AH 93-157 (ah93157-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-157 (ah93157-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.6 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93157-il-1000000.txt Download as CSV file: xf-ah93157-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-157
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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6515 0.05018 0.04711 -0.1225 0.8423 0.0112
-15.000 -0.6746 0.04346 0.04016 -0.1273 0.8354 0.0112
-14.750 -0.6923 0.03904 0.03555 -0.1290 0.8295 0.0112
-14.500 -0.6999 0.03628 0.03265 -0.1290 0.8244 0.0114
-14.250 -0.7089 0.03379 0.02999 -0.1280 0.8193 0.0115
-14.000 -0.7160 0.03165 0.02768 -0.1264 0.8146 0.0115
-13.750 -0.7167 0.03009 0.02600 -0.1247 0.8108 0.0118
-13.500 -0.7214 0.02830 0.02405 -0.1222 0.8069 0.0118
-13.250 -0.7172 0.02719 0.02281 -0.1201 0.8033 0.0120
-13.000 -0.7133 0.02607 0.02154 -0.1179 0.7994 0.0121
-12.750 -0.7077 0.02503 0.02040 -0.1156 0.7966 0.0122
-12.500 -0.7007 0.02409 0.01934 -0.1133 0.7934 0.0123
-12.250 -0.6893 0.02349 0.01865 -0.1114 0.7905 0.0125
-12.000 -0.6958 0.02152 0.01646 -0.1072 0.7874 0.0128
-11.750 -0.6887 0.02061 0.01543 -0.1045 0.7842 0.0130
-11.500 -0.6773 0.02002 0.01480 -0.1022 0.7819 0.0133
-11.250 -0.6641 0.01957 0.01431 -0.1000 0.7794 0.0136
-11.000 -0.6480 0.01922 0.01391 -0.0983 0.7769 0.0140
-10.750 -0.6309 0.01867 0.01329 -0.0969 0.7744 0.0142
-10.500 -0.6130 0.01812 0.01265 -0.0955 0.7721 0.0146
-10.250 -0.5946 0.01756 0.01198 -0.0942 0.7696 0.0149
-10.000 -0.5741 0.01715 0.01148 -0.0932 0.7671 0.0153
-9.750 -0.5527 0.01676 0.01103 -0.0924 0.7653 0.0156
-9.500 -0.5367 0.01574 0.00991 -0.0907 0.7630 0.0161
-9.250 -0.5165 0.01519 0.00932 -0.0897 0.7607 0.0167
-9.000 -0.4943 0.01479 0.00889 -0.0890 0.7585 0.0171
-8.750 -0.4713 0.01446 0.00852 -0.0883 0.7563 0.0176
-8.500 -0.4480 0.01414 0.00813 -0.0877 0.7540 0.0183
-8.250 -0.4240 0.01390 0.00782 -0.0872 0.7515 0.0189
-8.000 -0.3993 0.01365 0.00754 -0.0868 0.7499 0.0193
-7.750 -0.3798 0.01290 0.00674 -0.0856 0.7478 0.0203
-7.500 -0.3559 0.01257 0.00640 -0.0851 0.7456 0.0211
-7.250 -0.3311 0.01231 0.00612 -0.0847 0.7434 0.0221
-7.000 -0.3063 0.01204 0.00581 -0.0843 0.7413 0.0229
-6.750 -0.2811 0.01182 0.00554 -0.0839 0.7391 0.0237
-6.500 -0.2580 0.01142 0.00511 -0.0833 0.7366 0.0254
-6.250 -0.2325 0.01121 0.00489 -0.0830 0.7346 0.0268
-6.000 -0.2069 0.01100 0.00466 -0.0827 0.7326 0.0281
-5.750 -0.1823 0.01068 0.00433 -0.0822 0.7304 0.0300
-5.500 -0.1569 0.01044 0.00410 -0.0819 0.7281 0.0323
-5.250 -0.1306 0.01029 0.00392 -0.0817 0.7259 0.0345
-5.000 -0.1054 0.01003 0.00366 -0.0814 0.7237 0.0383
-4.750 -0.0790 0.00990 0.00350 -0.0812 0.7212 0.0416
-4.500 -0.0534 0.00969 0.00331 -0.0810 0.7190 0.0469
-4.250 -0.0271 0.00952 0.00316 -0.0808 0.7169 0.0523
-4.000 -0.0011 0.00933 0.00301 -0.0806 0.7145 0.0604
-3.750 0.0249 0.00913 0.00286 -0.0804 0.7120 0.0712
-3.500 0.0510 0.00895 0.00272 -0.0802 0.7095 0.0856
-3.250 0.0768 0.00876 0.00259 -0.0800 0.7069 0.1076
-3.000 0.1026 0.00858 0.00250 -0.0798 0.7041 0.1359
-2.750 0.1276 0.00832 0.00240 -0.0795 0.7020 0.1777
-2.500 0.1519 0.00801 0.00230 -0.0791 0.6992 0.2351
-2.250 0.1753 0.00764 0.00220 -0.0785 0.6965 0.3144
-2.000 0.1977 0.00721 0.00209 -0.0778 0.6938 0.4138
-1.750 0.2173 0.00664 0.00195 -0.0766 0.6909 0.5516
-1.500 0.2326 0.00593 0.00189 -0.0742 0.6880 0.7392
-1.250 0.2570 0.00593 0.00211 -0.0733 0.6851 0.8083
-1.000 0.2848 0.00601 0.00218 -0.0733 0.6819 0.8289
-0.750 0.3127 0.00613 0.00228 -0.0732 0.6787 0.8388
-0.500 0.3408 0.00626 0.00235 -0.0732 0.6755 0.8463
-0.250 0.3686 0.00641 0.00250 -0.0731 0.6723 0.8522
0.000 0.3964 0.00653 0.00259 -0.0731 0.6687 0.8592
0.250 0.4236 0.00665 0.00273 -0.0729 0.6649 0.8631
0.500 0.4504 0.00684 0.00290 -0.0725 0.6612 0.8684
0.750 0.4774 0.00705 0.00307 -0.0722 0.6576 0.8754
1.000 0.5021 0.00721 0.00328 -0.0713 0.6537 0.8800
1.250 0.5278 0.00736 0.00343 -0.0707 0.6493 0.8851
1.500 0.5546 0.00750 0.00352 -0.0705 0.6449 0.8901
1.750 0.5791 0.00752 0.00355 -0.0697 0.6406 0.8927
2.000 0.6057 0.00752 0.00356 -0.0696 0.6359 0.8942
2.250 0.6325 0.00754 0.00355 -0.0695 0.6310 0.8954
2.500 0.6593 0.00756 0.00355 -0.0695 0.6261 0.8968
2.750 0.6865 0.00756 0.00356 -0.0696 0.6206 0.8982
3.000 0.7132 0.00760 0.00357 -0.0696 0.6151 0.8995
3.250 0.7404 0.00762 0.00359 -0.0697 0.6093 0.9008
3.500 0.7673 0.00766 0.00362 -0.0698 0.6025 0.9022
3.750 0.7941 0.00773 0.00366 -0.0699 0.5960 0.9032
4.000 0.8206 0.00776 0.00369 -0.0699 0.5887 0.9042
4.250 0.8444 0.00777 0.00368 -0.0692 0.5818 0.9054
4.500 0.8695 0.00779 0.00371 -0.0689 0.5739 0.9063
4.750 0.8935 0.00786 0.00376 -0.0684 0.5659 0.9073
5.000 0.9179 0.00792 0.00382 -0.0679 0.5571 0.9082
5.250 0.9411 0.00802 0.00390 -0.0673 0.5476 0.9094
5.750 0.9865 0.00824 0.00409 -0.0658 0.5270 0.9118
6.000 1.0085 0.00837 0.00420 -0.0649 0.5168 0.9129
6.250 1.0287 0.00853 0.00434 -0.0637 0.5055 0.9140
6.500 1.0478 0.00871 0.00449 -0.0623 0.4922 0.9154
6.750 1.0648 0.00890 0.00464 -0.0605 0.4781 0.9167
7.000 1.0801 0.00908 0.00481 -0.0583 0.4653 0.9176
7.250 1.0932 0.00925 0.00495 -0.0558 0.4531 0.9189
7.500 1.1050 0.00950 0.00517 -0.0530 0.4402 0.9204
7.750 1.1109 0.00990 0.00550 -0.0491 0.4193 0.9223
8.000 1.1143 0.01041 0.00592 -0.0451 0.3986 0.9243
8.250 1.1215 0.01091 0.00636 -0.0419 0.3799 0.9259
8.500 1.1271 0.01151 0.00689 -0.0385 0.3593 0.9275
8.750 1.1331 0.01217 0.00749 -0.0354 0.3406 0.9291
9.000 1.1382 0.01293 0.00816 -0.0324 0.3221 0.9307
9.250 1.1471 0.01359 0.00878 -0.0300 0.3072 0.9321
9.500 1.1533 0.01435 0.00949 -0.0272 0.2896 0.9337
9.750 1.1602 0.01516 0.01023 -0.0247 0.2718 0.9352
10.000 1.1670 0.01601 0.01103 -0.0223 0.2543 0.9368
10.250 1.1739 0.01691 0.01187 -0.0200 0.2370 0.9383
10.500 1.1789 0.01794 0.01282 -0.0176 0.2182 0.9399
10.750 1.1829 0.01905 0.01384 -0.0151 0.1983 0.9418
11.000 1.1859 0.02026 0.01495 -0.0127 0.1764 0.9434
11.250 1.1887 0.02155 0.01613 -0.0103 0.1556 0.9448
11.500 1.1912 0.02296 0.01744 -0.0082 0.1331 0.9467
11.750 1.1948 0.02437 0.01876 -0.0064 0.1140 0.9486
12.000 1.1951 0.02608 0.02034 -0.0043 0.0911 0.9507
12.250 1.1995 0.02763 0.02182 -0.0029 0.0737 0.9526
12.500 1.2021 0.02941 0.02352 -0.0015 0.0575 0.9547
12.750 1.2085 0.03106 0.02512 -0.0006 0.0452 0.9567
13.000 1.2168 0.03279 0.02682 -0.0003 0.0362 0.9591
13.250 1.2287 0.03444 0.02848 -0.0005 0.0302 0.9616
13.500 1.2410 0.03625 0.03028 -0.0011 0.0248 0.9639
13.750 1.2540 0.03818 0.03222 -0.0019 0.0212 0.9658
14.000 1.2698 0.03992 0.03401 -0.0031 0.0189 0.9673
14.250 1.2821 0.04201 0.03614 -0.0041 0.0168 0.9687
14.500 1.2971 0.04387 0.03805 -0.0052 0.0154 0.9700
15.000 1.3203 0.04827 0.04255 -0.0074 0.0131 0.9801
15.250 1.3273 0.05031 0.04465 -0.0071 0.0124 1.0000
15.500 1.3321 0.05247 0.04686 -0.0067 0.0118 1.0000
15.750 1.3330 0.05504 0.04949 -0.0063 0.0111 1.0000
16.000 1.3361 0.05746 0.05197 -0.0061 0.0105 1.0000
16.250 1.3418 0.05960 0.05417 -0.0060 0.0102 1.0000
16.500 1.3441 0.06214 0.05678 -0.0058 0.0098 1.0000
16.750 1.3459 0.06477 0.05948 -0.0058 0.0095 1.0000
17.000 1.3475 0.06746 0.06224 -0.0058 0.0092 1.0000
17.250 1.3467 0.07047 0.06530 -0.0059 0.0088 1.0000
17.500 1.3378 0.07445 0.06938 -0.0060 0.0084 1.0000
17.750 1.3363 0.07766 0.07267 -0.0063 0.0083 1.0000
18.000 1.3359 0.08077 0.07586 -0.0066 0.0082 1.0000
18.250 1.3335 0.08419 0.07937 -0.0071 0.0080 1.0000
18.500 1.3321 0.08752 0.08277 -0.0076 0.0078 1.0000
18.750 1.3297 0.09099 0.08633 -0.0083 0.0077 1.0000
19.000 1.3258 0.09475 0.09017 -0.0091 0.0074 1.0000
19.250 1.3240 0.09825 0.09375 -0.0100 0.0073 1.0000
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