AH 94-156 (ah94156-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 94-156 (ah94156-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.15 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah94156-il-1000000.txt Download as CSV file: xf-ah94156-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4249 0.04563 0.04278 -0.1104 0.7733 0.0102
-10.750 -0.5322 0.03470 0.03126 -0.1029 0.7694 0.0097
-10.500 -0.5663 0.03097 0.02719 -0.0962 0.7664 0.0096
-10.250 -0.5739 0.02868 0.02463 -0.0922 0.7637 0.0099
-10.000 -0.5752 0.02625 0.02188 -0.0890 0.7609 0.0100
-9.750 -0.5686 0.02424 0.01961 -0.0866 0.7591 0.0102
-9.500 -0.5564 0.02263 0.01778 -0.0848 0.7572 0.0104
-9.250 -0.5411 0.02124 0.01618 -0.0833 0.7552 0.0105
-9.000 -0.5228 0.02014 0.01492 -0.0822 0.7532 0.0107
-8.750 -0.5020 0.01940 0.01403 -0.0814 0.7513 0.0109
-8.500 -0.4810 0.01853 0.01301 -0.0806 0.7493 0.0111
-8.250 -0.4603 0.01747 0.01177 -0.0798 0.7473 0.0113
-8.000 -0.4413 0.01597 0.01012 -0.0788 0.7451 0.0117
-7.750 -0.4181 0.01537 0.00949 -0.0783 0.7438 0.0121
-7.500 -0.3942 0.01484 0.00892 -0.0779 0.7421 0.0124
-7.250 -0.3695 0.01444 0.00848 -0.0777 0.7403 0.0129
-7.000 -0.3445 0.01406 0.00805 -0.0774 0.7384 0.0135
-6.750 -0.3193 0.01368 0.00761 -0.0771 0.7365 0.0140
-6.500 -0.2940 0.01332 0.00720 -0.0769 0.7348 0.0143
-6.250 -0.2700 0.01278 0.00658 -0.0764 0.7330 0.0146
-6.000 -0.2480 0.01208 0.00582 -0.0757 0.7311 0.0155
-5.750 -0.2227 0.01175 0.00548 -0.0755 0.7293 0.0162
-5.500 -0.1969 0.01145 0.00517 -0.0753 0.7277 0.0170
-5.250 -0.1708 0.01117 0.00486 -0.0752 0.7259 0.0178
-5.000 -0.1447 0.01089 0.00455 -0.0750 0.7240 0.0187
-4.750 -0.1195 0.01051 0.00415 -0.0748 0.7221 0.0205
-4.500 -0.0928 0.01030 0.00393 -0.0747 0.7203 0.0221
-4.250 -0.0661 0.01008 0.00367 -0.0747 0.7185 0.0238
-4.000 -0.0398 0.00984 0.00342 -0.0746 0.7166 0.0274
-3.750 -0.0130 0.00966 0.00322 -0.0746 0.7146 0.0319
-3.500 0.0138 0.00943 0.00304 -0.0746 0.7130 0.0404
-3.250 0.0403 0.00918 0.00288 -0.0746 0.7112 0.0577
-3.000 0.0661 0.00886 0.00272 -0.0745 0.7091 0.0978
-2.750 0.0912 0.00848 0.00256 -0.0743 0.7069 0.1609
-2.500 0.1155 0.00802 0.00241 -0.0741 0.7049 0.2515
-2.250 0.1392 0.00752 0.00228 -0.0738 0.7028 0.3620
-1.750 0.1822 0.00622 0.00202 -0.0723 0.6982 0.6685
-1.500 0.2048 0.00604 0.00228 -0.0711 0.6957 0.7889
-1.250 0.2338 0.00615 0.00235 -0.0713 0.6930 0.8136
-1.000 0.2625 0.00632 0.00249 -0.0714 0.6905 0.8265
-0.750 0.2905 0.00654 0.00270 -0.0713 0.6881 0.8351
-0.500 0.3194 0.00673 0.00282 -0.0715 0.6854 0.8421
-0.250 0.3473 0.00682 0.00293 -0.0715 0.6830 0.8462
0.000 0.3750 0.00696 0.00307 -0.0714 0.6804 0.8505
0.250 0.4033 0.00709 0.00319 -0.0715 0.6775 0.8560
0.500 0.4311 0.00716 0.00324 -0.0715 0.6748 0.8600
0.750 0.4581 0.00728 0.00334 -0.0712 0.6721 0.8631
1.000 0.4855 0.00741 0.00346 -0.0711 0.6693 0.8667
1.250 0.5136 0.00747 0.00353 -0.0713 0.6664 0.8704
1.500 0.5423 0.00752 0.00357 -0.0716 0.6634 0.8734
1.750 0.5686 0.00750 0.00355 -0.0714 0.6601 0.8756
2.000 0.5956 0.00756 0.00358 -0.0712 0.6566 0.8777
2.250 0.6229 0.00758 0.00362 -0.0713 0.6530 0.8798
2.500 0.6508 0.00759 0.00364 -0.0715 0.6491 0.8815
2.750 0.6790 0.00760 0.00365 -0.0718 0.6451 0.8832
3.000 0.7073 0.00765 0.00365 -0.0722 0.6410 0.8848
3.250 0.7360 0.00765 0.00369 -0.0726 0.6362 0.8861
3.500 0.7646 0.00768 0.00371 -0.0731 0.6307 0.8871
3.750 0.7917 0.00767 0.00368 -0.0732 0.6257 0.8881
4.000 0.8187 0.00763 0.00368 -0.0733 0.6199 0.8890
4.250 0.8450 0.00765 0.00367 -0.0733 0.6128 0.8898
4.500 0.8719 0.00766 0.00371 -0.0734 0.6055 0.8907
4.750 0.8981 0.00771 0.00375 -0.0733 0.5980 0.8915
5.000 0.9248 0.00775 0.00380 -0.0734 0.5892 0.8921
5.250 0.9502 0.00783 0.00387 -0.0732 0.5795 0.8930
5.500 0.9749 0.00794 0.00395 -0.0730 0.5682 0.8939
5.750 0.9998 0.00804 0.00405 -0.0727 0.5556 0.8945
6.000 1.0237 0.00818 0.00416 -0.0724 0.5421 0.8951
6.250 1.0462 0.00836 0.00430 -0.0717 0.5273 0.8961
6.500 1.0675 0.00857 0.00447 -0.0708 0.5115 0.8969
6.750 1.0858 0.00885 0.00468 -0.0694 0.4906 0.8976
7.000 1.1016 0.00918 0.00492 -0.0676 0.4677 0.8983
7.250 1.1146 0.00953 0.00519 -0.0652 0.4470 0.8992
7.500 1.1233 0.00986 0.00546 -0.0619 0.4271 0.9003
7.750 1.1326 0.01027 0.00581 -0.0589 0.4095 0.9009
8.000 1.1408 0.01078 0.00625 -0.0558 0.3912 0.9015
8.250 1.1467 0.01133 0.00673 -0.0526 0.3712 0.9025
8.500 1.1535 0.01194 0.00728 -0.0496 0.3512 0.9036
8.750 1.1589 0.01268 0.00795 -0.0466 0.3304 0.9047
9.000 1.1637 0.01354 0.00871 -0.0436 0.3064 0.9056
9.250 1.1674 0.01451 0.00957 -0.0407 0.2825 0.9064
9.500 1.1748 0.01538 0.01036 -0.0383 0.2619 0.9072
9.750 1.1787 0.01646 0.01133 -0.0357 0.2386 0.9080
10.000 1.1820 0.01761 0.01236 -0.0330 0.2127 0.9088
10.250 1.1864 0.01876 0.01340 -0.0307 0.1893 0.9095
10.500 1.1887 0.02007 0.01457 -0.0281 0.1633 0.9103
10.750 1.1933 0.02129 0.01568 -0.0260 0.1420 0.9111
11.000 1.1970 0.02261 0.01690 -0.0238 0.1200 0.9120
11.250 1.1980 0.02415 0.01829 -0.0216 0.0957 0.9128
11.500 1.2022 0.02556 0.01960 -0.0197 0.0780 0.9134
11.750 1.2065 0.02703 0.02098 -0.0180 0.0618 0.9139
12.000 1.2138 0.02835 0.02227 -0.0166 0.0510 0.9144
12.250 1.2202 0.02978 0.02365 -0.0153 0.0406 0.9149
12.500 1.2271 0.03123 0.02507 -0.0141 0.0325 0.9153
12.750 1.2347 0.03266 0.02648 -0.0130 0.0264 0.9160
13.000 1.2409 0.03422 0.02804 -0.0119 0.0210 0.9168
13.250 1.2478 0.03580 0.02961 -0.0109 0.0173 0.9175
13.500 1.2560 0.03731 0.03117 -0.0100 0.0151 0.9182
13.750 1.2629 0.03896 0.03284 -0.0092 0.0134 0.9189
14.000 1.2706 0.04059 0.03454 -0.0085 0.0123 0.9196
14.250 1.2792 0.04217 0.03617 -0.0079 0.0113 0.9204
14.500 1.2843 0.04412 0.03815 -0.0073 0.0103 0.9212
14.750 1.2891 0.04615 0.04026 -0.0067 0.0096 0.9220
15.000 1.2970 0.04793 0.04210 -0.0063 0.0093 0.9227
15.250 1.3030 0.04993 0.04417 -0.0059 0.0087 0.9235
15.500 1.3090 0.05198 0.04629 -0.0057 0.0085 0.9244
15.750 1.3144 0.05415 0.04851 -0.0055 0.0081 0.9252
16.000 1.3146 0.05694 0.05139 -0.0053 0.0077 0.9261
16.250 1.3087 0.06051 0.05507 -0.0051 0.0074 0.9268
16.500 1.3153 0.06272 0.05735 -0.0053 0.0071 0.9277
16.750 1.3168 0.06559 0.06031 -0.0055 0.0072 0.9286
17.000 1.3196 0.06839 0.06320 -0.0058 0.0069 0.9298
17.250 1.3223 0.07120 0.06610 -0.0062 0.0067 0.9313
17.500 1.3222 0.07445 0.06944 -0.0068 0.0065 0.9327
17.750 1.3228 0.07767 0.07276 -0.0075 0.0064 0.9343
18.000 1.3233 0.08099 0.07616 -0.0083 0.0062 0.9358
18.250 1.3230 0.08448 0.07975 -0.0092 0.0061 0.9375
18.500 1.3211 0.08826 0.08361 -0.0103 0.0058 0.9393
18.750 1.3168 0.09248 0.08793 -0.0117 0.0057 0.9410
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Polar data table (+)
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