AH 93-156 (ah93156-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AH 93-156 (ah93156-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.01 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93156-il-1000000.txt Download as CSV file: xf-ah93156-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-156
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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6432 0.05389 0.05081 -0.1174 0.8159 0.0111
-15.000 -0.6689 0.04604 0.04276 -0.1234 0.8118 0.0111
-14.750 -0.7001 0.03980 0.03627 -0.1261 0.8077 0.0110
-14.500 -0.7093 0.03689 0.03321 -0.1262 0.8037 0.0111
-14.250 -0.7139 0.03469 0.03091 -0.1255 0.8007 0.0112
-14.000 -0.7193 0.03264 0.02875 -0.1242 0.7974 0.0113
-13.750 -0.7287 0.03042 0.02635 -0.1219 0.7941 0.0113
-13.500 -0.7244 0.02932 0.02515 -0.1202 0.7910 0.0116
-13.250 -0.7216 0.02811 0.02382 -0.1182 0.7877 0.0117
-13.000 -0.7189 0.02688 0.02247 -0.1159 0.7851 0.0118
-12.750 -0.7169 0.02559 0.02106 -0.1133 0.7823 0.0120
-12.500 -0.7104 0.02463 0.01999 -0.1110 0.7797 0.0122
-12.250 -0.7050 0.02358 0.01880 -0.1084 0.7770 0.0123
-12.000 -0.6964 0.02277 0.01787 -0.1060 0.7744 0.0126
-11.750 -0.6864 0.02207 0.01706 -0.1037 0.7720 0.0127
-11.500 -0.6751 0.02147 0.01638 -0.1014 0.7699 0.0129
-11.250 -0.6611 0.02115 0.01598 -0.0994 0.7676 0.0131
-11.000 -0.6593 0.01935 0.01398 -0.0959 0.7652 0.0135
-10.750 -0.6440 0.01864 0.01319 -0.0943 0.7631 0.0138
-10.500 -0.6263 0.01807 0.01256 -0.0929 0.7611 0.0141
-10.250 -0.6077 0.01751 0.01192 -0.0917 0.7590 0.0144
-10.000 -0.5869 0.01714 0.01150 -0.0908 0.7568 0.0148
-9.750 -0.5664 0.01663 0.01093 -0.0899 0.7553 0.0152
-9.500 -0.5451 0.01616 0.01039 -0.0890 0.7535 0.0156
-9.250 -0.5232 0.01572 0.00988 -0.0882 0.7516 0.0160
-9.000 -0.4999 0.01540 0.00950 -0.0876 0.7497 0.0164
-8.750 -0.4817 0.01451 0.00852 -0.0863 0.7479 0.0171
-8.500 -0.4598 0.01403 0.00800 -0.0855 0.7462 0.0177
-8.250 -0.4359 0.01374 0.00767 -0.0850 0.7445 0.0184
-8.000 -0.4115 0.01350 0.00738 -0.0846 0.7424 0.0192
-7.750 -0.3869 0.01324 0.00709 -0.0842 0.7407 0.0199
-7.500 -0.3618 0.01300 0.00681 -0.0839 0.7392 0.0204
-7.250 -0.3407 0.01236 0.00613 -0.0829 0.7375 0.0217
-7.000 -0.3160 0.01207 0.00583 -0.0825 0.7358 0.0227
-6.750 -0.2906 0.01184 0.00558 -0.0823 0.7341 0.0239
-6.500 -0.2650 0.01161 0.00532 -0.0820 0.7324 0.0249
-6.250 -0.2408 0.01126 0.00493 -0.0815 0.7306 0.0264
-6.000 -0.2155 0.01101 0.00468 -0.0812 0.7289 0.0284
-5.750 -0.1894 0.01087 0.00450 -0.0811 0.7270 0.0302
-5.500 -0.1635 0.01068 0.00428 -0.0808 0.7254 0.0318
-5.250 -0.1385 0.01038 0.00401 -0.0805 0.7239 0.0350
-5.000 -0.1120 0.01023 0.00386 -0.0804 0.7222 0.0377
-4.750 -0.0864 0.00998 0.00362 -0.0801 0.7204 0.0419
-4.500 -0.0599 0.00982 0.00346 -0.0800 0.7187 0.0459
-4.250 -0.0338 0.00961 0.00327 -0.0798 0.7169 0.0521
-4.000 -0.0072 0.00946 0.00312 -0.0798 0.7151 0.0593
-3.750 0.0192 0.00930 0.00299 -0.0797 0.7134 0.0692
-3.500 0.0455 0.00914 0.00288 -0.0796 0.7113 0.0856
-3.250 0.0713 0.00894 0.00278 -0.0794 0.7097 0.1077
-3.000 0.0971 0.00872 0.00267 -0.0792 0.7079 0.1364
-2.750 0.1224 0.00846 0.00257 -0.0790 0.7059 0.1771
-2.500 0.1471 0.00816 0.00246 -0.0787 0.7037 0.2343
-2.250 0.1710 0.00780 0.00235 -0.0782 0.7017 0.3124
-2.000 0.1938 0.00737 0.00225 -0.0776 0.6995 0.4105
-1.750 0.2141 0.00681 0.00212 -0.0765 0.6968 0.5482
-1.500 0.2286 0.00605 0.00208 -0.0740 0.6943 0.7529
-1.250 0.2540 0.00608 0.00227 -0.0733 0.6918 0.8109
-1.000 0.2821 0.00616 0.00234 -0.0734 0.6894 0.8289
-0.750 0.3103 0.00627 0.00243 -0.0734 0.6869 0.8384
-0.500 0.3386 0.00638 0.00252 -0.0734 0.6845 0.8465
-0.250 0.3668 0.00656 0.00266 -0.0734 0.6820 0.8532
0.000 0.3951 0.00668 0.00275 -0.0736 0.6795 0.8592
0.250 0.4224 0.00680 0.00290 -0.0734 0.6770 0.8630
0.500 0.4495 0.00698 0.00308 -0.0731 0.6741 0.8688
0.750 0.4765 0.00713 0.00323 -0.0728 0.6714 0.8753
1.000 0.5021 0.00731 0.00341 -0.0721 0.6687 0.8797
1.250 0.5287 0.00751 0.00358 -0.0717 0.6657 0.8853
1.500 0.5551 0.00758 0.00367 -0.0714 0.6629 0.8899
1.750 0.5805 0.00759 0.00370 -0.0709 0.6596 0.8923
2.000 0.6077 0.00758 0.00369 -0.0708 0.6562 0.8938
2.250 0.6353 0.00759 0.00367 -0.0710 0.6528 0.8950
2.500 0.6628 0.00760 0.00367 -0.0711 0.6490 0.8964
2.750 0.6902 0.00758 0.00367 -0.0712 0.6447 0.8978
3.000 0.7178 0.00757 0.00366 -0.0714 0.6400 0.8991
3.250 0.7454 0.00760 0.00365 -0.0716 0.6356 0.9003
3.500 0.7733 0.00760 0.00369 -0.0719 0.6307 0.9016
3.750 0.8010 0.00763 0.00371 -0.0722 0.6247 0.9026
4.000 0.8275 0.00763 0.00370 -0.0722 0.6188 0.9035
4.250 0.8528 0.00760 0.00368 -0.0719 0.6116 0.9046
4.500 0.8777 0.00762 0.00369 -0.0715 0.6046 0.9057
4.750 0.9031 0.00765 0.00373 -0.0712 0.5961 0.9066
5.000 0.9278 0.00771 0.00377 -0.0709 0.5873 0.9075
5.250 0.9512 0.00779 0.00384 -0.0702 0.5769 0.9087
5.500 0.9750 0.00788 0.00392 -0.0697 0.5653 0.9099
5.750 0.9977 0.00800 0.00402 -0.0690 0.5527 0.9110
6.000 1.0188 0.00815 0.00414 -0.0680 0.5379 0.9122
6.250 1.0386 0.00834 0.00428 -0.0667 0.5221 0.9133
6.500 1.0559 0.00858 0.00446 -0.0650 0.5046 0.9147
6.750 1.0722 0.00883 0.00466 -0.0631 0.4884 0.9160
7.000 1.0835 0.00908 0.00486 -0.0602 0.4722 0.9172
7.250 1.0913 0.00929 0.00503 -0.0566 0.4566 0.9189
7.500 1.0991 0.00963 0.00533 -0.0531 0.4409 0.9205
7.750 1.1046 0.01005 0.00570 -0.0493 0.4244 0.9225
8.000 1.1107 0.01053 0.00614 -0.0458 0.4079 0.9244
8.250 1.1156 0.01113 0.00667 -0.0424 0.3886 0.9262
8.500 1.1215 0.01178 0.00727 -0.0393 0.3706 0.9278
8.750 1.1249 0.01258 0.00799 -0.0359 0.3502 0.9294
9.000 1.1294 0.01341 0.00873 -0.0329 0.3300 0.9309
9.250 1.1356 0.01416 0.00942 -0.0301 0.3116 0.9327
9.500 1.1364 0.01519 0.01034 -0.0268 0.2870 0.9345
9.750 1.1384 0.01625 0.01129 -0.0237 0.2610 0.9363
10.000 1.1460 0.01712 0.01210 -0.0215 0.2449 0.9377
10.250 1.1486 0.01826 0.01312 -0.0188 0.2201 0.9393
10.750 1.1582 0.02045 0.01514 -0.0142 0.1805 0.9426
11.000 1.1632 0.02160 0.01619 -0.0120 0.1608 0.9440
11.250 1.1677 0.02288 0.01738 -0.0101 0.1405 0.9457
11.500 1.1745 0.02409 0.01851 -0.0085 0.1222 0.9474
11.750 1.1781 0.02555 0.01987 -0.0066 0.1026 0.9492
12.000 1.1844 0.02692 0.02117 -0.0052 0.0854 0.9510
12.250 1.1892 0.02846 0.02263 -0.0038 0.0689 0.9529
12.500 1.1937 0.03012 0.02420 -0.0025 0.0528 0.9548
12.750 1.2020 0.03164 0.02568 -0.0018 0.0426 0.9568
13.000 1.2115 0.03326 0.02728 -0.0015 0.0335 0.9592
13.250 1.2222 0.03499 0.02899 -0.0016 0.0260 0.9616
13.500 1.2340 0.03681 0.03079 -0.0020 0.0201 0.9638
13.750 1.2471 0.03866 0.03266 -0.0028 0.0160 0.9656
14.000 1.2608 0.04054 0.03457 -0.0037 0.0132 0.9671
14.250 1.2738 0.04253 0.03660 -0.0047 0.0114 0.9685
14.500 1.2873 0.04451 0.03864 -0.0057 0.0101 0.9698
14.750 1.2981 0.04685 0.04103 -0.0067 0.0088 0.9734
15.000 1.3097 0.04890 0.04314 -0.0074 0.0082 0.9980
15.250 1.3161 0.05093 0.04522 -0.0071 0.0077 1.0000
15.500 1.3212 0.05306 0.04740 -0.0067 0.0075 1.0000
15.750 1.3178 0.05608 0.05051 -0.0061 0.0069 1.0000
16.000 1.3241 0.05815 0.05263 -0.0059 0.0067 1.0000
16.250 1.3265 0.06064 0.05520 -0.0057 0.0066 1.0000
16.500 1.3302 0.06304 0.05768 -0.0056 0.0063 1.0000
16.750 1.3301 0.06592 0.06064 -0.0055 0.0062 1.0000
17.000 1.3306 0.06878 0.06358 -0.0055 0.0061 1.0000
17.250 1.3324 0.07151 0.06639 -0.0056 0.0060 1.0000
17.500 1.3314 0.07460 0.06954 -0.0058 0.0057 1.0000
17.750 1.3303 0.07778 0.07281 -0.0060 0.0058 1.0000
18.000 1.3270 0.08129 0.07639 -0.0064 0.0056 1.0000
18.250 1.3229 0.08498 0.08017 -0.0070 0.0055 1.0000
18.500 1.3200 0.08855 0.08383 -0.0076 0.0055 1.0000
18.750 1.3099 0.09314 0.08850 -0.0085 0.0053 1.0000
19.000 1.3049 0.09716 0.09261 -0.0095 0.0053 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AH 93-156 (ah93156-il)