.0738 0.6836 0.0345
-3.000 0.0663 0.00894 0.00238 -0.0739 0.6818 0.0435
-2.750 0.0936 0.00877 0.00227 -0.0741 0.6795 0.0581
-2.500 0.1203 0.00856 0.00215 -0.0741 0.6771 0.0845
-2.250 0.1470 0.00834 0.00205 -0.0742 0.6748 0.1193
-2.000 0.1730 0.00807 0.00194 -0.0741 0.6724 0.1724
-1.750 0.1984 0.00775 0.00184 -0.0741 0.6699 0.2429
-1.500 0.2237 0.00737 0.00176 -0.0740 0.6671 0.3311
-1.250 0.2484 0.00695 0.00166 -0.0738 0.6637 0.4305
-1.000 0.2712 0.00637 0.00155 -0.0734 0.6606 0.5746
-0.750 0.2924 0.00578 0.00150 -0.0724 0.6577 0.7308
-0.500 0.3184 0.00585 0.00174 -0.0719 0.6550 0.7951
-0.250 0.3476 0.00592 0.00179 -0.0722 0.6518 0.8098
0.000 0.3764 0.00600 0.00186 -0.0725 0.6485 0.8184
0.250 0.4052 0.00609 0.00191 -0.0729 0.6449 0.8266
0.500 0.4334 0.00619 0.00198 -0.0730 0.6415 0.8313
0.750 0.4620 0.00628 0.00208 -0.0732 0.6382 0.8357
1.000 0.4907 0.00637 0.00215 -0.0735 0.6344 0.8401
1.250 0.5193 0.00644 0.00219 -0.0739 0.6305 0.8434
1.500 0.5470 0.00652 0.00226 -0.0740 0.6268 0.8459
1.750 0.5752 0.00659 0.00234 -0.0742 0.6224 0.8482
2.000 0.6032 0.00666 0.00240 -0.0744 0.6169 0.8504
2.250 0.6309 0.00674 0.00245 -0.0745 0.6114 0.8522
2.500 0.6593 0.00678 0.00249 -0.0749 0.6059 0.8536
2.750 0.6871 0.00685 0.00253 -0.0751 0.5995 0.8548
3.000 0.7150 0.00691 0.00258 -0.0754 0.5932 0.8559
3.250 0.7423 0.00699 0.00263 -0.0756 0.5842 0.8567
3.500 0.7695 0.00708 0.00269 -0.0757 0.5747 0.8575
3.750 0.7962 0.00718 0.00276 -0.0758 0.5655 0.8581
4.000 0.8223 0.00729 0.00283 -0.0757 0.5543 0.8587
4.250 0.8470 0.00743 0.00293 -0.0754 0.5395 0.8593
4.500 0.8713 0.00760 0.00305 -0.0751 0.5248 0.8600
4.750 0.8957 0.00776 0.00317 -0.0747 0.5113 0.8605
5.000 0.9188 0.00797 0.00333 -0.0741 0.4957 0.8611
5.250 0.9408 0.00820 0.00351 -0.0733 0.4794 0.8617
5.500 0.9621 0.00845 0.00371 -0.0724 0.4635 0.8624
5.750 0.9830 0.00870 0.00391 -0.0715 0.4483 0.8631
6.250 1.0224 0.00921 0.00434 -0.0691 0.4193 0.8642
6.500 1.0411 0.00947 0.00456 -0.0678 0.4064 0.8648
6.750 1.0530 0.00978 0.00482 -0.0650 0.3901 0.8656
7.000 1.0616 0.01018 0.00516 -0.0618 0.3719 0.8668
7.250 1.0699 0.01068 0.00558 -0.0586 0.3515 0.8677
7.500 1.0778 0.01124 0.00607 -0.0556 0.3319 0.8685
7.750 1.0842 0.01192 0.00666 -0.0525 0.3106 0.8694
8.000 1.0926 0.01260 0.00726 -0.0499 0.2907 0.8701
8.250 1.0963 0.01352 0.00806 -0.0467 0.2646 0.8709
8.500 1.1043 0.01434 0.00879 -0.0443 0.2443 0.8715
8.750 1.1091 0.01534 0.00966 -0.0416 0.2201 0.8722
9.000 1.1122 0.01647 0.01065 -0.0387 0.1925 0.8728
9.250 1.1148 0.01766 0.01170 -0.0359 0.1646 0.8737
9.500 1.1218 0.01867 0.01262 -0.0338 0.1445 0.8745
9.750 1.1266 0.01984 0.01368 -0.0315 0.1216 0.8752
10.000 1.1311 0.02108 0.01480 -0.0292 0.1003 0.8758
10.250 1.1366 0.02229 0.01592 -0.0272 0.0804 0.8764
10.500 1.1443 0.02343 0.01699 -0.0255 0.0665 0.8770
10.750 1.1534 0.02450 0.01803 -0.0240 0.0559 0.8775
11.000 1.1629 0.02559 0.01909 -0.0226 0.0465 0.8781
11.250 1.1710 0.02680 0.02027 -0.0212 0.0370 0.8786
11.500 1.1817 0.02788 0.02134 -0.0200 0.0314 0.8791
11.750 1.1908 0.02911 0.02254 -0.0188 0.0252 0.8796
12.000 1.2014 0.03025 0.02369 -0.0178 0.0219 0.8802
12.250 1.2120 0.03143 0.02489 -0.0169 0.0184 0.8807
12.500 1.2220 0.03269 0.02616 -0.0159 0.0155 0.8812
12.750 1.2327 0.03391 0.02740 -0.0151 0.0138 0.8817
13.000 1.2427 0.03523 0.02874 -0.0143 0.0121 0.8822
13.250 1.2529 0.03656 0.03010 -0.0136 0.0107 0.8827
13.500 1.2622 0.03800 0.03158 -0.0128 0.0097 0.8833
13.750 1.2729 0.03933 0.03296 -0.0122 0.0090 0.8837
14.000 1.2817 0.04086 0.03453 -0.0116 0.0082 0.8842
14.250 1.2902 0.04246 0.03617 -0.0110 0.0076 0.8847
14.500 1.2989 0.04408 0.03784 -0.0105 0.0070 0.8852
14.750 1.3077 0.04572 0.03953 -0.0101 0.0066 0.8857
15.000 1.3154 0.04749 0.04135 -0.0097 0.0063 0.8861
15.250 1.3223 0.04937 0.04328 -0.0093 0.0059 0.8866
15.500 1.3287 0.05136 0.04532 -0.0090 0.0057 0.8871
16.000 1.3402 0.05557 0.04968 -0.0086 0.0052 0.8884
16.250 1.3461 0.05773 0.05191 -0.0085 0.0051 0.8890
16.500 1.3516 0.05996 0.05421 -0.0085 0.0048 0.8896
16.750 1.3561 0.06236 0.05669 -0.0086 0.0049 0.8902
17.000 1.3597 0.06491 0.05931 -0.0087 0.0046 0.8907
17.250 1.3629 0.06757 0.06205 -0.0089 0.0044 0.8913
17.500 1.3655 0.07036 0.06491 -0.0093 0.0043 0.8918
17.750 1.3671 0.07330 0.06794 -0.0098 0.0042 0.8924
18.000 1.3681 0.07639 0.07112 -0.0103 0.0041 0.8929
18.250 1.3690 0.07959 0.07439 -0.0110 0.0040 0.8935
18.500 1.3639 0.08368 0.07858 -0.0119 0.0037 0.8940
18.750 1.3650 0.08695 0.08194 -0.0129 0.0037 0.8946
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Polar data table (+)
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